CN113062777A - Performance debugging method of booster stage and turbofan engine - Google Patents
Performance debugging method of booster stage and turbofan engine Download PDFInfo
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- CN113062777A CN113062777A CN202110616611.9A CN202110616611A CN113062777A CN 113062777 A CN113062777 A CN 113062777A CN 202110616611 A CN202110616611 A CN 202110616611A CN 113062777 A CN113062777 A CN 113062777A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a performance debugging method of a booster stage and a turbofan engine, wherein the booster stage comprises a drum barrel and a rotor blade arranged on the drum barrel, and the performance debugging method of the booster stage comprises the following steps: s1, determining the installation angle of the rotor blade relative to the drum; s2, disassembling the old rotor blade; and S3, selecting a new rotor blade corresponding to the installation angle, and installing the new rotor blade in the drum. The performance debugging method of the booster stage is used for debugging the booster stage of the low-pressure section of the turbofan engine, and only the installation angle of the rotor blade and the drum barrel needs to be determined, and the corresponding rotor blade is installed on the drum barrel, so that the regulation of the booster stage is completed.
Description
Technical Field
The invention relates to a performance debugging method of a supercharging stage and a turbofan engine.
Background
The supercharging stage is one of the important components of the turbofan engine, is located between the fan and the high-pressure compressor, and is used for supercharging gas entering the content behind the fan. After the gas passes through the pressurizing stage, the gas enters the transition section and the high-pressure compressor. The supercharging stage has important significance for the serialization development of the turbofan engine, the physical flow of the connotation can be adjusted by the supercharging stage, the supercharging stage or the redesign of the supercharging stage, and the thrust of the engine is increased or reduced by matching with the flow and pressure ratio adjustment of the fan connotation.
For the turbofan engine, the bypass ratio is increased when the bypass flow is reduced, so that the oil consumption rate can be reduced, but the temperature in front of the turbine is increased; conversely, increasing the bypass flow, i.e. decreasing the bypass ratio, reduces the pre-turbine temperature, but increases the fuel consumption. Therefore, during the performance debugging process of the turbofan engine, the content flow is often required to be adjusted within a certain range so as to realize the compromise balance of the turbine front temperature and the oil consumption rate. In the serialization development and the performance debugging of the turbofan engine, the pressure ratio and the flow of a supercharging stage need to be adjusted for multiple times so as to adapt to the performance debugging requirements of the engine, such as the debugging of thrust, oil consumption and the temperature before a turbine.
Typical booster stages are typically 3-4 stages for a total of 6-8 rows of blades. One way to adjust the performance of a boost stage is to redesign and trial-manufacture the boost stage based on the overall design requirements, such as redesign of the stator blades, rotor blades, and drums, which may also require redesign of other structural components such as fans, which is a long design cycle and costly process. Moreover, all blade rows need to be replaced, the assembly is complex, and the efficiency is low. In another mode, an adjustable stator blade is adopted to adjust the flow and the pressure ratio of a booster stage, but the adjustable stator blade is complex in structure, and an adjustable mechanism and the weight thereof need to be additionally introduced, so that the structure is complex and the performance debugging is not facilitated.
Disclosure of Invention
The invention aims to overcome the defects that a performance debugging method of a booster stage in the prior art is long in debugging period and uneconomical, and provides the performance debugging method of the booster stage and a turbofan engine.
The invention solves the technical problems through the following technical scheme:
a method of commissioning the performance of a boost stage comprising a drum and a rotor blade mounted to the drum, the method of commissioning the performance of the boost stage comprising the steps of:
s1, determining the installation angle of the rotor blade relative to the drum;
s2, disassembling the old rotor blade;
and S3, selecting a new rotor blade corresponding to the installation angle, and installing the new rotor blade in the drum barrel.
In the scheme, the performance debugging method of the booster stage is used for debugging the booster stage of the low-pressure section of the turbofan engine, and only the installation angle of the rotor blade and the drum barrel needs to be determined, and the corresponding rotor blade is installed on the drum barrel, so that the regulation of the booster stage is completed.
Preferably, the installation position of the new rotor blade is a first position, the installation position of the old rotor blade is a second position, the new rotor blade rotates from the first position to the second position by a preset angle by taking a center-of-gravity connecting line of the blade tip element level and the blade root element level as a rotating axis, and the preset angle is a difference value between the installation angle of the new rotor blade and the installation angle of the old rotor blade.
In the scheme, the blade profile of the new rotor blade is the same as that of the old rotor blade by adopting the structural form. The new rotor blade takes the gravity center connecting line of the blade tip element level and the blade root element level as a rotating shaft, and the new rotor blade can be rotated from the first position to the second position by a preset angle only by rotating around the rotating shaft. In other embodiments, the old rotor blade may be rotated about other axes of rotation to obtain the setting angle of the new rotor blade. The new rotor blade is rotated by only a predetermined angle, i.e. the difference in the setting angle, compared to the old rotor blade.
