CN116685765A - Fastening an exhaust cone in a turbine - Google Patents

Fastening an exhaust cone in a turbine Download PDF

Info

Publication number
CN116685765A
CN116685765A CN202180085307.4A CN202180085307A CN116685765A CN 116685765 A CN116685765 A CN 116685765A CN 202180085307 A CN202180085307 A CN 202180085307A CN 116685765 A CN116685765 A CN 116685765A
Authority
CN
China
Prior art keywords
exhaust
annular wall
fastening
annular
exhaust cone
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202180085307.4A
Other languages
Chinese (zh)
Inventor
托马斯·范戴洛斯
伯诺伊特·卡雷雷
埃里克·科内泰
金-菲利普·乔雷特
文森特·戴范莱
克莱门特·玛丽·伯诺伊特·劳西莱
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Ceramics SA
Original Assignee
Safran Ceramics SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Ceramics SA filed Critical Safran Ceramics SA
Priority claimed from PCT/FR2021/051948 external-priority patent/WO2022096832A1/en
Publication of CN116685765A publication Critical patent/CN116685765A/en
Pending legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)

Abstract

The present disclosure relates to an assembly for a turbine having a longitudinal axis, comprising: -an exhaust cone (102) comprising an outer annular wall (104) for the flow of a primary air flow and an annular box (106) arranged radially inside the outer annular wall (104), -an exhaust housing (111) arranged upstream of the exhaust cone (102) and connected to the exhaust cone, and wherein one end of the outer annular wall (104) or one end of the annular box (106) is free to move relative to the exhaust cone (102) or relative to the exhaust housing.

