CN112096496A - Turbine power recovery unit, aviation piston engine and aviation aircraft - Google Patents

Turbine power recovery unit, aviation piston engine and aviation aircraft Download PDF

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Publication number
CN112096496A
CN112096496A CN201910565786.4A CN201910565786A CN112096496A CN 112096496 A CN112096496 A CN 112096496A CN 201910565786 A CN201910565786 A CN 201910565786A CN 112096496 A CN112096496 A CN 112096496A
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China
Prior art keywords
power recovery
turbine
compressor
air
stage compressor
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Pending
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CN201910565786.4A
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Chinese (zh)
Inventor
李清
周尹强
张登峰
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Fonair Aviation Co Ltd
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Fonair Aviation Co Ltd
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Publication of CN112096496A publication Critical patent/CN112096496A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N5/00—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy
    • F01N5/04—Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using kinetic energy
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/08—Adaptations for driving, or combinations with, pumps
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/12—Combinations with mechanical gearing
    • 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
    • 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)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)

Abstract

The invention provides a turbine power recovery device, an aviation piston engine and an aviation aircraft, wherein the turbine power recovery device comprises a turbine shaft and a turbine, a turbine is arranged in the turbine, the turbine power recovery device also comprises at least one power recovery mechanism and a transmission mechanism used for transmitting the power of the turbine to the power recovery mechanism, the transmission mechanism comprises a driven wheel in transmission connection with the power recovery mechanism and a driving wheel used for driving the driven wheel to rotate, and the turbine and the driving wheel are respectively fixed on the turbine shaft so that the turbine drives the driving wheel to rotate. The turbine power recovery device, the aviation piston engine and the aviation aircraft effectively improve the utilization efficiency of energy, the power generated by the turbine can be matched with the power according to the actual requirement of the power recovery mechanism, the matching performance is better, and the power recovery mechanism can reach the optimal working state.

Description

Turbine power recovery unit, aviation piston engine and aviation aircraft
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a turbine power recovery device, an aviation piston engine and an aviation aircraft.
Background
The aviation aircraft in the low-altitude and low-speed field is often used as an ideal flying platform to be widely applied to various fields of military and civil use due to simple structure and low manufacturing cost. The aviation aircraft in the low-altitude low-speed field is generally powered by an aviation piston engine, propellers such as an air propeller are driven by the engine to rotate to generate propulsive force, but in the flying process, along with the increase of flying height, the air density is reduced, the air inlet pressure is reduced, so that the power output of the aviation piston engine is reduced quickly, and the power demand of the aviation aircraft cannot be met.
To solve the above problem, a turbocharger is generally used to increase the intake pressure to meet the power demand of the aircraft. The traditional turbocharger generally adopts a pressurization mode that one turbine coaxially drives one compressor, however, the power generated by the turbine cannot be matched according to actual needs, so that the problem of low energy utilization rate is caused.
Disclosure of Invention
The invention aims to provide a turbine power recovery device, which aims to solve the technical problem that the power generated by a turbine in the prior art cannot be matched according to actual needs, so that the energy utilization rate is low.
In order to achieve the purpose, the invention adopts the technical scheme that: the turbine power recovery device further comprises at least one power recovery mechanism used for converting the power of the turbine into driving force and a transmission mechanism used for transmitting the power of the turbine to the power recovery mechanism, the transmission mechanism comprises a driven wheel in transmission connection with the power recovery mechanism and a driving wheel used for driving the driven wheel to rotate, and the turbine and the driving wheel are respectively fixed on the turbine shaft so that the turbine drives the driving wheel to rotate.
Further, the driving wheel and the driven wheel are gears which are meshed with each other respectively.
Further, the driving wheel and the driven wheel are respectively conical gears which are meshed with each other.
Further, the transmission mechanism further comprises a speed reducing mechanism, and the speed reducing mechanism is connected between the driven wheel and the power recovery mechanism.
Further, the reduction gears include a first gear and a second gear meshed with the first gear, the first gear is in transmission connection with the driven wheel, the second gear is in transmission connection with the power recovery mechanism, and the number of teeth of the first gear is smaller than the number of teeth of the second gear.
Furthermore, the reduction mechanism also comprises a transmission shaft, and the driven wheel and the first gear are respectively arranged at two ends of the transmission shaft.
Further, the first air inlet of the turbine is used for communicating with an exhaust gas outlet of an aviation piston engine so that exhaust gas discharged by the aviation piston engine enters the turbine and drives the turbine to rotate.
Further, the power recovery mechanism is a generator.
Further, turbine power recovery unit still includes the one-level compressor, the one-level compressor is fixed in the turbine shaft is kept away from the one end of turbine, be provided with in the one-level compressor by the turbine drives the one-level compressor wheel that rotates in order to carry out the compression to the air that gets into in the one-level compressor, the one-level compressor is seted up and is used for supplying the air to get into second air inlet in the one-level compressor and be used for the first gas outlet with aviation piston engine's air inlet intercommunication.
Further, the power recovery mechanism is a primary compressor, a primary compressor impeller is arranged in the primary compressor, the turbine drives the turbine to rotate so as to compress air entering the primary compressor, and a first air outlet which is used for supplying air to enter a second air inlet in the primary compressor and is used for being communicated with an air inlet of the aviation piston engine is formed in the primary compressor.
