CN112780400B - Special booster for high-altitude power recovery of aviation piston engine - Google Patents

Special booster for high-altitude power recovery of aviation piston engine Download PDF

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Publication number
CN112780400B
CN112780400B CN202110239309.6A CN202110239309A CN112780400B CN 112780400 B CN112780400 B CN 112780400B CN 202110239309 A CN202110239309 A CN 202110239309A CN 112780400 B CN112780400 B CN 112780400B
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China
Prior art keywords
compressor
lubricating oil
turbine
volute
rotating shaft
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CN112780400A (en
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赵振峰
俞春存
王蕾
冯熠硕
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Beijing Institute of Technology BIT
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Beijing Institute of Technology BIT
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F04D29/0566—Ceramic bearing designs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/06—Lubrication
    • F04D29/063—Lubrication specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • 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
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Supercharger (AREA)

Abstract

The invention discloses a special booster for recovering high altitude power of an aviation piston engine, which comprises: a turbine and a compressor; the turbine comprises a volute, and one end of the volute is connected with the gas compressor; the turbine blade is connected with a rotating shaft at one side, and a waste gas inlet is formed in the position, close to the turbine blade, of the volute; the compressor comprises a compressor housing, one end of the compressor housing is connected with the volute, the compressor further comprises an impeller, and the rotating shaft penetrates through the impeller; one end of the rotating shaft is provided with a bearing, the compressor shell is provided with a lubricating oil cavity, the lubricating oil cavity is provided with a lubricating oil pipe, one end of the lubricating oil pipe is positioned in the lubricating oil cavity, and the other end of the lubricating oil pipe is close to the bearing; the compressor housing is provided with a compressor outlet. The lubricating oil in the lubricating oil cavity is sucked to the bearing for lubrication through the lubricating oil pipe according to the siphon principle, the supercharger does not need to be externally connected with a lubricating pipeline, a lubricating system is simplified, the complexity of arrangement of the supercharger is reduced, the structure is more compact, and the weight of the supercharger is reduced.

Description

Special booster for high-altitude power recovery of aviation piston engine
Technical Field
The invention relates to the field of superchargers, in particular to a special supercharger for high-altitude power recovery of an aviation piston engine.
Background
The booster that aviation piston engine high altitude power resumes adopts exhaust gas turbine booster theory of operation, is a supercharging device that admits air for increase the engine air input along with unmanned aerial vehicle altitude increase, keep the output of engine, realize along with the recovery of height above sea level rising engine power. The working principle of the engine exhaust gas turbine engine is that the turbine is driven to rotate by the engine exhaust gas, and then the compressor is driven to rotate, so that the air inlet pressurization is realized, and the engine power recovery is realized. A supercharger in the prior art needs a special high-pressure lubricating system, is complex in mechanism and heavy in weight, and can cause oil leakage along with elevation, so that the reliability of the system is seriously influenced.
Therefore, the problem to be solved is to provide the compact-structure supercharger special for high altitude power recovery of the aviation piston engine.
Disclosure of Invention
In view of this, the present invention provides a special booster for recovering high altitude power of an aviation piston engine, including: a turbine and a compressor;
the turbine comprises a volute, the volute is a sleeve body with openings at two ends, one end of the volute is connected with the compressor, and one end of the volute, close to the compressor, is connected with a turbine end sealing plate;
the turbine also comprises a turbine blade arranged in the volute, the central axis of the turbine blade is perpendicular to the turbine end sealing plate, one side of the turbine blade, which is close to the turbine end sealing plate, is fixedly connected with a rotating shaft, and the rotating shaft penetrates through the turbine end sealing plate;
the volute is provided with a waste gas inlet close to the turbine blade;
the compressor comprises a compressor shell, the compressor shell is a sleeve body with openings at two ends, one end of the compressor shell is connected with the volute, one end of the compressor shell, which is close to the volute, is connected with a compressor end sealing plate, and the rotating shaft penetrates through the compressor end sealing plate;
the compressor also comprises an impeller, the rotating shaft penetrates through the impeller, and the central axes of the turbine blades, the rotating shaft and the impeller are superposed;
a bearing is arranged between one end, far away from the turbine, of the rotating shaft and the impeller, a lubricating oil cavity is formed in the compressor shell, a lubricating oil pipe is arranged in the lubricating oil cavity, one end of the lubricating oil pipe is located in the lubricating oil cavity, the other end of the lubricating oil pipe is close to the bearing, and the lubricating oil pipe is used for sucking lubricating oil in the lubricating oil cavity to the bearing for lubrication according to a siphon principle;
and a compressor outlet is formed in the compressor housing close to the impeller.