Description

Fastening an exhaust cone in a turbine
Technical Field
The present invention relates to a component for fastening an exhaust cone in a turbine of a turbine, in particular for fastening an exhaust cone made of a ceramic matrix composite.
Background
The present disclosure relates to an assembly located at the rear (downstream end) of an aircraft turbojet engine to optimise the flow of hot gases emitted by said turbojet engine and possibly absorb at least part of the noise generated by the interaction of these hot gases from the internal parts of the engine (combustion chamber, turbine) with ambient air and with the flow of cold air emitted by the fan of the turbojet engine.
More specifically, the present disclosure relates to the connection between an object, often referred to as an "exhaust cone", and a gas outlet from a turbojet engine located just upstream.
Typically, the exhaust cone is surrounded (surrounded) by a so-called "primary nozzle" portion.
The "exhaust cone" is intended to be positioned downstream of the turbine (section) of the turbojet engine, around which the main nozzle is placed concentrically. Both the exhaust cone and the main nozzle are fastened to the housing of the turbojet engine by means of a system for fastening by means of flanges.
An assembly for an aircraft turbojet engine is known, represented in fig. 1, comprising:
-a jet centre element which is annular about an axis (X) and adapted so that gas is ejected from the surrounding turbojet engine from upstream to downstream, and
a connecting flange interposed between the so-called metal outlet of the turbojet engine upstream and the central element downstream to connect them together.
The aforementioned axis X is the longitudinal or rotational axis of the turbine, in particular of the moving blades of the fan 20 and of the engine 12.
The jet centre element may correspond to the aforementioned exhaust cone (hereinafter denoted 1), or at least to the upstream portion 1a hereinafter.
In fig. 1a conventional exhaust cone 1 is shown, wherein the structure along the engine axis (axis X above) is located upstream (AM) and downstream (AV) to the left and right of the drawing, respectively.
More generally, an aircraft turbojet 10 is shown in FIG. 1, with a central portion forming a gas turbine engine 12 mounted inside an engine nacelle assembly 14, as is typical of aircraft designed for infrasonic wave operation, such as a turboprop or turbofan engine. In general, nacelle assembly 14 includes an engine nacelle 16 and a fan housing 18 that surrounds a fan 20 that is axially upstream of engine 12.
The engine 12 includes at least one turbine, which may be a low pressure turbine, axially in a downstream portion, and an exhaust casing 22, still in the downstream portion, including an inner annular shroud 22a and an outer annular shroud 22b, defining a downstream portion therebetween of a primary annular flow path 24 in which combustion gases originating from a combustion chamber of the engine 12 flow. Fig. 2 shows an enlarged schematic view of portion II of fig. 1.
The inner annular shroud 22a is axially connected at its downstream end to an upstream portion 1a of the exhaust cone 1, which may comprise an upstream portion 1a having a generally cylindrical shape and a downstream portion 1b having a conical shape. Furthermore, an acoustic box 3 is arranged inside the exhaust cone 1 to reduce noise pollution of the exhaust gases. The sound box 3 is connected at its upstream end to the inner annular shroud 22a and at its downstream end to the downstream portion of the exhaust cone.
In practice, it is still difficult to connect together the aforementioned metal outlet of the turbojet engine (which may be the inner annular shroud 22 a) with the central element (which may be the upstream portion 1a of the exhaust cone 1). In practice, at least one portion of the exhaust cone is made of a different material than the exhaust housing and/or than another portion of the exhaust cone, or at least one portion of the exhaust cone is subjected to a different temperature than the exhaust housing and/or than another portion of the exhaust cone, which induces thermo-mechanical stresses created by the different thermal gradients between the portion of the exhaust cone and the exhaust housing. The connection of the sound box to the exhaust housing and/or the exhaust cone is also complicated, since the material differences and the temperature differences and thus the resulting thermo-mechanical stresses are also different.
Disclosure of Invention
The present disclosure proposes an assembly using an annular box to exhaust cone that is more reliable and more robust to thermal gradients due to its connection to only any of the aforementioned parts.
To this end, the present disclosure provides a first assembly for a turbine of a turbomachine having a longitudinal axis, comprising:
an exhaust cone comprising an outer annular wall for the flow of a primary air flow and an annular tank arranged radially inside said outer annular wall,
an exhaust housing arranged upstream of and connected to the exhaust cone, and
wherein one end of the outer annular wall or one end of the annular case is free to move relative to the exhaust cone or relative to the exhaust housing.
The annular box may be an annular sound box allowing for reduced sound emissions.
Thus, the outer annular wall or annular box of the exhaust cone may be at least axially movable under the influence of thermal expansion without any risk of cracking and/or while limiting the level of thermo-mechanical stress at the origin of the damage or cracking. This allows limiting the influence of material differences and/or temperature differences between the annular box, the exhaust cone and the exhaust housing. Accordingly, the present disclosure provides an architecture that enables free, axial and radial expansion of the outer annular wall relative to the annular tank by decoupling between the annular tank and the outer annular wall upstream or downstream of the exhaust cone.
In the present disclosure, upstream and downstream are defined with respect to the air inlet and outlet of the turbine, the upstream corresponding to the air inlet and the downstream corresponding to the air outlet. Furthermore, the axial direction corresponds to the direction of the rotation axis of the turbine of the exhaust cone (which corresponds to the rotation axis of the turbine), and the radial direction is a direction perpendicular (i.e. radial) to the rotation axis.
In the present disclosure, one end of the outer annular wall or annular case may refer to an axially peripheral portion of the outer annular wall or annular case.
The free movement of the one end of the outer annular wall or the one end of the annular tank relative to the exhaust cone or relative to the exhaust housing may be that the one end of the outer annular wall or the one end of the annular tank does not have a mechanical connection with the exhaust cone or the exhaust housing.
According to one embodiment, the annular box may be connected to the exhaust cone on the one hand and to the exhaust housing on the other hand, and the upstream end of the outer annular wall may be free to move, in particular axially and radially, relative to the exhaust housing.
According to this embodiment, the exhaust cone is connected to the exhaust housing via an annular box. The outer annular wall of the exhaust cone may have an upstream end that is movable to keep the thermal expansion level low. This allows limiting the influence of material differences and/or thermal gradients between the annular box, the exhaust cone and the exhaust housing.
According to one embodiment, the outer annular wall of the exhaust cone may be connected to the exhaust cone on the one hand and to the exhaust housing on the other hand, and the upstream end of the annular tank may be free to move, in particular axially, relative to the exhaust housing.
According to this embodiment, the exhaust cone is connected to the exhaust housing via an outer annular wall. The annular box may have an upstream end that is movable to keep the thermal expansion level low. This allows limiting the influence of material differences and/or thermal gradients between the annular box, the exhaust cone and the exhaust housing.
According to one embodiment, the outer annular wall of the exhaust cone may be connected to the exhaust cone on the one hand and to the exhaust housing on the other hand, and the downstream end of the annular box may be free to move, in particular axially and radially, with respect to the exhaust cone.