The turbine power recovery device further comprises a primary compressor, the primary compressor is fixed at one end, far away from the turbine, of the turbine shaft, a primary compressor impeller driven by the turbine to rotate so as to compress air entering the primary compressor is arranged in the primary compressor, and the primary compressor is provided with a first air outlet and a second air inlet for allowing air to enter the primary compressor;
the power recovery mechanism is a secondary compressor, a secondary compressor impeller which is in transmission connection with the driven wheel and is used for compressing air entering the secondary compressor is arranged in the secondary compressor, and the secondary compressor is provided with a third air inlet communicated with the first air outlet and a second air outlet communicated with an air inlet of the aviation piston engine.
Furthermore, the number of the power recovery mechanisms is at least two, the number of the driven wheels is the same as that of the power recovery mechanisms, each power recovery mechanism is in transmission connection with the corresponding driven wheel, the number of the driving wheels is one, and one driving wheel is in transmission connection with each driven wheel.
Further, each of the power recovery mechanisms is a generator.
Further, at least one of the power recovery mechanisms is a primary compressor, at least one of the power recovery mechanisms is a secondary compressor,
a first-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the first-stage compressor is arranged in the first-stage compressor, and the first-stage compressor is provided with a first air outlet and a second air inlet for allowing air to enter the first-stage compressor;
and a second-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the second-stage compressor is arranged in the second-stage compressor, and the second-stage compressor is provided with a second air outlet and a third air inlet communicated with the first air outlet.
Furthermore, at least one power recovery mechanism is the generator, at least one power recovery mechanism is the primary compressor, be provided with in the primary compressor with correspond from the driving wheel transmission connect in order to carry out the one-level compressor wheel that compresses to the air that gets into in the primary compressor, the primary compressor has seted up first gas outlet and is used for supplying air to get into the second air inlet in the primary compressor.
Further, the turbine power recovery device further comprises a first-stage compressor, the first-stage compressor is fixed at one end, far away from the turbine shaft, of the turbine, a first-stage compressor impeller is arranged in the first-stage compressor, the turbine drives the turbine to rotate so as to compress air entering the first-stage compressor, and a second air inlet and a first air outlet are formed in the first-stage compressor and used for allowing air to enter the first-stage compressor.
Further, each of the power recovery mechanisms is a generator.
Further, at least one of the power recovery mechanisms is a secondary compressor, at least one of the power recovery mechanisms is a tertiary compressor,
a second-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the second-stage compressor is arranged in the second-stage compressor, and the second-stage compressor is provided with a second air outlet and a third air inlet communicated with the first air outlet;
and a third-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the third-stage compressor is arranged in the third-stage compressor, and the third-stage compressor is provided with a third air outlet and a fourth air inlet communicated with the second air outlet.
Furthermore, at least one power recovery mechanism is a generator, at least one power recovery mechanism is a secondary compressor, a secondary compressor impeller which is in transmission connection with the corresponding driven wheel and is used for compressing air entering the secondary compressor is arranged in the secondary compressor, and the secondary compressor is provided with a second air outlet and a third air inlet communicated with the first air outlet.
The invention also provides an aviation piston engine which is provided with the turbine power recovery device, wherein the turbine power recovery device is the turbine power recovery device.
The invention also provides an aviation aircraft, which comprises the aviation piston engine.
The turbine power recovery device, the aviation piston engine and the aviation aircraft provided by the invention have the beneficial effects that: compared with the prior art, the turbine power recovery device has the advantages that the power recovery mechanism is arranged, the power of the turbine is transmitted to the power recovery mechanism through the transmission mechanism, the utilization efficiency of energy is effectively improved, the power generated by the turbine can be matched with the power of the power recovery mechanism according to the actual requirement of the power recovery mechanism through the matching arrangement of the driving wheel and the driven wheel, the matching performance is better, the power recovery mechanism can reach the optimal working state, and the waste of energy is avoided.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive exercise.
Fig. 1 is a schematic structural view of a turbine power recovery apparatus according to a first embodiment of the present invention;
FIG. 2 is a schematic structural view of a turbine power recovery apparatus according to a second embodiment of the present invention;
FIG. 3 is a schematic structural view of a turbine power recovery apparatus according to a third embodiment of the present invention;
FIG. 4 is a schematic structural view of a turbine power recovery apparatus according to a fourth embodiment of the present invention;
FIG. 5 is a schematic structural view of a turbine power recovery apparatus according to a fifth embodiment of the present invention;
FIG. 6 is a schematic structural view of a turbine power recovery apparatus according to a sixth embodiment of the present invention;
FIG. 7 is a schematic structural diagram of a transmission mechanism according to a sixth embodiment of the present invention;
FIG. 8 is a schematic structural view of a turbine power recovery apparatus according to a seventh embodiment of the present invention;
fig. 9 is a schematic structural view of a turbine power recovery apparatus according to an eighth embodiment of the present invention;
fig. 10 is a schematic structural view of a turbine power recovery apparatus according to a ninth embodiment of the present invention;
fig. 11 is a schematic structural view of a turbine power recovery apparatus according to a tenth embodiment of the present invention;
fig. 12 is a schematic structural view of a turbine power recovery apparatus according to an eleventh embodiment of the present invention;
fig. 13 is a schematic structural view of a turbine power recovery apparatus according to a twelfth embodiment of the present invention;
fig. 14 is a schematic structural view of a turbine power recovery apparatus according to a thirteenth embodiment of the present invention;
fig. 15 is a schematic structural view of a turbine power recovery apparatus according to a fourteenth embodiment of the present invention.