Preferably, the turbine further comprises an exhaust gas bypass mechanism,
the waste gas bypass mechanism comprises a bypass valve arranged on the volute, the bypass valve comprises a valve plate, a valve shaft and a shaft sleeve, the valve shaft penetrates through the shaft sleeve, and one end of the valve shaft is connected with the valve plate;
the waste gas bypass mechanism further comprises a motor, a pull wire, a control arm and a spring, wherein one end of the pull wire is connected with the motor, and the other end of the pull wire is connected with the control arm; one end of the control arm is connected with the pull wire, the other end of the control arm is connected with the spring, the middle of the control arm is connected with one end, far away from the valve plate, of the valve shaft, one end of the spring is connected with the control arm, and the other end of the spring is connected with the volute.
Preferably, a heat insulation plate is arranged on one side, close to the compressor end sealing plate, of the turbine end sealing plate, and a shaft seal for sealing is arranged at the position, close to the rotating shaft, of the turbine end sealing plate.
Preferably, an inner ring of the bearing is integrated with the rotating shaft, and an outer ring of the bearing is engaged with the compressor housing.
Preferably, the number of the bearings is at least one, and the lubricating oil pipes correspond to the bearings one to one.
Preferably, the lubricant chamber is integral with the compressor housing.
Preferably, the impeller and the rotating shaft are connected by bolt fixing.
Preferably, the bearing is a ceramic rolling bearing.
Compared with the prior art, the special booster for recovering the high altitude power of the aviation piston engine provided by the invention at least realizes the following beneficial effects:
1. the lubricating oil cavity of the special supercharger for high-altitude power recovery of the aviation piston engine is arranged in the air compressor, the lubricating oil pipe is used for sucking the lubricating oil in the lubricating oil cavity to the bearing for lubrication according to the siphon principle, the supercharger does not need to be externally connected with a lubricating pipeline, a lubricating system is simplified, the complexity of the arrangement of the supercharger is reduced, the structure is more compact, and the weight of the supercharger is reduced.
2. The special supercharger for high altitude power recovery of the aviation piston engine, provided by the invention, has the advantages that the bearing, the lubricating oil cavity and the lubricating oil pipe are positioned in the compressor and far away from the high-temperature turbine, and meanwhile, the heat dissipation is carried out by utilizing the high-speed flowing air inlet flow in the compressor, so that the working temperature is lower, and the reliability of the supercharger is improved.
3. One end of a rotating shaft in the supercharger special for high-altitude power recovery of the aviation piston engine is fixedly connected with a turbine blade, and the other end of the rotating shaft is provided with a bearing for supporting, so that the normal working position and the rotating precision of the rotating shaft are kept.
Of course, it is not necessary for any product in which the present invention is practiced to achieve all of the above-described technical effects simultaneously.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a schematic structural diagram of a supercharger dedicated for high altitude power recovery of an aviation piston engine provided by the invention;
FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;
FIG. 3 is an enlarged view of a portion of region B in FIG. 2;
FIG. 4 is a left side view of FIG. 1;
FIG. 5 is a bottom view of FIG. 1;
the device comprises a turbine 1, a compressor 2, a volute 3, turbine blades 4, a turbine end sealing plate 5, a rotating shaft 6, an exhaust gas inlet 7, a compressor shell 8, a compressor end sealing plate 9, an impeller 10, a bearing 11, a lubricating oil cavity 12, a lubricating oil pipe 13, a compressor outlet 14, an exhaust gas bypass mechanism 15, a bypass valve 16, a valve plate 17, a valve shaft 18, a shaft sleeve 19, a motor 20, a stay wire 21, a control arm 22, a spring 23, a heat insulation plate 24 and a shaft seal 25.