According to this embodiment, the exhaust cone is connected to the exhaust housing via an outer annular wall. The annular box may have a downstream end that is movable to keep the thermal expansion level low. This allows limiting the influence of material differences and/or thermal gradients between the annular box, the exhaust cone and the exhaust housing.
The annular tank may include an inner annular wall arranged concentric with the outer annular wall, and the upstream end of the annular tank may correspond to an upstream end of the inner annular wall, and the downstream end of the annular tank may correspond to a downstream end of the inner annular wall.
The annular tank may comprise a plurality of partitions extending radially from (in particular in the direction of) the inner annular wall of the annular tank and extending axially along the inner annular wall. In case the box is an acoustic box allowing for reduced noise emission, the partitions thus form acoustic partitions.
According to one embodiment, the first assembly may comprise a connection means fastened to the exhaust housing and connected to the outer annular wall of the exhaust cone and/or to the annular box.
The fastening member may include an annular flange fastened to a corresponding flange of the exhaust housing about the longitudinal axis. Additionally, the fastening member may include a plurality of flexible fastening lugs circumferentially distributed about the longitudinal axis and connected to the annular flange. The fastening lugs may be connected to the outer annular wall of the exhaust cone and/or to the sound box.
The exhaust cone may be made of a ceramic matrix composite. The outer annular wall may be made of a ceramic matrix composite.
The annular tank, which may be an annular acoustic tank, particularly the inner annular wall and the acoustic partition, may be made of a ceramic matrix composite. Alternatively, the sound partition may be metallic.
The present disclosure provides a second assembly for a turbine of a turbomachine having a longitudinal axis, comprising:
an exhaust cone comprising an outer annular wall for the flow of a primary air flow and a tank arranged to comprise an inner annular wall arranged radially inwards from said outer annular wall,
an exhaust housing arranged upstream of the exhaust cone, and
-a connecting member interposed longitudinally between the exhaust housing and the exhaust cone, the connecting member being fastened to the exhaust housing and comprising first flexible fastening lugs distributed circumferentially around the longitudinal axis and second flexible fastening lugs distributed circumferentially around the longitudinal axis.
The first fastening tab may be connected to an upstream annular portion of the outer annular wall and the second fastening tab is connected to an upstream annular portion of the inner annular wall of the tank.
This arrangement allows decoupling of the connection of the housing to the exhaust cone and to the tank by using a connection member with two fastening lugs. In addition, the connection of the exhaust cone and the tank is achieved by flexible lugs that allow the portions of different thermal expansions to be absorbed by their deformation. This allows limiting the influence of material differences between the tank, the exhaust cone and the exhaust housing.
The connecting member of the second assembly may be used as the connecting member of the first assembly.
Each first fastening tab and each second fastening tab may include an intermediate portion disposed between the first end and the second end of the first fastening tab and an intermediate portion between the first end and the second end of the second fastening tab, respectively. The central portion may be configured to impart flexible properties to the first and second fastening lugs, respectively. The thickness of the intermediate portion may be different from the thickness of the first and second ends.
In the present disclosure, upstream and downstream are defined with respect to the air inlet and outlet of the turbine, the upstream corresponding to the air inlet and the downstream corresponding to the air outlet. Furthermore, the axial direction corresponds to the direction of the rotation axis of the impeller (which corresponds to the rotation axis of the impeller), and the radial direction is a direction perpendicular (i.e. radial) to the rotation axis. Similarly, the axial plane is the plane containing the axis of rotation of the impeller, and the radial plane is the plane perpendicular to this axis.
The first fastening lug may have a hardness that is lower than the hardness of the outer annular wall of the exhaust cone. The first fastening lug thus allows limiting the thermo-mechanical stresses on the exhaust housing and the tank due to its deformation. In particular, a lower stiffness of the first fastening tab may be obtained by the material properties and geometrical parameters of the first fastening tab.
The inner annular wall of the tank may be made of a metallic material or a ceramic matrix composite.
The second fastening lug may have a hardness that is lower than the hardness of the inner annular wall of the tank. The second fastening lug thus allows limiting the thermomechanical stresses on the exhaust housing and on the exhaust cone due to its deformation. In particular, a lower stiffness of the second fastening tab can be obtained by the material properties and geometrical parameters of the second fastening tab.
The inner annular wall of the tank may have a downstream portion connected to a downstream portion of the outer annular wall of the exhaust cone. The downstream portion of the inner annular wall of the housing may be connected to the downstream portion of the outer annular wall of the exhaust cone, for example by screwing. The downstream connecting member may be fastened to the downstream portion of the inner annular wall of the housing on the one hand and to the downstream portion of the outer annular wall of the exhaust cone on the other hand. The downstream connecting member may be formed from a flexible sheet. This enables relative movement between the tank and the exhaust cone and reduces the effects of thermo-mechanical stress.
Alternatively, the downstream portion of the annular wall may be free. In other words, the downstream portion of the inner annular wall of the tank may be free of connections, in particular the downstream portion of the outer annular wall of the exhaust cone. Thus, the downstream portion of the inner annular wall of the housing is free to move, which enables relative movement between the tank and the exhaust cone and reduces the effects of thermo-mechanical stresses.
The tank may be annular. The tank may include a plurality of sound zones extending radially outwardly from an inner annular wall of the tank. The sound partition may be made of a metallic material or a ceramic matrix composite. The box may be an acoustic box. The sound box allows limiting noise pollution due to the flow of gas from the turbine.
The number of second fastening tabs may be greater than the number of first fastening tabs.
The connecting member may include an annular flange extending radially and connected to the exhaust housing, to which the first and second fastening lugs are connected. The annular flange may be connected to a corresponding annular flange of the exhaust housing.
The first and second fastening lugs may be connected to the radially outer annular portion of the annular flange. The first and second fastening lugs may be connected to the radially outer end of the annular flange.
The first and second fastening lugs may be connected to a radially inner annular portion of the annular flange. The first and second fastening lugs may be connected to the radially inner end of the annular flange.
The first and second fastening lugs may extend perpendicular to the annular flange of the connecting member.
Each of the first fastening lugs may be circumferentially spaced apart from one of the second fastening lugs. Thus, the first fastening tab and the second fastening tab may, for example, be evenly distributed circumferentially around the longitudinal axis.
Each of the second fastening lugs may have a first end connected to the annular flange, and each of the first fastening lugs may have a first end connected to a first end of one of the second fastening lugs. Several, in particular two, of the first fastening lugs may be connected to the first end of one single second fastening lug.
In this context, connecting one part to another part or fastening one part to another part means fastening parts together by mechanical means (in particular screwing, welding) or creating a one-piece connection so that the two parts are fixed to each other.