Wherein, in the figures, the respective reference numerals:
a 10-turbine shaft; 20-a turbine; 21-a turbine; 22-a first air inlet; 30-a primary compressor; 31-primary compressor impeller; 32-a first air outlet; 33-a second gas inlet; 40-a power recovery mechanism; 41-a generator; 42-a secondary compressor; 421-two-stage compressed air impeller; 422-third air inlet; 423-second air outlet; 50-a driving wheel; 60-driven wheel; 70-a first gear; 80-a second gear; 90-a drive shaft; 100-three-stage compressor; 110-three-stage compressor impeller; 120-a fourth inlet; 130-third outlet.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and is therefore not to be construed as limiting the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
Example 1
Referring to fig. 1, a turbine power recovery apparatus according to a first embodiment of the present invention will now be described. The first embodiment of the invention provides a turbine power recovery device, which comprises a turbine shaft 10 and a turbine 20. The turbine 21 is provided in the turbine 20, and the turbine power recovery apparatus further includes at least one power recovery mechanism 40 for converting power of the turbine 21 into driving power and a transmission mechanism for transmitting the power of the turbine 21 to the power recovery mechanism 40. Specifically, the transmission mechanism includes a driven wheel 60 in transmission connection with the power recovery mechanism 40, and a driving wheel 50 for driving the driven wheel 60 to rotate. Turbine 21, drive wheel 50 is fixed in respectively on turbine shaft 10, thereby make turbine 21 can drive wheel 50 and rotate, because this follow driving wheel 60 is connected with the transmission of power recovery mechanism 40, thereby realize that the power transmission that produces turbine 21 is for power recovery mechanism 40, the utilization efficiency of the energy has effectively been improved, and because this drive wheel 50 sets up with the cooperation from driving wheel 60, make the power that turbine 21 produced can carry out power matching according to the actual need of power recovery mechanism 40, the matching performance is better, power recovery mechanism 40 can reach the best operating condition, avoid the waste of the energy.
Compared with the prior art, the turbine power recovery device provided by the invention has the advantages that the power recovery mechanism 40 is arranged, the power of the turbine 21 is transmitted to the power recovery mechanism 40 through the transmission mechanism, the utilization efficiency of energy is effectively improved, the power generated by the turbine 21 can be matched with the power according to the actual requirement of the power recovery mechanism 40 through the matching arrangement of the driving wheel 50 and the driven wheel 60, the matching performance is better, the power recovery mechanism 40 can reach the optimal working state, and the waste of energy is avoided.
Further, referring to fig. 1, as an embodiment of the turbine power recovery device according to the first embodiment of the present invention, the driving wheel 50 and the driven wheel 60 are gears engaged with each other. The driving wheel 50 and the driven wheel 60 are driven by adopting gears which are meshed with each other, so that the utilization efficiency of energy can be improved. Preferably, the driving pulley 50 and the driven pulley 60 may be bevel gears that mesh with each other, and the driving direction may be changed by performing driving using the bevel gears that mesh with each other, so that the driving direction is changed from a direction coaxial with the turbine shaft 10 to a direction perpendicular to the turbine shaft 10, and the size of the turbine power recovery apparatus in the axial direction may be reduced. It should be noted that the transmission manner of the driving wheel 50 and the driven wheel 60 is not limited to this, for example, in other preferred embodiments of the present invention, the driving wheel 50 and the driven wheel 60 can also be transmitted by a belt or a chain.
Further, referring to fig. 1, as a specific implementation of the turbine power recovery device according to the first embodiment of the present invention, the first air inlet 22 of the turbine 20 is used to communicate with an exhaust gas outlet (not shown) of the aviation piston engine, so that the exhaust gas discharged by the aviation piston engine enters the turbine 20 and drives the turbine 21 to rotate, which not only can avoid the problem of low thermal efficiency caused by the exhaust gas discharged to the atmosphere from the aviation piston engine, but also can drive the turbine 21 to rotate by using the exhaust gas, and the turbine 21 then provides power to the power recovery mechanism 40, thereby effectively improving the utilization efficiency of energy.
Example 2
Referring to fig. 2, a specific structure of a turbine power recovery apparatus according to a second embodiment of the present invention is substantially the same as the specific structure of the turbine power recovery apparatus according to the first embodiment of the present invention, except that:
in the present embodiment, the power recovery mechanism 40 is a generator 41. The generator 41 is in transmission connection with the driven wheel 60. The waste gas exhausted by the aviation piston engine is utilized to push the turbine 21 to rotate at a high speed, the turbine 21 transmits power to the generator 41 through the driving wheel 50 and the driven wheel 60, so that the waste gas exhausted by the aviation piston engine is converted into required electric power, the waste gas heat energy of the aviation piston engine is fully utilized, the heat efficiency of the aviation piston engine is improved, the effective output power of the aviation piston engine is improved, and the problems that the effective output power of the aviation piston engine is reduced and the fuel consumption rate is increased due to the fact that the generator extracts power from the crankshaft end of the aviation piston engine in the prior art are solved.