Preferably, the adjustment range of the installation angle is 2-4 degrees.
In this solution, the above-mentioned adjustment range is used for the adjustment of the rotor blade within a small angle range.
Preferably, the rotor blade comprises a blade body, a platform and a tenon for detachable connection to the drum.
In this scheme, adopt above-mentioned structural style, be convenient for change rotor blade.
Preferably, the blade body of the new rotor blade and the blade body of the old rotor blade are the same in shape;
the included angle between the tenon of the new rotor blade and the blade body is a first angle, the included angle between the tenon of the old rotor blade and the blade body is a second angle, and the difference value between the first angle and the second angle is equal to the difference value between the installation angle of the new rotor blade and the installation angle of the old rotor blade.
In the scheme, the blade body of the new rotor blade is the same as the blade body of the old rotor blade in shape, the blade body of the new rotor blade can be machined by adopting a die or a machining program of the old rotor blade, and then the tenon of the new rotor blade is machined according to the rotating angle of the installation angle, so that the machining cost is effectively reduced.
Preferably, the booster stage further comprises a stator blade mounted on the outer circumferential surface of the drum, and the mounting angle of the stator blade is not adjustable.
In the scheme, the stator blades do not rotate, and the stator blades are used for reducing kinetic energy and increasing pressure potential energy. When the rotor blade is debugged, the stator blade is not required to be disassembled and assembled, and only the rotor blade is adjusted, so that the debugging efficiency is improved. In other schemes, the adjustable installation angle of the stator blade can be adjusted by additionally arranging the adjustable mechanism.
Preferably, the supercharging stages are 3 stages or 4 stages, each stage including a row of stator blades and a row of rotor blades, and the stator blades and the rotor blades are arranged at intervals in the axial direction of the drum.
In this scheme, adopt above-mentioned structural style, the turbofan engine of being convenient for pressurizes step by step.
Preferably, the stagger angles of the rotor blades of the same stage are the same.
In this scheme, adopt above-mentioned structural style, the rotor blade of being convenient for leads wind to same direction.
Preferably, the stagger angles of the rotor blades of different stages are the same.
In this scheme, adopt above-mentioned structural style, the turbofan engine of being convenient for pressurizes step by step. When the installation angles of the rotor blades of different stages are the same, the airflow angle of the stator blade can be basically unchanged, the corresponding stator blade can be kept unchanged, and the adjustment range of the pressure increasing stage blade is greatly reduced. In other alternatives, the setting angles of the rotor blades of different stages may also differ. When the setting angles of the rotor blades of different stages are different, the performance of the turbofan engine can be adjusted in a wider range.
A turbofan engine comprising a boost stage commissioned using a performance commissioning method for a boost stage as described above.
In the scheme, the performance of the turbofan engine can be debugged by the aid of the supercharging stage so as to meet debugging requirements of the performance of the engine, such as thrust, oil consumption and turbine front temperature.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows: the performance debugging method of the booster stage is used for debugging the booster stage of the low-pressure section of the turbofan engine, and only the installation angle of the rotor blade and the drum barrel needs to be determined, and the corresponding rotor blade is installed on the drum barrel, so that the regulation of the booster stage is completed.
Drawings
Fig. 1 is a flowchart of a performance tuning method of a booster stage according to a preferred embodiment of the present invention.
FIG. 2 is a schematic view of the location of the supercharging stage in the turbofan engine according to the preferred embodiment of the present invention.
Figure 3 is a schematic view of the location of the rotating shaft in the booster stage according to the preferred embodiment of the invention.
FIG. 4 is a schematic view of a rotor blade according to a preferred embodiment of the present invention.
FIG. 5 is a schematic view of a variation of the setting angle of a rotor blade according to a preferred embodiment of the present invention.
Description of reference numerals:
Drum 1
Tenon 23
Setting angle adjustment range 40
Steps S1-S3.
Detailed Description
The present invention will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, but the present invention is not limited thereto.
As shown in fig. 1, the booster stage 10 is one of the important components of a turbofan engine, located between the fan 30 and the high pressure compressor, for boosting the air that enters the contents behind the fan 30. After passing through the fan 30, the air flow is divided into two ducts, the outer duct is discharged through the outlet guide vanes 20, and the inner duct enters the transition section and the high-pressure compressor through the booster stage 10. The pressure increasing stage 10 has an important significance for the serialization development of the turbofan engine, the physical flow of the culvert can be adjusted by increasing the stage, reducing the stage or redesigning the pressure increasing stage 10, and the thrust of the engine is increased or reduced by matching with the adjustment of the flow and the pressure ratio of the culvert of the fan 30.