The first fastening lug may be connected to a radially outer annular portion of the annular flange, in particular to one end of the annular flange, and the second fastening lug may be connected to a radially inner annular portion of the annular flange, in particular to one end of the annular flange. Thus, the first fastening tab and the second fastening tab are better decoupled.
Each of the first fastening lugs may have a first end connected to the annular flange and a second end connected to the upstream annular portion of the outer annular wall of the exhaust cone, and each of the second fastening lugs may have a first end connected at the second end of one of the first fastening lugs and a second end connected to the upstream annular portion of the inner annular wall of the tank.
The first end of each second fastening lug may be connected to the second end of one of the first fastening lugs by screwing.
The first end of each second fastening tab may coincide with the second end of one of the first fastening tabs such that the first fastening tab and the second fastening tab form one unitary piece.
The second end of each of the second fastening lugs may be disposed upstream of and radially inward relative to the first end of the second fastening lug.
The second end of each of the second fastening lugs may be disposed downstream of and radially inward relative to the first end of the second fastening lug.
Each first end of one of the first fastening lugs may be connected to a radially outer annular portion of the annular flange, in particular to one end of the annular flange.
Each of the second fastening lugs may have a first end connected to the annular flange and a second end connected to the upstream annular portion of the inner annular wall of the tank, and each of the first fastening lugs may have a first end connected to the second end of one of the second fastening lugs and a second end connected to the upstream annular portion of the outer annular wall.
The first end of each first fastening lug may be connected to the second end of one of the second fastening lugs by screwing.
The first end of each first fastening tab may coincide with the second end of one of the second fastening tabs such that the first fastening tab and the second fastening tab form one unitary piece.
The second end of each of the first fastening lugs may be disposed upstream of and radially outward of the first end of the first fastening lug.
The second end of each of the first fastening lugs may be disposed downstream of and radially outward of the first end of the first fastening lug.
Each first end of the second fastening lugs may be connected to a radially inner annular portion of the annular flange, in particular to one end of the annular flange.
At least one of the first fastening tabs, and in particular each of the first fastening tabs, may extend radially outwardly about the longitudinal axis in a first manner in a circumferential direction.
At least one of the first fastening lugs, and in particular each of the first fastening lugs, may extend radially outwardly about the longitudinal axis in a second manner circumferentially opposite the first manner.
Each first fastening tab extending in the first manner may alternate with a first fastening tab extending in the second manner. The first end of each first fastening tab extending in the first manner may be disposed adjacent to the first end of the first fastening tab extending in the second manner.
The exhaust cone, and in particular the outer annular wall of the exhaust cone, may be made of a ceramic matrix composite. The exhaust housing may be made of a metallic material. The connection member may be made of a metal material.
The upstream annular end of the outer annular wall of the exhaust cone may be longitudinally aligned with the annular shroud of the exhaust casing. This shroud defines an inner annular surface externally for the flow of primary air flow from the turbine.
The present disclosure also relates to a turbine comprising a first or second assembly of the aforementioned type.
Drawings
Fig. 1, which has been described, shows a schematic cross-section of a turbine for an aircraft.
FIG. 2, which has been described, shows a schematic side view of the downstream portion of the turbine of FIG. 1.
Fig. 3 is a schematic representation of a side view of a first example of the assembly of an exhaust cone to an exhaust housing.
Fig. 4 is a schematic representation of a side view of a variation of the first example of assembling an exhaust cone to an exhaust housing.
Fig. 5 is a schematic representation of a side view of a second example of the assembly of an exhaust cone to an exhaust housing.
Fig. 6 is a schematic representation of a side view of a third example of the assembly of an exhaust cone to an exhaust housing.
Fig. 7a and 7b show a schematic perspective view of a first example of a connecting member and a schematic perspective view of an exhaust cone provided with the first example of a connecting member, respectively.
Fig. 8a, 8b and 8c show a schematic perspective view of an exhaust cone equipped with a second example of a connecting member, a schematic perspective view of a second example of a connecting member and a schematic side cross-sectional view of a second connecting member, respectively.
Fig. 9a and 9b show schematic side cross-sectional views of a third example of a connecting member.
Fig. 10a and 10b show a schematic partial perspective view of a fourth example of a connecting member and a schematic side cross-sectional view of a fourth example of a connecting member, respectively.
Fig. 11a and 11b show a schematic partial perspective view of a fifth example of a connecting member and a schematic side cross-sectional view of the fifth example of a connecting member, respectively.
Fig. 12a, 12b and 12c show a schematic side cross-sectional view, a schematic front cross-sectional view according to axis AA and a schematic perspective view, respectively, of a sixth example of a connecting member.
Fig. 13a and 13b show a schematic front cross-sectional view and a schematic perspective view, respectively, of a seventh example of a connecting member.
Fig. 14a and 14b show a schematic side cross-sectional view and a schematic perspective view, respectively, of an eighth example of a connecting member.
Fig. 15 shows a schematic perspective view of a ninth example of the connecting member.
Fig. 16a and 16d show schematic side cross-sectional views of a tenth example of a connecting member, and fig. 16b and 16c show schematic perspective views of the tenth example of a connecting member.
Fig. 17a and 17b show schematic side cross-sectional views of an eleventh example of a connecting member.
Fig. 18a and 18b show schematic side cross-sectional views of a twelfth example of a connecting member.
Fig. 19a and 19b show schematic side cross-sectional views of a thirteenth example of a connecting member, and fig. 19c shows a schematic perspective view of the thirteenth example.
Detailed Description
Referring to fig. 3, the exhaust cone 102 may be the exhaust cone 1 of the turbine 1 of fig. 1 and includes an outer annular wall 104 surrounding the longitudinal axis X and forming a flow path for the primary flow at the outlet of the turbine arranged upstream of the exhaust cone 102. The exhaust cone 102 is made of a ceramic matrix composite material and the outer annular wall 104 is made of a ceramic matrix composite material.
The annular acoustic box 106 is further disposed in the exhaust cone 102 to absorb a portion of the noise generated by the turbine including the exhaust cone 102. The sound box 106 includes an inner annular wall 108 disposed in the outer annular wall 104 of the exhaust cone 102. The sound box 106 further includes a plurality of partitions 110 extending radially from the inner annular wall 108 of the sound box 106 and extending axially along the wall 108.
The inner annular wall 108 and/or the sound partition is made of a ceramic matrix composite or a metallic material.
The inner annular wall 108 is fastened, for example by screwing, to the exhaust cone 102 and is connected to a shroud 112 of an exhaust housing 111 of the turbine. The shroud 112 of the exhaust housing 111 is arranged to engage the outer annular wall 104 so as to define an upstream portion of the flow path of the primary flow from the turbine.
The inner annular wall 108 is connected to a shroud 112 of the exhaust housing 111 via a connecting member 114.
The outer annular wall 104 is connected at its downstream end to the exhaust cone 102. The upstream end of the outer annular wall 104 has no mechanical connection and it is free to move, in particular axially and radially, relative to the shroud 112 (i.e., relative to the exhaust housing). The upstream end of the outer annular wall 104 is disposed in sliding contact with the shroud 112.