Example 3
Referring to fig. 3, a specific structure of a turbine power recovery apparatus according to a third embodiment of the present invention is substantially the same as the specific structure of the turbine power recovery apparatus according to the first embodiment of the present invention, except that:
in the present embodiment, the power recovery mechanism 40 is a primary compressor 30, and a primary compressor impeller 31 is disposed in the primary compressor 30. The turbine 21 drives the primary compressor impeller 31 to rotate so as to compress air entering the primary compressor 30, and the air compressed by the primary compressor impeller 31 can enter a cylinder of the aviation piston engine to be used as power input of the aviation piston engine. Due to the arrangement of the primary air compressor 30, the air inlet pressure of the aviation piston engine can be increased, and the power requirement of the aviation piston engine is met. Specifically, the primary compressor 30 is provided with a first air outlet 32 and a second air inlet 33. A second air inlet 33 is used to supply air into the primary compressor 30. The first air outlet 32 communicates with the air inlet of the aviation piston engine.
Example 4
Referring to fig. 4, a specific structure of a turbine power recovery apparatus according to a fourth embodiment of the present invention is substantially the same as the specific structure of the turbine power recovery apparatus according to the second embodiment of the present invention, except that:
in the embodiment, the turbine power recovery device further includes a primary compressor 30, the primary compressor 30 is fixed on an end of the turbine shaft 10 away from the turbine 21, and a primary compressor impeller 31 is disposed in the primary compressor 30. The turbine 21 drives the primary compressor impeller 31 to rotate so as to compress air entering the primary compressor 30, and the primary compressor 30 is provided with a first air outlet 32 and a second air inlet 33. The second air inlet 33 is used for allowing air to enter the primary air compressor 30, and the first air outlet 32 is communicated with an air inlet of the aviation piston engine, so that the air compressed by the primary air compressor impeller 31 can enter an air cylinder of the aviation piston engine and is used as power input of the aviation piston engine. The primary compressor 30 of the embodiment is fixed at one end of the turbine shaft 10 far away from the turbine 21, so that the turbine 21 can directly drive the primary compressor impeller 31 to rotate so as to compress air.
The operating principle of the turbine power recovery device in the present embodiment is as follows:
firstly, the aviation piston engine discharges exhaust gas with higher temperature and certain pressure, and the exhaust gas enters the turbine 20 through the first air inlet 22 and impacts the turbine 21 to push the turbine 21 to rotate at high speed;
then, the turbine 21 drives the primary compressor impeller 31 and the driving wheel 50 which are coaxially fixed with the turbine to rotate synchronously, air is compressed by the primary compressor impeller 31 rotating at a high speed and then enters a cylinder of the aviation piston engine, and the driving wheel 50 drives the driven wheel 60 to rotate, so that the generator 41 is driven to rotate, and therefore waste gas discharged by the aviation piston engine is converted into required electric power.
Example 5
Referring to fig. 5, a specific structure of a turbine power recovery apparatus according to a fifth embodiment of the present invention is substantially the same as the specific structure of the turbine power recovery apparatus according to the first embodiment of the present invention, except that:
in the embodiment, the turbine power recovery device further includes a primary compressor 30, the primary compressor 30 is fixed on one end of the turbine shaft 10 far away from the turbine 21, and the power recovery mechanism 40 is a secondary compressor 42. Specifically, a secondary compressor wheel 421 is arranged in the secondary compressor 42, and the secondary compressor wheel 421 is in transmission connection with the driven wheel 60. The turbine 21 transmits power to the secondary compressor wheel 421 via the drive pulley 50 and the driven pulley 60. The specific structure of the primary compressor 30 is the same as that of the primary compressor 30 in the third embodiment of the present invention, and will not be described herein again. The primary compressor 30 is fixed on one end of the turbine shaft 10 far away from the turbine 21, so that the turbine 21 can directly drive the primary compressor impeller 31 to rotate so as to compress air. The secondary compressor 42 is provided with a third air inlet 422 and a second air outlet 423, the third air inlet 422 is communicated with the first air outlet 32, and the second air outlet 423 is communicated with an air inlet of the aviation piston engine, so that the air compressed by the primary compressor 30 can enter the secondary compressor 42 through the third air inlet 422 and is subjected to secondary compression by a secondary compressor impeller 421, the air inlet pressure of the aviation piston engine is increased, the effective power output of the aviation piston engine is increased, the plateau and high altitude adaptability of the aviation piston engine is improved, and the fuel economy of the aviation piston engine is improved.
Example 6
Referring to fig. 6 to 7, a specific structure of a turbine power recovery apparatus according to a sixth embodiment of the present invention is substantially the same as that of the turbine power recovery apparatus according to the first embodiment of the present invention, except that:
in this embodiment, the transmission mechanism further includes a speed reduction mechanism connected between the driven wheel 60 and the power recovery mechanism 40. Through setting up reduction gears to make the speed of power recovery mechanism 40 be less than the speed of turbine 21, the power that turbine 21 produced can carry out power matching according to the actual need of power recovery mechanism 40, and the matching performance is better, and power recovery mechanism 40 can reach the best operating condition, avoids the waste of the energy. Specifically, in the present embodiment, the speed reducing mechanism includes a first gear 70 and a second gear 80 engaged with the first gear 70, the first gear 70 is in transmission connection with the driven wheel 60, the second gear 80 is in transmission connection with the power recovery mechanism 40, and the number of teeth of the first gear 70 is smaller than the number of teeth of the second gear 80. Preferably, the first gear 70 and the second gear 80 are spur gears, which are simple to manufacture and low in cost. It should be noted that the arrangement of the first gear 70 and the second gear 80 is not limited to this, for example, in other preferred embodiments of the present invention, the first gear 70 and the second gear 80 may also be helical gears.