Detailed Description
Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that: the relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise.
The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses.
Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate.
In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
Example 1
The following describes a specific embodiment of the special booster for recovering high altitude power of an aviation piston engine provided by the invention with reference to fig. 1, fig. 2, fig. 3 and fig. 4, and comprises: a turbine 1 and a compressor 2;
the turbine 1 comprises a volute 3, the volute 3 is a sleeve body with openings at two ends, one end of the volute 3 is connected with the compressor 2, and one end of the volute 3, close to the compressor 2, is connected with a turbine end sealing plate 5;
the turbine 1 further comprises a turbine blade 4 arranged in the volute 3, the central axis of the turbine blade 4 is perpendicular to the turbine end sealing plate 5, one side, close to the turbine end sealing plate 5, of the turbine blade 4 is fixedly connected with a rotating shaft 6, and the rotating shaft 6 penetrates through the turbine end sealing plate 5;
a waste gas inlet 7 is arranged at the position of the volute 3 close to the turbine blade 4;
the compressor 2 comprises a compressor shell 8, the compressor shell 8 is a sleeve body with openings at two ends, one end of the compressor shell 8 is connected with the volute 3, one end of the compressor shell 8, which is close to the volute 3, is connected with a compressor end sealing plate 9, and the rotating shaft 6 penetrates through the compressor end sealing plate 9;
the compressor 2 also comprises an impeller 10, the rotating shaft 6 penetrates through the impeller 10, and the central axes of the turbine blades 4, the rotating shaft 6 and the impeller 10 are superposed;
a bearing 11 is arranged between one end, far away from the turbine 1, of the rotating shaft 6 and the impeller 10, a lubricating oil cavity 12 is arranged on the compressor shell 8, a lubricating oil pipe 13 is arranged in the lubricating oil cavity 12, one end of the lubricating oil pipe 13 is located in the lubricating oil cavity 12, the other end of the lubricating oil pipe is close to the bearing 11, and the lubricating oil pipe 13 is used for sucking lubricating oil in the lubricating oil cavity 12 to the bearing 11 for lubrication according to a siphon principle; the supercharger does not need to be externally connected with a lubricating pipeline, a lubricating system is simplified, the complexity of arrangement of the supercharger is reduced, the structure is more compact, and the weight of the supercharger is reduced. The lubricating mode utilizes the siphon principle to perform micro-lubrication, has small lubricating oil consumption, can be used for at least half a year after once oiling the lubricating oil cavity 12, and also has the advantage of realizing maintenance-free. One end of the rotating shaft 6 is fixedly connected with the turbine blade 4, and the other end of the rotating shaft is provided with a bearing 11 for supporting, so that the normal working position and the rotating precision of the rotating shaft 6 are kept.
The bearing 11, the lubricating oil cavity 12 and the lubricating oil pipe 13 are located in the compressor 2 and far away from the high-temperature turbine 1, and meanwhile, heat dissipation is carried out by utilizing high-speed flowing air inlet flow in the compressor 2, so that the working temperature is low, and the reliability of the supercharger is improved.
The compressor housing 8 is provided with a compressor outlet 14 adjacent the impeller 10.
Engine exhaust gas is introduced into the turbine 1 from the exhaust gas inlet 7, pressure energy and heat energy of the exhaust gas are converted into mechanical energy for rotating the turbine blades 4, the turbine blades 4 are coaxial with the impeller 10, the impeller 10 is driven to rotate, and intake pressurization is achieved. When the impeller 10 rotates at a high speed, the lubricating oil in the lubricating oil chamber 12 is sucked to the bearing 11 for lubrication through the lubricating oil pipe 13 by using the siphon principle. Because the bearing 11, the lubricating oil cavity 12 and the lubricating oil pipe 13 of the supercharger special for high altitude power recovery of the aviation piston engine are far away from the turbine 1 with high temperature, the consumption of the lubricating oil is low, and the supercharger can work for a long time only by injecting a certain amount of lubricating oil into the lubricating oil cavity 12.