The outer annular wall 104 of the injection cone 102 has an upstream end that is capable of moving axially and radially when thermal expansion is substantial. This allows limiting the material differences and/or the influence of thermal gradients between the sound box, the exhaust cone and the exhaust housing.
In the variant represented in fig. 4, the outer annular wall 104 may also have an upstream end extending up to the exhaust housing 111. In this case, the shroud 112 is not necessary, and the connection member 114 is directly attached to the exhaust housing 111, particularly to a flange of the exhaust housing 111. Thus, the upstream end of the outer annular wall 104 is not in contact. The outer annular wall 104 then defines an upstream portion of the flow path of the primary flow from the turbine.
In the variant represented in fig. 5, the upstream end of the outer annular wall 104 is connected to the connecting member 114, whereas the upstream end of the inner annular wall 108 of the sound box 106 has no connection with said connecting member 114. The upstream end of the inner annular wall 108 of the sound box 106 is free to move, in particular axially and radially, relative to the shroud 112 (i.e. relative to the exhaust housing).
The inner annular wall 108 of the acoustic box 106 has an upstream end that is capable of moving axially and radially when thermal expansion is substantial. This allows limiting the material differences and/or the influence of thermal gradients between the sound box, the exhaust cone and the exhaust housing.
In this variant, the exhaust cone 102 is connected to the exhaust housing 111 by an outer annular wall 104.
In the variant represented in fig. 6, the upstream end of the outer annular wall 104 is connected to the connecting member 114, and the upstream end of the inner annular wall 108 of the sound box 106 is also connected to the connecting member 114. Conversely, the downstream end of the inner annular wall 108 of the sound box 106 has no connection to the exhaust cone 102. The downstream end of the inner annular wall 108 of the sound box 106 is free to move, in particular axially and radially, relative to the exhaust cone 102.
The inner annular wall 108 of the acoustic box 106 has a downstream end that is capable of moving axially and radially when thermal expansion is substantial. This allows limiting the material differences and/or the influence of thermal gradients between the sound box, the exhaust cone and the exhaust housing.
In this variant, the exhaust cone 102 is connected to the exhaust housing 111 via an outer annular wall 104.
Although the description is made with reference to a ring tank, the description is also applicable to ring tanks that are not necessarily acoustic.
FIG. 7 illustrates an upstream portion of a turbine wheel, such as the turbine of FIG. 1. The turbine includes an exhaust cone 102 that includes an outer annular wall 104 that defines a flow path for primary air flow from the turbine. The shroud 106-1 is disposed upstream AM of an outer annular wall that is disposed in engagement with the outer annular wall 104 of the exhaust casing and the exhaust cone 102, not shown in fig. 7, and defines an annular surface for the flow of primary air flow from the turbine. The box 106 is disposed in the exhaust cone 102 and is configured to absorb a portion of the noise generated by the turbine. The tank 106 includes an inner annular wall 108 disposed concentric with the outer annular wall 104 of the exhaust cone 102. The tank 106 comprises a partition 110 extending radially from the inner annular wall 108 in the direction of the outer annular wall 104.
The outer annular wall 104 of the exhaust cone 102 is made of a ceramic matrix composite or metal. The tank 106, and in particular the inner annular wall 108 and the partitions 110, are made of a ceramic matrix composite or metal.
The connection member 100 is used to secure the exhaust cone 102 and case 106 assembly to the exhaust housing. The connecting member 100 includes a plurality of first 112-1 and second 114-1 flexible fastening lugs distributed circumferentially about the longitudinal axis X.
The connection member comprises a radially extending annular flange 116 and comprises apertures to be fastened to the exhaust housing, in particular to corresponding flanges of the exhaust housing.
A first end of each first fastening lug 112-1 is connected to a radially outer end of the annular flange 116 via an outer annular portion 113. The first end of each second fastening lug 114-1 is connected to the radially inner end of an annular flange 116 via an inner annular portion 115.
The second end of each first fastening tab 112-1 is connected by screwing to the upstream end 103 of the exhaust cone 102, in particular to the upstream end 103 of the outer annular wall 104 of the exhaust cone 102, and the second end of each second fastening tab 114-1 is connected by screwing to the inner annular wall 108 of the tank 106.
The annular flange 116 is formed by a plurality of beams 117 distributed circumferentially around the longitudinal axis X and connecting the outer annular portion 113 with the inner annular portion 115. Alternatively, the annular flange may be solid and contain holes to be assembled to the shroud 106-1 of the exhaust housing by screwing.
The second end of each first fastening lug 112-1 is arranged radially inwards, i.e. in the direction of the longitudinal axis X with respect to the first end of said first fastening lug 112-1.
The first fastening tab ensures connection of the exhaust cone 102 to the exhaust housing and the second fastening tab ensures connection of the tank 106 to the exhaust housing. The first and second fastening lugs are flexible and decoupled. It therefore allows to absorb the part of the thermodynamic stress due to the material difference between the exhaust cone and the exhaust housing on the one hand and the tank and the exhaust housing on the other hand. The connecting lugs also allow to absorb part of the thermodynamic stresses to which the external annular wall and the tank are subjected due to their different thermal expansions.
Referring to fig. 8, the connection member 200 includes the same elements as the connection member 100. In contrast, the annular flange 116 is integrally formed. Each first fastening lug 112-1 is formed from a plate having a second end 202 that is connected to an upstream portion of the outer annular wall 104 downstream of the upstream end 103 of the outer annular wall 104. Each first fastening lug 112-1 further includes a first end 210 directly connected to the annular flange 116, and in particular to a radially outer end 214 of the annular flange 116. Each first fastening tab 112-1 includes a central portion 212 between the second end 202 and the first end 210. The second end 202 is arranged to protrude radially outwardly relative to the first end 210. In addition, the second end 202 is longitudinally aligned with the first end 210.
The radial thickness of the second end 202 is less than the radial thickness of the central portion 212 and the radial thickness of the first end 210. This difference in radial thickness makes the first fastening tab 112-1 flexible.
Each second fastening lug 114-1 includes a first end 208 connected to the annular flange 116 via an inner annular portion 115 extending from a radially inner end 216 of the annular flange 116. Each second fastening tab 114-1 includes a second end 204 that is connected to the inner annular wall 108 of the tank 106 by screwing. Each second fastening tab 114-1 includes a central portion 206 between the second end 204 and the first end 208.
The radial thickness of the central portion 206 is less than the radial thickness of the first end 208 and the radial thickness of the second end 204. This difference in radial thickness makes the second fastening tab 114-1 flexible.
The second end 204 of each second fastening tab 114-1 has a width in the circumferential direction that is less than the width in the circumferential direction of the first end 208 of the second fastening tab 114-1.
The outer annular wall 104 may extend upstream to ensure engagement with the exhaust housing rather than the shroud 106-1.
The number of first fastening tabs 112-1 may be less than the number of second fastening tabs 114-1. In this case, each first fastening lug 112-1 may be disposed circumferentially opposite one of the second fastening lugs 114-1.