Further, referring to fig. 7, as a specific implementation manner of the turbine power recovery device according to the sixth embodiment of the present invention, the speed reducing mechanism further includes a transmission shaft 90, and the driven wheel 60 and the first gear 70 are respectively mounted at two ends of the transmission shaft 90. By the arrangement of the transmission shaft 90, the driven wheel 60 and the first gear 70 can be arranged in the radial direction of the turbine shaft 10, thereby effectively reducing the size of the turbine power recovery apparatus in the axial direction.
Example 7
Referring to fig. 8, a specific structure of a turbine power recovery apparatus according to a seventh embodiment of the present invention is substantially the same as the specific structure of the turbine power recovery apparatus according to the first embodiment of the present invention, except that:
in the present embodiment, the number of the power recovery mechanisms 40 is at least two, the number of the driven wheels 60 is the same as the number of the power recovery mechanisms 40, each power recovery mechanism 40 is in transmission connection with the corresponding driven wheel 60, the number of the driving wheels 50 is one, and one driving wheel 50 is in transmission connection with each driven wheel 60. Each power recovery mechanism 40 is driven by the same driving wheel 50, so that the use of parts can be saved, the production cost can be reduced, the whole weight of the turbine power recovery device can be reduced, and the utilization rate of energy sources can be improved. In this embodiment, the number of the power recovery mechanisms 40 is two, and it should be noted that the number of the power recovery mechanisms 40 is not limited to this, for example, in other preferred embodiments of the present invention, the number of the power mechanisms 40 may also be set according to actual needs, and may be, for example, three, four, or six.
Example 8
Referring to fig. 9, a specific structure of a turbine power recovery apparatus according to an eighth embodiment of the present invention is substantially the same as that of the turbine power recovery apparatus according to the seventh embodiment of the present invention, except that:
in the present embodiment, each power recovery mechanism 40 is a generator 41. Preferably, the number of the generators 41 may be set to two. The turbine 21 is pushed to rotate at a high speed by using the waste gas discharged by the aviation piston engine, and the turbine 21 simultaneously drives the generators 41 to rotate through the driving wheel 50 to generate electricity, so that the waste gas discharged by the aviation piston engine is converted into the driving force for rotating the generators 41, the waste gas heat energy of the aviation piston engine is fully utilized, and the electricity generation amount of the generators 41 can be improved to the maximum extent.
Example 9
Referring to fig. 10, a detailed structure of a turbine power recovery apparatus according to a ninth embodiment of the present invention is substantially the same as the detailed structure of the turbine power recovery apparatus according to the seventh embodiment of the present invention, except that:
in the present embodiment, at least one power recovery mechanism 40 is a primary compressor 30 and at least one power recovery mechanism 40 is a secondary compressor 42. Preferably, the number of the power recovery mechanisms 40 is two, wherein one power recovery mechanism 40 is the primary compressor 30 and the other power recovery mechanism 40 is the secondary compressor 42. Wherein, a primary compressor impeller 31 is arranged in the primary compressor 30. The primary compressor impeller 31 is in transmission connection with the corresponding driven wheel 60, and the turbine 21 transmits power to the primary compressor impeller 31 through the driving wheel 50 and the driven wheel 60, so that the primary compressor impeller 31 compresses air entering the primary compressor 30. The primary compressor 30 is provided with a first outlet 32 and a second inlet 33. A secondary compressor wheel 421 is arranged in the secondary compressor 42, and the secondary compressor wheel 421 is in transmission connection with the corresponding driven wheel 60. The turbine 21 transmits power to the secondary compressor wheel 421 through the driving wheel 50 and the corresponding driven wheel 60, so that the secondary compressor wheel 421 compresses air entering the secondary compressor 42. The secondary compressor is provided with a second air outlet 423 and a third air inlet 422. A second air inlet 33 is used to supply air into the primary compressor 30. The third air inlet 422 is communicated with the first air outlet 32, and the second air outlet 423 is directly communicated with an air inlet of the aviation piston engine, so that the gas compressed by the primary compressor 30 can enter the secondary compressor 42 through the third air inlet 422 and is subjected to secondary compression by the secondary compressor impeller 421, the air inlet pressure of the aviation piston engine is increased, the effective power output of the aviation piston engine is increased, the plateau and high altitude adaptive capacity of the aviation piston engine is improved, and the fuel economy of the aviation piston engine is improved. It should be noted that the number of the power recovery mechanisms 40 is not limited to this, for example, in other preferred implementations of the present invention, the power recovery mechanisms 40 may be further configured as a plurality of compressors for sequentially compressing air to achieve maximum layer-by-layer compression of air, and may be configured as three, four, or five, for example.
Example 10
Referring to fig. 11, a specific structure of a turbine power recovery apparatus according to a tenth embodiment of the present invention is substantially the same as that of the turbine power recovery apparatus according to a seventh embodiment of the present invention, except that:
in the present embodiment, at least one power recovery mechanism 40 is a generator 41 and at least one power recovery mechanism is a primary compressor 30. Preferably, the number of the power recovery mechanisms 40 is two, wherein one power recovery mechanism 40 is the generator 41, and the other power recovery mechanism is the primary compressor 30. The primary compressor 30 is internally provided with a primary compressor impeller 31 in transmission connection with the corresponding driven wheel 60, and the primary compressor impeller 31 compresses air entering the primary compressor 30. The primary compressor 30 is provided with a first air outlet 32 and a second air inlet 33 for air to enter the primary compressor 30, and the first air outlet 32 is directly communicated with an air inlet of the aviation piston engine. The generator 41 and the primary compressor 30 are driven to rotate by the same driving wheel 50, so that the energy utilization efficiency can be effectively improved. It should be noted that the number of the power recovery mechanisms 40 is not limited to this, for example, in other preferred implementations of the present invention, the power recovery mechanisms 40 may be further configured as a plurality of compressors for sequentially compressing air to achieve maximum layer-by-layer compression of air, and may be configured as three, four, or five, for example.