Another specific embodiment of the aero piston engine high altitude power recovery dedicated supercharger provided by the present invention is described below with reference to fig. 1, fig. 2, fig. 3, fig. 4 and fig. 5.
Example 2
The invention provides another specific embodiment of the special booster for recovering the high altitude power of the aviation piston engine, which comprises the following steps: a turbine 1 and a compressor 2;
the turbine 1 comprises a volute 3, the volute 3 is a sleeve body with openings at two ends, one end of the volute 3 is connected with the compressor 2, and one end of the volute 3, close to the compressor 2, is connected with a turbine end sealing plate 5;
the turbine 1 further comprises a turbine blade 4 arranged in the volute 3, the central axis of the turbine blade 4 is perpendicular to the turbine end sealing plate 5, one side, close to the turbine end sealing plate 5, of the turbine blade 4 is fixedly connected with a rotating shaft 6, and the rotating shaft 6 penetrates through the turbine end sealing plate 5; the turbine blade 4 and the rotating shaft 6 are integrated, so that the stability is higher.
A waste gas inlet 7 is arranged at the position of the volute 3 close to the turbine blade 4;
the turbine 1 further comprises an exhaust gas bypass mechanism 15,
the waste gas bypass mechanism 15 comprises a bypass valve 16 arranged on the volute 3, the bypass valve 16 comprises a valve plate 17, a valve shaft 18 and a shaft sleeve 19, the valve shaft 18 penetrates through the shaft sleeve 19, and one end of the valve shaft 18 is connected with the valve plate 17;
the waste gas bypass mechanism 15 further comprises a motor 20, a pull wire 21, a control arm 22 and a spring 23, wherein one end of the pull wire 21 is connected with the motor 20, and the other end of the pull wire 21 is connected with the control arm 22; one end of the control arm 22 is connected with the pull wire 21, the other end is connected with the spring 23, the middle part of the control arm 22 is connected with one end of the valve shaft 18 far away from the valve plate 17, one end of the spring 23 is connected with the control arm 22, and the other end is connected with the volute 3.
The waste gas bypass mechanism 15 can control the bypass valve 16 to have different opening degrees, and the adjustment of the supercharging degree is realized at different altitudes.
The compressor 2 comprises a compressor shell 8, the compressor shell 8 is a sleeve body with openings at two ends, one end of the compressor shell 8 is connected with the volute 3, one end of the compressor shell 8, which is close to the volute 3, is connected with a compressor end sealing plate 9, and the rotating shaft 6 penetrates through the compressor end sealing plate 9;
the compressor 2 also comprises an impeller 10, the rotating shaft 6 penetrates through the impeller 10, and the central axes of the turbine blades 4, the rotating shaft 6 and the impeller 10 are superposed;
the impeller 10 is connected with the rotating shaft 6 in a bolt fixing mode.
A bearing 11 is arranged between one end, away from the turbine 1, of the rotating shaft 6 and the impeller 10, a lubricating oil cavity 12 is arranged on the compressor shell 8, a lubricating oil pipe 13 is arranged in the lubricating oil cavity 12, one end of the lubricating oil pipe 13 is located in the lubricating oil cavity 12, the other end of the lubricating oil pipe is close to the bearing 11, and the lubricating oil pipe 13 is used for sucking lubricating oil in the lubricating oil cavity 12 to the bearing 11 for lubrication according to the siphon principle; the supercharger does not need to be externally connected with a lubricating pipeline, a lubricating system is simplified, the complexity of arrangement of the supercharger is reduced, the structure is more compact, and the weight of the supercharger is reduced. The lubricating mode utilizes the siphon principle to perform micro-lubrication, has small lubricating oil consumption, can be used for at least half a year after once oiling the lubricating oil cavity 12, and also has the advantage of realizing maintenance-free. One end of the rotating shaft 6 is fixedly connected with the turbine blade 4, and the other end of the rotating shaft is provided with a bearing 11 for supporting, so that the normal working position and the rotating precision of the rotating shaft 6 are maintained.
The lubricant chamber 12 is integral with the compressor housing 8. The bearing 11, the lubricating oil cavity 12 and the lubricating oil pipe 13 are located in the compressor 2 and far away from the high-temperature turbine 1, and meanwhile, heat dissipation is carried out by utilizing high-speed flowing air inlet flow in the compressor 2, so that the working temperature is low, and the reliability of the supercharger is improved.