Referring to fig. 9, the connection member 300 includes the same elements as the connection member 200 of fig. 8. In contrast, each first fastening lug 112-1 is detachable and is connected to the annular flange 116 by screwing, in particular in the central portion of the connecting flange 116. Alternatively, each second fastening lug 114-1 is detachable and connected to the annular flange 116 by screwing, in particular in the central portion of the connecting flange 116. In this case, each second fastening lug 114-1 has a uniform radial thickness at its first end 208, its second end 204 and its central portion 206.
Thus, the first fastening tab 112-1 in the case of fig. 9a or the second fastening tab 114-1 in the case of fig. 9b may be replaced more easily.
The upstream annular end 103 of the outer annular wall 104 of the exhaust cone 102 is arranged to engage with the annular portion 304 of the exhaust housing to form a flow surface for the primary flow from the turbine.
Referring to fig. 10, the connection member 400 1 Including the same elements as the connecting member 200 of fig. 8. In contrast, the first and second fastening lugs 112-1 and 114-1 are connected to the radially outer end 214 of the annular flange 116. The first end 210 of each first fastening lug 112-1 extends from the outer annular portion 113 of the annular flange. The first end 210 of each second fastening lug 114-1 also extends from the outer annular portion 113 of the annular flange.
Each of the first fastening tabs 112-1 is inserted with a second fastening tab 114-1. Each first fastening tab 112-1 is also circumferentially spaced apart from a second fastening tab 114-1 disposed on either side of the first fastening tab 112-1.
The connecting member 400 is shown in fig. 16d 1 Wherein each first fastening tab 112-1 overlaps a second fastening tab 114-1. The first end 210 of the first fastening lug 112-1 is screwed to the first end 208 of a second fastening lug which overlaps said first fastening lug 112-1 at the radially outer end 214 of the annular flange 116.
Referring to fig. 11, the connection member 400 2 Comprising a connecting member 400 as in fig. 10 1 Identical elements. In contrast, the first and second fastening lugs 112-1 and 114-1 are connected to the radially inner end 216 of the annular flange 116. The first end 210 of each first fastening lug 112-1 extends from the inner annular portion 115 of the annular flange 116. The first end 210 of each second fastening tab 114-1 also extends from the outer annular portion of the annular flange 116115 extends.
Each of the first fastening tabs 112-1 is inserted with a second fastening tab 114-1. Each first fastening tab 112-1 is also circumferentially spaced apart from a second fastening tab 114-1 disposed on either side of the first fastening tab 112-1.
In fig. 16a, a connecting member 400 is shown 2 Wherein each first fastening tab 112-1 overlaps a second fastening tab 114-1. The first end 210 of the first fastening lug 112-1 is screwed to the first end 208 of the second fastening lug 114-1, which overlaps said first fastening lug 112-1 at the radially inner end 216 of the annular flange 116.
Each first fastening tab 112-1 as represented in fig. 16b may be formed from a plate.
Each first fastening lug 112-1 as represented in fig. 16c may be formed of two fingers radially disjoint and connected at the first end 210 of the first fastening lug. The finger has a second end 202 connected to the outer annular wall 104 of the exhaust cone 102 2 Sum 202 1 。
Referring to fig. 12, the connection member 500 includes the same elements as the connection member 400. In contrast, each first fastening tab 112-1 extends in a first manner in the circumferential direction B about the longitudinal axis X. The second end 202 of each first fastening tab 112-1 is arranged to protrude radially relative to the first end 210 of said first fastening tab 112-1. In addition, the second end 202 of each first fastening tab 112-1 is circumferentially offset relative to the first end 210 of the first fastening tab 112-1.
In the variant represented in fig. 13, the connecting member 500 further comprises at least one first fastening lug 112-1 extending in a first manner in the circumferential direction B 1 And at least one first fastening lug 112-1 extending in a second manner opposite to the first manner of the circumferential direction B 2 . A pair of first fastening lugs 112-1 1 And 112-1 2 Are arranged end to end. First fastening tab 112-1 extending in a first manner 1 Is provided at the second end 210 of (2) 1 Adjacent to the first fastening lug 112-1 extending in the second manner 2 Is provided at the second end 210 of (2) 2 . In the first wayFirst fastening tab 112-1 extending in a manner 1 Is arranged at the first end 202 of (1) 1 And a first fastening tab 112-1 extending in a second manner 2 Is arranged at the first end 202 of (1) 2 On the contrary.
First fastening tab 112-1 extending in a first manner 1 Is provided at the second end 210 of (2) 1 And a first fastening tab 112-1 extending in a second manner 2 Is provided at the second end 210 of (2) 2 To the same first end 208 of the second fastening tab 114-1.
Referring to fig. 14, the connection member 600 includes the same elements as the connection member 500 of fig. 12. In contrast, each first fastening lug 112-1 extends simultaneously in the direction of the longitudinal axis X and in a first manner in the circumferential direction B. The second end 202 of each first fastening tab 112-1 is circumferentially offset and offset relative to the first end 210 of the first fastening tab 112-1 in the direction of the longitudinal axis X.
The variation of the connecting member 600 shown in fig. 15 includes the same elements as the connecting member 500 of fig. 13. In comparison and similar to the connecting member 600 of fig. 14, the first fastening lug 112-1 1 While extending in the direction of the longitudinal axis X and in a first manner in the circumferential direction B and with the first fastening lug 112-1 inserted 2 The first fastening tab 112-1 2 While extending in the direction of the longitudinal axis X and in a second manner in the circumferential direction B. Each first fastening tab 112-1 1 And 112-1 2 Is provided at the second end 202 of (2) 1 Sum 202 2 Circumferentially offset and in the direction of the longitudinal axis X relative to said first fastening lug 112-1 1 And 112-1 2 Is arranged at the first end 210 of (1) 1 And 210 2 Offset.
Referring to fig. 17, a connection member 700 includes a connection member 400 similar to that of fig. 16 2 Identical elements. In contrast, the first end 210 of each first fastening tab 112-1 is fastened to the second end 204 of the second fastening tab 114-1 by screwing.
The second end 204 of each second fastening tab 114-1 is connected to the inner annular wall 108.
The second end 202 of each first fastening tab 112-1 is connected to the outer annular wall 104.
The first end 208 of each second fastening lug 114-1 is connected to the annular flange 116 at its radially inner end 216.
In fig. 17a, the second end 202 of each first fastening lug 112-1 is arranged to protrude radially outwards and downstream of the first end 210 of said first fastening lug 112-1.
In fig. 17b, the second end 202 of each first fastening lug 112-1 is arranged to protrude radially outwards and upstream of the first end 210 of said first fastening lug 112-1.
In the variant represented in fig. 19b and 19c, the first end 210 of each first fastening lug 112-1 is fixed to the second end 204 of the second fastening lug 114-1, such that the first fastening lug 112-1 forms one integral piece with said second fastening lug 114-1.
Referring to fig. 18, the connection member 800 includes the same elements as the connection member 700 of fig. 17. In contrast, the first end 208 of each second fastening lug 114-1 is fastened to the second end 202 of the first fastening lug 112-1 by screwing.
The second end 210 of each second fastening tab 114-1 is connected to the inner annular wall 108.
The second end 202 of each first fastening tab 112-1 is connected to the outer annular wall 104.
The first end 210 of each first fastening lug 112-1 is connected to the annular flange 116 at its radially outer end 214.
In fig. 18a, the second end 204 of each second fastening lug 114-1 is arranged to protrude radially inwardly and downstream of the first end 208 of said second fastening lug 114-1.
In fig. 18b, the second end 204 of each second fastening lug 114-1 is arranged to protrude radially inwardly and upstream of the first end 208 of said second fastening lug 114-1.
In the variant represented in fig. 19a, the first end 208 of each second fastening lug 114-1 is fixed to the second end 202 of the first fastening lug 112-1, such that the first fastening lug 112-1 forms one integral piece with said second fastening lug 114-1.