As shown in fig. 2-5, the present embodiment discloses a method for tuning the performance of a boost stage, wherein the boost stage 10 comprises a drum 1 and a rotor blade 2 mounted on the drum 1, and the method for tuning the performance of the boost stage 10 comprises the following steps:
s1, determining the installation angle of the rotor blade 2 relative to the drum 1;
s2, disassembling the old rotor blade 2;
s3, selecting a new rotor blade 2 corresponding to the installation angle, and installing the new rotor blade 2 in the drum 1.
The performance debugging method of the booster stage is used for debugging the booster stage 10 of the low-pressure section of the turbofan engine, only the installation angle of the rotor blade 2 and the drum barrel 1 needs to be determined, and the corresponding rotor blade 2 is installed on the drum barrel 1, so that the regulation of the booster stage 10 is completed.
The installation angle is an included angle between a connecting line of a front edge and a tail edge of the element level of the rotor blade 2 and the axial direction, and is used for representing the opening and closing degree of the rotor blade 2.
The rotor blade 2 comprises a body 21, a platform 22 and a tenon 23, the tenon 23 being adapted for detachable connection to the drum 1 for facilitating replacement of the rotor blade 2.
The blade body 21 of the new rotor blade 2 and the blade body 21 of the old rotor blade 2 are identical in shape, the included angle between the tenon 23 of the new rotor blade 2 and the blade body 21 is a first angle, the included angle between the tenon 23 of the old rotor blade 2 and the blade body 21 is a second angle, and the difference between the first angle and the second angle is equal to the difference between the installation angle of the new rotor blade 2 and the installation angle of the old rotor blade 2.
In the embodiment, the blade body 21 of the new rotor blade 2 and the blade body 21 of the old rotor blade 2 have the same shape, the blade body 21 of the new rotor blade 2 can be machined by adopting a mold or a machining program of the old rotor blade, and then the rabbet 23 of the new rotor blade 2 is machined according to the rotating angle of the installation angle, so that the machining cost is effectively reduced.
The installation position of the new rotor blade 2 is a first position, the installation position of the old rotor blade 2 is a second position, the new rotor blade 2 rotates from the first position to the second position by a preset angle by taking a gravity center connecting line of a blade tip element level and a blade root element level as a rotating shaft 24, and the preset angle is a difference value between the installation angle of the new rotor blade 2 and the installation angle of the old rotor blade 2. Since the new rotor blade 2 has the same profile as the old rotor blade 2, the new rotor blade 2 can be brought into register with the old rotor blade 2 by only rotating the new rotor blade 2 by a predetermined angle about the axis of rotation 24. In other embodiments, the old rotor blade 2 may also be used to rotate about other rotational axes 24 to obtain the setting angle of the new rotor blade 2.
The booster stage 10 further comprises stator blades mounted on the outer circumferential surface of the drum 1, the mounting angles of the stator blades being non-adjustable. The stator blades do not rotate, and the stator blades are used for reducing kinetic energy and increasing pressure potential energy. When debugging the rotor blade, need not to carry out the dismouting to stator blade, only adjust rotor blade 2, improve debugging efficiency. In other embodiments, the adjustable installation angle of the stator blade can be adjusted by additionally arranging an adjustable mechanism.
In the present embodiment, the pressurizing stages 10 are 3 stages, each stage includes a row of stator blades and a row of rotor blades 2, and the stator blades and the rotor blades 2 are arranged at intervals in the axial direction of the drum 1, so as to facilitate the gradual pressurization of the turbofan engine. In other embodiments, the boost level may be 4 levels.
Wherein, the rotor blade 2's of the same stage erection angle is the same, is convenient for rotor blade 2 with wind direction to same direction.
The setting angles of the rotor blades 2 of different stages may be identical. When the installation angles of the rotor blades 2 of different stages are the same, the airflow angle of the stator blade can be basically unchanged, the corresponding stator blade can be kept unchanged, and the adjustment range of the blades of the booster stage 10 is greatly reduced.
The setting angles of the rotor blades 2 of different stages may differ. When the installation angles of the rotor blades 2 of different stages are different, the performance of the turbofan engine can be debugged in a wider range, and the debugging flexibility is improved.
In the present embodiment, the adjustment range 40 of the installation angle is 2 ° -4 °, and the adjustment range is used for the adjustment of the rotor blade 2 within a small angle range.
The present embodiment also discloses a turbofan engine that includes a boost stage 10 that is tuned using the performance tuning method for a boost stage as described above. The turbofan engine can utilize the supercharging stage 10 to debug the performance of the turbofan engine so as to adapt to the debugging requirements of the engine performance, such as the debugging of thrust, oil consumption and temperature before turbine.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (10)
1. A method of commissioning a performance of a boost stage comprising a drum and a rotor blade mounted to the drum, characterized in that the method of commissioning a performance of the boost stage comprises the steps of:
s1, determining the installation angle of the rotor blade relative to the drum;
s2, disassembling the old rotor blade;
and S3, selecting a new rotor blade corresponding to the installation angle, and installing the new rotor blade in the drum barrel.