The inner ring of the bearing 11 is integrated with the rotating shaft 6, and the outer ring of the bearing 11 is fastened with the compressor housing 8. The number of the bearings 11 is at least one, and the lubricating oil pipes 13 correspond to the bearings 11 one to one. The support is more stable, and friction loss is little, and bearing capacity is better.
The bearing 11 is a ceramic rolling bearing. The ceramic rolling bearing has the advantages of corrosion resistance, light weight, difficult deformation under stress, high temperature resistance and the like.
A compressor outlet 14 is provided in the compressor housing 8 adjacent the impeller 10.
One side of the turbine end sealing plate 5, which is close to the compressor end sealing plate 9, is provided with a heat insulation plate 24, and the turbine end sealing plate 5, which is close to the rotating shaft 6, is provided with a shaft seal 25 for sealing. The heat insulation plate 24 prevents the turbine 1 with high temperature from influencing the compressor 2 during operation, and the shaft seal 25 can play a good role in sealing during high-speed rotation.
Engine exhaust gas is introduced into the turbine 1 from the exhaust gas inlet 7, pressure energy and heat energy of the exhaust gas are converted into mechanical energy for rotating the turbine blades 4, the turbine blades 4 are coaxial with the impeller 10, the impeller 10 is driven to rotate, and intake pressurization is achieved. When the impeller 10 rotates at a high speed, the lubricating oil in the lubricating oil chamber 12 is sucked to the rolling elements of the bearing 11 for lubrication through the lubricating oil pipe 13 by using the siphon principle. Because the bearing 11, the lubricating oil cavity 12 and the lubricating oil pipe 13 of the supercharger special for high-altitude power recovery of the aviation piston engine are far away from the high-temperature turbine 1, the consumption of the lubricating oil is low, and the supercharger can work for a long time only by injecting a certain amount of lubricating oil into the lubricating oil cavity 12. The spring 23 in the exhaust gas bypass mechanism 15 is an extension spring, the spring 23 in a natural state is connected with the control arm 22, the valve plate 17 is in an open state, most of the engine exhaust gas directly flows out from the bypass valve 16 without passing through the turbine 1, and the supercharging degree is low. When the boost pressure needs to be increased, the control motor 20 pulls the pull wire 21, the pull wire 21 pulls the control arm 22 to rotate against the initial tension of the spring 23, the control arm 22 drives the valve shaft 18 to open the valve plate 17, the amount of exhaust gas passing through the turbine 1 is increased, and the boost degree is increased. Thus, the bypass valve 16 has different opening degrees under the control of the motor 20. At different altitudes, the degree of supercharging is adjusted by adjusting the opening degree of the bypass valve 16 in the waste gas bypass mechanism 15 according to the demand. The supercharger special for high-altitude power recovery of the aviation piston engine provided by the invention has the advantages that the structure and the light weight design are realized, the lubricating system of the traditional supercharger is simplified, the high-altitude power recovery bypass valve and the control system thereof are added, the weight is reduced, the complexity of the arrangement of the lubricating system is reduced, the power requirement of the aviation piston engine can be met, and a certain flying height is achieved.
According to the embodiment, the special booster for recovering the high altitude power of the aviation piston engine provided by the invention at least has the following beneficial effects:
1. the lubricating oil cavity of the special supercharger for high-altitude power recovery of the aviation piston engine is arranged in the air compressor, the lubricating oil pipe is used for sucking the lubricating oil in the lubricating oil cavity to the bearing for lubrication according to the siphon principle, the supercharger does not need to be externally connected with a lubricating pipeline, a lubricating system is simplified, the complexity of the arrangement of the supercharger is reduced, the structure is more compact, and the weight of the supercharger is reduced.
2. The bearing, the lubricating oil cavity and the lubricating oil pipe in the special supercharger for high-altitude power recovery of the aviation piston engine are positioned in the air compressor and far away from the high-temperature turbine, and meanwhile, the air inlet airflow flowing at high speed in the air compressor is used for heat dissipation, so that the working temperature is low, and the reliability of the supercharger is improved.