Example 11
Referring to fig. 12, a specific structure of a turbine power recovery apparatus according to an eleventh embodiment of the present invention is substantially the same as that of the turbine power recovery apparatus according to the eighth embodiment of the present invention, except that:
in this embodiment, the turbine power recovery device further includes a primary compressor 30, the primary compressor 30 is fixed to one end of the turbine shaft 10, which is far away from the turbine 21, so that the turbine 21 can directly drive the primary compressor impeller 31 to rotate so as to compress air, and the air compressed by the primary compressor impeller 31 can enter a cylinder of the aviation piston engine to be used as power input of the aviation piston engine. Due to the arrangement of the primary air compressor 30, the air inlet pressure of the aviation piston engine can be increased, and the power requirement of the aviation piston engine is met. The specific structure of the primary compressor 30 is the same as that of the primary compressor 30 in the third embodiment of the present invention, and is not described herein again.
Example 12
Referring to fig. 13, a specific structure of a turbine power recovery apparatus according to a twelfth embodiment of the present invention is substantially the same as that of the turbine power recovery apparatus according to the eleventh embodiment of the present invention, except that:
in the present embodiment, each power recovery mechanism 40 is a generator 41. Preferably, the number of the generators 41 may be set to two. The turbine 21 is pushed to rotate at a high speed by using the waste gas discharged by the aviation piston engine, and the turbine 21 simultaneously drives the generators 41 to rotate through the driving wheel 50 to generate electricity, so that the waste gas discharged by the aviation piston engine is converted into the driving force for rotating the generators 41, the waste gas heat energy of the aviation piston engine is fully utilized, and the electricity generation amount of the generators 41 can be improved to the maximum extent.
Example 13
Referring to fig. 14, a specific structure of a turbine power recovery apparatus according to a thirteenth embodiment of the present invention is substantially the same as that of the turbine power recovery apparatus according to the eleventh embodiment of the present invention, except that:
in the present embodiment, at least one power recovery mechanism 40 is a secondary compressor 42 and at least one power recovery mechanism 40 is a tertiary compressor 100. Preferably, the number of the power recovery mechanisms 40 is two, wherein one power recovery mechanism 40 is a secondary compressor 42 and the other power recovery mechanism 40 is a tertiary compressor 100. Wherein, a secondary compressor wheel 421 is arranged in the secondary compressor 42, and the secondary compressor wheel 421 is in transmission connection with the corresponding driven wheel 60. The turbine 21 transmits power to the secondary compressor wheel 421 through the driving wheel 50 and the corresponding driven wheel 60, so that the secondary compressor wheel 421 compresses air entering the secondary compressor 42. The secondary compressor 42 is provided with a second outlet 423 and a third inlet 422. A three-stage compressor wheel 110 is arranged in the three-stage compressor 100, and the three-stage compressor wheel 110 is in transmission connection with the corresponding driven wheel 60. The turbine 21 transmits power to the three-stage compressor wheel 110 through the drive pulley 50 and the corresponding driven pulley 60, so that the three-stage compressor wheel 110 compresses air entering the three-stage compressor 100. The tertiary compressor 100 is provided with a third outlet 130 and a fourth inlet 120. Air enters from the second air inlet 33, the first air outlet 32 is communicated with the third air inlet 422, the second air outlet 423 is communicated with the fourth air inlet 120, the third air outlet 130 is directly communicated with the air inlet of the aviation piston engine, so that the air compressed by the primary air compressor 30 can enter the secondary air compressor 42 through the third air inlet 422 and be subjected to secondary compression by the secondary compressor impeller 421, the air compressed by the secondary compressor impeller 421 can enter the tertiary air compressor 100 through the second air outlet 423 and be subjected to tertiary compression by the tertiary compressor impeller 110, the air inlet pressure of the aviation piston engine is increased, the effective power output of the aviation piston engine is increased, the plateau and high altitude adaptive capacity of the aviation piston engine is improved, and the fuel economy of the aviation piston engine is improved. It should be noted that the number of the power recovery mechanisms 40 is not limited to this, for example, in other preferred implementations of the present invention, the power recovery mechanisms 40 may be further configured as a plurality of compressors for sequentially compressing air to achieve maximum layer-by-layer compression of air, and may be configured as three, four, or five, for example.