2. The method of tuning the performance of a boost stage according to claim 1, wherein the new rotor blade is mounted at a first position and the old rotor blade is mounted at a second position, and the new rotor blade is rotated from the first position to the second position by a predetermined angle using a line connecting the centers of gravity of the blade tip element stage and the blade root element stage as a rotation axis, the predetermined angle being a difference between a mounting angle of the new rotor blade and a mounting angle of the old rotor blade.
3. The method of tuning the performance of a boost stage of claim 1, wherein the setting angle is adjusted in the range of 2 ° to 4 °.
4. The method of debugging the performance of a boost stage of claim 1, wherein a rotor blade comprises a body, a platform, and a rabbet for removably coupling with the drum.
5. The method of debugging the performance of a pressure boost stage according to claim 4, wherein the blade body of the new rotor blade and the blade body of the old rotor blade are the same in shape;
the included angle between the tenon of the new rotor blade and the blade body is a first angle, the included angle between the tenon of the old rotor blade and the blade body is a second angle, and the difference value between the first angle and the second angle is equal to the difference value between the installation angle of the new rotor blade and the installation angle of the old rotor blade.
6. The method of debugging the performance of a booster stage according to claim 1, characterized in that the booster stage further comprises a stator blade mounted on the outer circumferential surface of the drum, and the mounting angle of the stator blade is not adjustable.
7. The method of debugging the performance of a boost stage according to claim 6, wherein the boost stage is 3 stages or 4 stages, each stage including a row of stator blades and a row of rotor blades, the stator blades and the rotor blades being provided at intervals in the axial direction of the drum.
8. A method of commissioning a pressure stage according to claim 7 wherein the stagger angles of the rotor blades of the same stage are the same.
9. A method of commissioning a pressure stage as recited in claim 7 wherein the stagger angles of the rotor blades of different stages are the same.
10. Turbofan engine, characterized in that it comprises a pressure boosting stage that is commissioned using a method of performance commissioning of a pressure boosting stage according to any one of claims 1-9.
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| CN202110616611.9A CN113062777B (en) | 2021-06-03 | 2021-06-03 | Performance debugging method of booster stage and turbofan engine |
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| CN202110616611.9A CN113062777B (en) | 2021-06-03 | 2021-06-03 | Performance debugging method of booster stage and turbofan engine |
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| US5338155A (en) * | 1992-08-03 | 1994-08-16 | Asea Brown Boveri Ltd. | Multi-zone diffuser for turbomachine |
| CN102235267A (en) * | 2010-05-05 | 2011-11-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Gas turbine engine modified by using exservice turbofan engine through low-pressure crest truncation |
| US20180073375A1 (en) * | 2015-10-27 | 2018-03-15 | Mitsubishi Heavy Industries, Ltd. | Rotary machine |
| CN108691806A (en) * | 2018-05-09 | 2018-10-23 | 中国航空发动机研究院 | Using the engine structure changes fan of guide rail wheel disc and set tooth pipe |
| CN109595041A (en) * | 2017-09-30 | 2019-04-09 | 中国航发商用航空发动机有限责任公司 | Become and recycles big Bypass Ratio Turbofan Engine |
| CN111173570A (en) * | 2019-12-30 | 2020-05-19 | 中国南方航空股份有限公司 | Method for replacing turbine blade |
| CN210769380U (en) * | 2019-10-31 | 2020-06-16 | 中国航发商用航空发动机有限责任公司 | Turbofan engine and low-pressure compressor |
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2021
- 2021-06-03 CN CN202110616611.9A patent/CN113062777B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5338155A (en) * | 1992-08-03 | 1994-08-16 | Asea Brown Boveri Ltd. | Multi-zone diffuser for turbomachine |
| CN102235267A (en) * | 2010-05-05 | 2011-11-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Gas turbine engine modified by using exservice turbofan engine through low-pressure crest truncation |
| US20180073375A1 (en) * | 2015-10-27 | 2018-03-15 | Mitsubishi Heavy Industries, Ltd. | Rotary machine |
| CN107923409A (en) * | 2015-10-27 | 2018-04-17 | 三菱重工业株式会社 | Rotating machinery |
| CN109595041A (en) * | 2017-09-30 | 2019-04-09 | 中国航发商用航空发动机有限责任公司 | Become and recycles big Bypass Ratio Turbofan Engine |
| CN108691806A (en) * | 2018-05-09 | 2018-10-23 | 中国航空发动机研究院 | Using the engine structure changes fan of guide rail wheel disc and set tooth pipe |
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| CN111173570A (en) * | 2019-12-30 | 2020-05-19 | 中国南方航空股份有限公司 | Method for replacing turbine blade |
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