3. One end of a rotating shaft in the supercharger special for high-altitude power recovery of the aviation piston engine is fixedly connected with a turbine blade, and the other end of the rotating shaft is provided with a bearing for supporting, so that the normal working position and the rotating precision of the rotating shaft are kept.
Although some specific embodiments of the present invention have been described in detail by way of examples, it should be understood by those skilled in the art that the above examples are for illustrative purposes only and are not intended to limit the scope of the present invention. It will be appreciated by those skilled in the art that modifications may be made to the above embodiments without departing from the scope and spirit of the invention. The scope of the invention is defined by the appended claims.

Claims (5)

1. The utility model provides a special booster of aviation piston engine high altitude power recovery which characterized in that includes: a turbine and a compressor;
the turbine comprises a volute, the volute is a sleeve body with openings at two ends, one end of the volute is connected with the compressor, and one end of the volute, close to the compressor, is connected with a turbine end sealing plate;
the turbine also comprises a turbine blade arranged in the volute, the central axis of the turbine blade is perpendicular to the turbine end sealing plate, one side of the turbine blade, which is close to the turbine end sealing plate, is fixedly connected with a rotating shaft, and the rotating shaft penetrates through the turbine end sealing plate;
the volute is provided with a waste gas inlet close to the turbine blade;
the compressor comprises a compressor shell, the compressor shell is a sleeve body with openings at two ends, one end of the compressor shell is connected with the volute, one end of the compressor shell, which is close to the volute, is connected with a compressor end sealing plate, and the rotating shaft penetrates through the compressor end sealing plate;
the compressor also comprises an impeller, the rotating shaft penetrates through the impeller, and the central axes of the turbine blades, the rotating shaft and the impeller are superposed;
a bearing is arranged between one end, far away from the turbine, of the rotating shaft and the impeller, a lubricating oil cavity is formed in the compressor shell, a lubricating oil pipe is arranged in the lubricating oil cavity, one end of the lubricating oil pipe is located in the lubricating oil cavity, the other end of the lubricating oil pipe is close to the bearing, and the lubricating oil pipe is used for sucking lubricating oil in the lubricating oil cavity to the bearing for lubrication according to the siphon principle;
a compressor outlet is formed in the compressor shell close to the impeller;
the turbine further comprises an exhaust gas bypass mechanism,
the waste gas bypass mechanism comprises a bypass valve arranged on the volute, the bypass valve comprises a valve plate, a valve shaft and a shaft sleeve, the valve shaft penetrates through the shaft sleeve, and one end of the valve shaft is connected with the valve plate;
the waste gas bypass mechanism also comprises a motor, a pull wire, a control arm and a spring, wherein one end of the pull wire is connected with the motor, and the other end of the pull wire is connected with the control arm; one end of the control arm is connected with the pull wire, the other end of the control arm is connected with the spring, the middle part of the control arm is connected with one end, far away from the valve plate, of the valve shaft, one end of the spring is connected with the control arm, and the other end of the spring is connected with the volute;
a heat insulation plate is arranged on one side, close to the compressor end sealing plate, of the turbine end sealing plate, and a shaft seal for sealing is arranged at the position, close to the rotating shaft, of the turbine end sealing plate;
the inner ring of the bearing is integrated with the rotating shaft, and the outer ring of the bearing is clamped with the compressor shell.
2. The aviation piston engine high-altitude power recovery dedicated supercharger according to claim 1, wherein the number of the bearings is at least one, and the lubricating oil pipes are in one-to-one correspondence with the bearings.
3. The aviation piston engine high altitude power recovery dedicated supercharger of claim 1 wherein the lubricating oil cavity is integral with the compressor housing.
4. The special booster for high altitude power recovery of aviation piston engines as claimed in claim 1, wherein the impeller and the rotating shaft are connected by bolt fastening.
5. The special booster for high altitude power recovery of aviation piston engines as claimed in claim 1, wherein the bearings are ceramic rolling bearings.
CN202110239309.6A 2021-03-04 2021-03-04 Special booster for high-altitude power recovery of aviation piston engine Active CN112780400B (en)

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