Claims (15)

1. An assembly for a turbine of a turbomachine having a longitudinal axis, comprising:
an exhaust cone (102) comprising an outer annular wall (104) for the flow of a primary air flow and an annular tank (106) radially arranged inside said outer annular wall (104),
-an exhaust housing (111) arranged upstream of and connected to the exhaust cone (102), and
wherein one end of the outer annular wall (104) or one end of the annular box (106) is free to move relative to the exhaust cone (102) or relative to the exhaust housing.
2. The combination of claim 1, wherein the annular box (106) is connected to the exhaust cone (102) on the one hand and to the exhaust housing on the other hand, and wherein an upstream end of the outer annular wall (104) is free to move relative to the exhaust housing.
3. The combination of claim 1, wherein the outer annular wall (104) of the exhaust cone (102) is connected to the exhaust cone (102) on the one hand and to the exhaust housing on the other hand, and wherein an upstream end of the annular box (106) is free to move relative to the exhaust housing.
4. The assembly according to claim 1, wherein the outer annular wall (104) of the exhaust cone (102) is connected to the exhaust cone (102) on the one hand and to the exhaust housing on the other hand, and wherein a downstream end of the annular box (106) is free to move relative to the exhaust cone (102).
5. The combination of any of the preceding claims, wherein the annular tank (106) comprises an inner annular wall (108) arranged concentric with the outer annular wall (104), and the upstream end of the annular tank (106) corresponds to an upstream end of the inner annular wall (108) and the downstream end of the annular tank (106) corresponds to a downstream end of the inner annular wall (108).
6. The assembly of claim 5, wherein the annular box (106) comprises a plurality of partitions (110) extending radially from the inner annular wall (108) of the annular box (110) and extending axially along the inner annular wall (108).
7. Assembly according to any of the preceding claims, comprising a connecting member (114) fastened to the exhaust housing (111) and connected to the outer annular wall (104) of the exhaust cone (102) and/or to the annular box (106).
8. The combination of claims 5 and 7, wherein the connecting member comprises a first flexible fastening lug (112-1) circumferentially distributed about the longitudinal axis and a second flexible fastening lug (114-1) circumferentially distributed about the longitudinal axis, wherein the first fastening lug (112-1) is connected to an upstream annular portion of the outer annular wall (104) of the exhaust cone (102) and the second fastening lug (114-1) is connected to an upstream annular portion of the inner annular wall (109) of the tank (108).
9. The assembly of the preceding claim, wherein each first flexible fastening lug (112-1) is circumferentially spaced apart from one of the second flexible fastening lugs (114-1).
10. The combination of claim 8 or 9, wherein the connection member (100, 200, 300, 400, 500, 600, 700) comprises an annular flange (116) extending radially and connected to the exhaust housing (111), the first flexible fastening lug (112-1) and the second flexible fastening lug (114-1) being connected to the annular flange (116).
11. The combination of any one of claims 8 to 10, wherein at least one of the first flexible fastening lugs (112-1) extends radially outwardly and about a longitudinal axis (X) in a first manner in a circumferential direction (B).
12. Assembly according to the preceding claim, wherein at least one of the first flexible fastening lugs (112-1) extends radially outwards and around the longitudinal axis (X) in a second manner opposite to the first manner of the circumferential direction (B).
13. The assembly of any of the preceding claims, wherein the exhaust cone (102) is made of a ceramic matrix composite.
14. Assembly according to any of the preceding claims, wherein the sound box (106) is made of a ceramic matrix composite.
15. A turbine comprising an assembly according to any one of the preceding claims.
CN202180085307.4A 2020-11-05 2021-11-04 Fastening an exhaust cone in a turbine Pending CN116685765A (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
FRFR2011377 2020-11-05
FRFR2011376 2020-11-05
FR2011377A FR3115833B1 (en) 2020-11-05 2020-11-05 Fixing an exhaust cone in a turbomachine turbine
PCT/FR2021/051948 WO2022096832A1 (en) 2020-11-05 2021-11-04 Fastening of an exhaust cone in a turbine of a turbomachine