Example 14
Referring to fig. 15, a specific structure of a turbine power recovery apparatus according to a fourteenth embodiment of the present invention is substantially the same as that of the turbine power recovery apparatus according to the eleventh embodiment of the present invention, except that:
in the present embodiment, at least one power recovery mechanism 40 is a generator 41 and at least one power recovery mechanism 40 is a secondary compressor 42. The generator 41 and the secondary compressor 42 are driven to rotate by the same driving wheel 50, so that the energy utilization efficiency can be effectively improved. Preferably, the number of the power recovery mechanisms 40 is two, wherein one power recovery mechanism 40 is the generator 41, and the other power recovery mechanism is the secondary compressor 42. Wherein, a secondary compressor wheel 421 is arranged in the secondary compressor 42, and the secondary compressor wheel 421 is in transmission connection with the corresponding driven wheel 60. The turbine 21 transmits power to the secondary compressor wheel 421 through the driving wheel 50 and the corresponding driven wheel 60, so that the secondary compressor wheel 421 compresses air entering the secondary compressor 42. The secondary compressor is provided with a second air outlet 423 and a third air inlet 422. In this embodiment, the third air inlet 422 is communicated with the first air outlet 32, and the second air outlet 423 is directly communicated with the air inlet of the aviation piston engine, so that the gas compressed by the primary compressor 30 can enter the secondary compressor 42 through the third air inlet 422 and is subjected to secondary compression by the secondary compressor impeller 421, thereby increasing the air inlet pressure of the aviation piston engine, further increasing the effective power output of the aviation piston engine, improving the plateau and high altitude adaptability of the aviation piston engine, and improving the fuel economy of the aviation piston engine. It should be noted that the number of the power recovery mechanisms 40 is not limited to this, for example, in other preferred implementations of the present invention, the power recovery mechanisms 40 may be further configured as a plurality of compressors for sequentially compressing air to achieve maximum layer-by-layer compression of air, and may be configured as three, four, or five, for example.
The invention also provides an aviation piston engine which is provided with the turbine power recovery device, and the turbine power recovery device adopts the turbine power recovery device in the specific embodiment.
The aviation piston engine provided by the invention adopts the turbine power recovery device in the above specific embodiment, so that the power recovery mechanism 40 is arranged, and the power of the turbine 21 is transmitted to the power recovery mechanism 40 through the transmission mechanism, thereby not only effectively improving the utilization efficiency of energy, but also enabling the power generated by the turbine 21 to be matched with the power according to the actual requirement of the power recovery mechanism 40 through the matching arrangement of the driving wheel 50 and the driven wheel 60, having better matching performance, enabling the power recovery mechanism 40 to reach the optimal working state, and avoiding the waste of energy.
The invention also provides an aviation aircraft which comprises the aviation piston engine, wherein the aviation piston engine adopts the aviation piston engine in the specific embodiment.
The aviation aircraft provided by the invention adopts the aviation piston engine in the above specific embodiment, so that the power recovery mechanism 40 is arranged, and the power of the turbine 21 is transmitted to the power recovery mechanism 40 through the transmission mechanism, thereby not only effectively improving the utilization efficiency of energy, but also enabling the power generated by the turbine 21 to be matched with the power according to the actual requirement of the power recovery mechanism 40 through the matching arrangement of the driving wheel 50 and the driven wheel 60, so that the matching performance is better, the power recovery mechanism 40 can reach the optimal working state, and the waste of energy is avoided.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.

Claims (21)

1. The turbine power recovery device comprises a turbine shaft and a turbine, wherein a turbine is arranged in the turbine, and the turbine power recovery device is characterized in that: the turbine power recovery device further comprises at least one power recovery mechanism for converting the power of the turbine into driving force and a transmission mechanism for transmitting the power of the turbine to the power recovery mechanism, the transmission mechanism comprises a driven wheel in transmission connection with the power recovery mechanism and a driving wheel for driving the driven wheel to rotate, and the turbine and the driving wheel are respectively fixed on the turbine shaft so that the turbine drives the driving wheel to rotate.
2. The turbine power recovery device of claim 1, wherein: the driving wheel and the driven wheel are gears which are meshed with each other respectively.
3. The turbine power recovery device of claim 2, wherein: the driving wheel and the driven wheel are respectively conical gears which are meshed with each other.
4. The turbine power recovery device of claim 1, wherein: the transmission mechanism further comprises a speed reducing mechanism, and the speed reducing mechanism is connected between the driven wheel and the power recovery mechanism.
5. The turbine power recovery device of claim 4, wherein: the speed reducing mechanism comprises a first gear and a second gear meshed with the first gear, the first gear is in transmission connection with the driven wheel, the second gear is in transmission connection with the power recovery mechanism, and the number of teeth of the first gear is smaller than that of teeth of the second gear.
6. The turbine power recovery device of claim 5, wherein: the speed reducing mechanism further comprises a transmission shaft, and the driven wheel and the first gear are respectively installed at two ends of the transmission shaft.
7. The turbine power recovery device of claim 1, wherein: the first air inlet of the turbine is used for being communicated with an exhaust gas outlet of an aviation piston engine so that exhaust gas discharged by the aviation piston engine enters the turbine and drives the turbine to rotate.
8. The turbine power recovery device of any one of claims 1 to 7, wherein: the power recovery mechanism is a generator.
9. The turbine power recovery device of claim 8, wherein: the turbine power recovery device further comprises a first-stage compressor, the first-stage compressor is fixed on the turbine shaft and is far away from one end of the turbine, a first-stage compressor impeller is arranged in the first-stage compressor and is driven by the turbine to rotate so as to compress air entering the first-stage compressor, and a first air outlet which is used for allowing air to enter a second air inlet in the first-stage compressor and is communicated with an air inlet of an aviation piston engine is formed in the first-stage compressor.
10. The turbine power recovery device of any one of claims 1 to 7, wherein: the power recovery mechanism is a primary compressor, a primary compressor impeller which is driven by the turbine to rotate so as to compress air entering the primary compressor is arranged in the primary compressor, and a second air inlet used for allowing air to enter the primary compressor and a first air outlet used for being communicated with an air inlet of an aviation piston engine are arranged on the primary compressor.
11. The turbine power recovery device of any one of claims 1 to 7, wherein: the turbine power recovery device further comprises a primary compressor, the primary compressor is fixed at one end, far away from the turbine, of the turbine shaft, a primary compressor impeller driven by the turbine to rotate so as to compress air entering the primary compressor is arranged in the primary compressor, and the primary compressor is provided with a first air outlet and a second air inlet for allowing air to enter the primary compressor;
the power recovery mechanism is a secondary compressor, a secondary compressor impeller which is in transmission connection with the driven wheel and is used for compressing air entering the secondary compressor is arranged in the secondary compressor, and the secondary compressor is provided with a third air inlet communicated with the first air outlet and a second air outlet communicated with an air inlet of the aviation piston engine.
12. The turbine power recovery device of any one of claims 1 to 7, wherein: the number of the power recovery mechanisms is at least two, the number of the driven wheels is the same as that of the power recovery mechanisms, each power recovery mechanism is in transmission connection with the corresponding driven wheel, the number of the driving wheels is one, and one driving wheel is in transmission connection with each driven wheel.
13. The turbine power recovery device of claim 12, wherein: each power recovery mechanism is a generator.
14. The turbine power recovery device of claim 12, wherein: at least one of the power recovery mechanisms is a primary compressor, at least one of the power recovery mechanisms is a secondary compressor,
a first-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the first-stage compressor is arranged in the first-stage compressor, and the first-stage compressor is provided with a first air outlet and a second air inlet for allowing air to enter the first-stage compressor;
and a second-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the second-stage compressor is arranged in the second-stage compressor, and the second-stage compressor is provided with a second air outlet and a third air inlet communicated with the first air outlet.
15. The turbine power recovery device of claim 12, wherein: at least one the power recovery mechanism is the generator, at least one the power recovery mechanism is the primary compressor, be provided with in the primary compressor with correspond from the driving wheel transmission connect in order to carry out the primary compressor impeller that compresses to the air that gets into in the primary compressor, first gas outlet and being used for supplying air entering have been seted up to the primary compressor the second air inlet in the primary compressor.
16. The turbine power recovery device of claim 12, wherein: the turbine power recovery device further comprises a first-stage compressor, the first-stage compressor is fixed at one end, far away from the turbine shaft, of the turbine, a first-stage compressor impeller is arranged in the first-stage compressor, the turbine drives the turbine to rotate so as to compress air entering the first-stage compressor, and a second air inlet and a first air outlet are formed in the first-stage compressor and used for allowing air to enter the first-stage compressor.
17. The turbine power recovery device of claim 16, wherein: each power recovery mechanism is a generator.
18. The turbine power recovery device of claim 16, wherein: at least one of the power recovery mechanisms is a secondary compressor, at least one of the power recovery mechanisms is a tertiary compressor,
a second-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the second-stage compressor is arranged in the second-stage compressor, and the second-stage compressor is provided with a second air outlet and a third air inlet communicated with the first air outlet;
and a third-stage compressor impeller which is in transmission connection with the corresponding driven wheel to compress air entering the third-stage compressor is arranged in the third-stage compressor, and the third-stage compressor is provided with a third air outlet and a fourth air inlet communicated with the second air outlet.
19. The turbine power recovery device of claim 16, wherein: at least one power recovery mechanism is a generator, at least one power recovery mechanism is a secondary compressor, a secondary compressor impeller which is in transmission connection with the corresponding driven wheel and is used for compressing air entering the secondary compressor is arranged in the secondary compressor, and the secondary compressor is provided with a second air outlet and a third air inlet communicated with the first air outlet.
20. Aviation piston engine is provided with turbine power recovery unit, its characterized in that: the turbine power recovery apparatus is the turbine power recovery apparatus of any one of claims 1 to 19.
21. Aviation aircraft, including aviation piston engine, its characterized in that: the aviation piston engine of claim 20.
CN201910565786.4A 2019-06-18 2019-06-27 Turbine power recovery unit, aviation piston engine and aviation aircraft Pending CN112096496A (en)

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CN2019105267897 2019-06-18

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011012861A1 (en) * 2011-03-02 2012-09-06 Voith Patent Gmbh Turbo-compound system, in particular of a motor vehicle
CN102748121A (en) * 2012-06-27 2012-10-24 北京航空航天大学 Two-stage turbocharger for aviation piston engine
US20160017973A1 (en) * 2013-03-06 2016-01-21 Robert Bosch Gmbh Assembly, comprising at least an expansion machine and a gearing
CN106401764A (en) * 2016-11-28 2017-02-15 吉林大学 Automobile engine time-sharing supercharging device
CN107035570A (en) * 2017-03-17 2017-08-11 江苏大学 A kind of centrifugal canister desorption apparatus of exhaust gas turbine and method

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011012861A1 (en) * 2011-03-02 2012-09-06 Voith Patent Gmbh Turbo-compound system, in particular of a motor vehicle
CN102748121A (en) * 2012-06-27 2012-10-24 北京航空航天大学 Two-stage turbocharger for aviation piston engine
US20160017973A1 (en) * 2013-03-06 2016-01-21 Robert Bosch Gmbh Assembly, comprising at least an expansion machine and a gearing
CN106401764A (en) * 2016-11-28 2017-02-15 吉林大学 Automobile engine time-sharing supercharging device
CN107035570A (en) * 2017-03-17 2017-08-11 江苏大学 A kind of centrifugal canister desorption apparatus of exhaust gas turbine and method

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