Publications (1)

Publication Number Publication Date
CN116685765A true CN116685765A (en) 2023-09-01

Family

ID=75339806

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202180085307.4A Pending CN116685765A (en) 2020-11-05 2021-11-04 Fastening an exhaust cone in a turbine

Country Status (2)

Country Link
CN (1) CN116685765A (en)
FR (1) FR3115833B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3137722A1 (en) * 2022-07-11 2024-01-12 Safran Ceramics Turbomachine turbine assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2875854B1 (en) * 2004-09-29 2009-04-24 Snecma Propulsion Solide Sa MIXER FOR TUYERE WITH SEPARATE FLUX
FR2916018B1 (en) * 2007-05-10 2009-08-21 Snecma Propulsion Solide Sa EXHAUST SYSTEM FOR GAS TURBINE
BR112014026533A2 (en) * 2012-04-27 2017-06-27 Gen Electric Gas turbine engine assembly.
FR3084916B1 (en) * 2018-08-10 2020-07-17 Safran Ceramics FLEXIBLE FIXING EJECTION CONE

Also Published As

Publication number Publication date
FR3115833B1 (en) 2022-12-02
FR3115833A1 (en) 2022-05-06

Similar Documents

Publication Publication Date Title
CN112543843B (en) Exhaust cone with flexible fitting
US6969233B2 (en) Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity
US10060631B2 (en) Hybrid diffuser case for a gas turbine engine combustor
US11112117B2 (en) Fuel nozzle cooling structure
US11821387B2 (en) Ejection cone having a flexible aerodynamic attachment
US10429070B2 (en) Combustor assembly
US20170130653A1 (en) Igniter for a gas turbine engine
EP3211310B1 (en) Combustor assembly
US10378771B2 (en) Combustor assembly
CN116685765A (en) Fastening an exhaust cone in a turbine
CN116648556A (en) Turbine assembly for a turbomachine
US10502424B2 (en) Volute combustor for gas turbine engine
US11959437B2 (en) Fastening of an exhaust cone in a turbomachine nozzle
US10228136B2 (en) Combustor assembly
US11313560B2 (en) Combustor assembly for a heat engine
US12116954B2 (en) Fastening of an exhaust cone in a turbomachine nozzle
US10612780B2 (en) Combustion chamber arrangement
US10823416B2 (en) Purge cooling structure for combustor assembly
US20230407814A1 (en) Fastening of an exhaust cone in a turbomachine turbine
CN111836998B (en) Double-chamber bottom of combustion chamber
US12065985B2 (en) Sealing assembly for a turbine ejection cone
US20230114116A1 (en) Combustor swirler to cmc dome attachment
US20240053009A1 (en) Dome-deflector for a combustor of a gas turbine
CN118805023A (en) Assembly for an exhaust cone in a turbine nozzle
CN118829784A (en) Injection cone for an aircraft turbine engine

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination