CN113006940B - Micro turboprop engine without external speed reducer - Google Patents
Micro turboprop engine without external speed reducer Download PDFInfo
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- CN113006940B CN113006940B CN202110492140.5A CN202110492140A CN113006940B CN 113006940 B CN113006940 B CN 113006940B CN 202110492140 A CN202110492140 A CN 202110492140A CN 113006940 B CN113006940 B CN 113006940B
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 32
- 230000007704 transition Effects 0.000 claims description 22
- 238000002485 combustion reaction Methods 0.000 claims description 12
- 239000002737 fuel gas Substances 0.000 abstract description 8
- 230000001050 lubricating effect Effects 0.000 abstract description 6
- 238000013461 design Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 20
- 239000000306 component Substances 0.000 description 10
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012549 training Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/20—Adaptations of gas-turbine plants for driving vehicles
- F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses a microminiature turboprop engine without an external speed reducer, which comprises a fuel gas generator, a power output device and a propeller, wherein a multi-stage free turbine is arranged in the power output device, an output shaft penetrates through the interior of the multi-stage free turbine, the end face of one end of the power output device is fixedly connected with the fuel gas generator, and the end, far away from the fuel gas generator, of the power output device is connected with the propeller through the output shaft. The invention adopts the multi-stage free turbine, so that the output shaft can directly drive the propeller to generate thrust, and a speed reducer part is omitted, thereby reducing the quality of an engine, reducing the failure rate of the engine, prolonging the service life of the engine, further omitting accessories such as an independent lubricating system and the like introduced for lubricating the speed reducer, reducing the workload of each stage of turbine by adopting the multi-stage free turbine, reducing the rotating speed of the turbine under the condition of ensuring that the load of the turbine stage is not changed, and greatly simplifying the design of the engine.
Description
Technical Field
The invention belongs to the field of aviation turbine engines, and particularly relates to a microminiature turboprop engine without an external speed reducer.
Background
The turbojet engine is the main power of the contemporary aircraft, and can be mainly divided into four types of turbojet, turbofan, turboshaft and turboprop engines according to the structure, and is mainly used for passenger planes, transport planes, fighters, cruise missiles and the like; the microminiature turbine engine refers to a turbojet engine and a turbofan engine with the thrust of hundreds of kilograms, and a turboshaft engine and a turboprop engine with the power of hundreds of kilowatts. The microminiature turboprop engine is mainly used for platforms such as aeromodelling, cruise bombs, sports planes, training machines and unmanned aerial vehicles, and has the advantages of high propelling efficiency and low oil consumption rate compared with turbojet and turbofan engines. The conventional micro turboprop is mostly obtained by modifying a micro turboprop, because the micro turboprop is small in size, a shaft sleeve shaft front output structure of a large turboprop is difficult to adopt, and a rear output shaft structure is mostly used, because the rotating speed is high, a speed reducer and other devices are mostly adopted for reducing the speed and then are connected with a propeller with low working rotating speed, so that the propeller is driven to generate thrust. Because the turboshaft engine and the turboprop engine have high universality and structural similarity, the common micro turboprop engine can also be used as a micro turboshaft engine through adaptability improvement.
The main disadvantages of the traditional micro turboprop engine are that because the working rotating speed of the power output shaft is not matched with the working rotating speed of the propeller, a speed reducer part needs to be added, the weight of the engine is greatly increased, the output efficiency of the engine is reduced, the available service life of the engine is reduced due to the precision of the speed reducer, and an additional lubricating device needs to be added to lubricate the speed reducer.
The invention patent of publication No. CN108798904A provides a novel microminiature turboprop jet engine, which is formed by modifying a turbojet engine as a core machine instead of a fuel gas generator component in the turboprop jet engine; the gas generator consists of a gas generator component, a power turbine and exhaust component, a speed reducer component and a propeller, wherein the front end of the speed reducer component is connected with the power turbine and the exhaust component, and an output shaft is connected with the propeller.
The power turbine 21, i.e. the single-stage component of the multi-stage free turbine in the present application, still needs an external speed reducer to connect with the propeller, and does not solve the above problems.
Disclosure of Invention
The purpose of the invention is: the traditional microminiature turboprop engine needs to adopt a speed reducer part to enable a power output shaft, namely a free turbine shaft, to be matched with the working rotating speed of a propeller, so that the following problems are brought: 1. the engine size and weight increase; 2. the reliability of the engine is reduced, and the service life is shortened; 3. a complex independent lubricating system is required to be introduced to lubricate the speed reducer; 4. the reduction ratio of the speed reducer is limited, the rotating speed of the propeller is limited, and the propeller cannot be large, so that the promotion of the propelling efficiency and the propelling force is limited.
The micro turboprop engine is different from the traditional micro turboprop engine, the introduction of a speed reducer part is omitted, and the matching of the parts of the engine power output shaft and the propeller rotating speed is achieved.
The technical purpose of the invention is realized by the following technical scheme:
the microminiature turboprop engine without an external speed reducer comprises a fuel gas generator, a power output device and a propeller, wherein a multistage free turbine is arranged in the power output device, an output shaft penetrates through the interior of the multistage free turbine, the end face of one end of the power output device is fixedly connected with the fuel gas generator, and one end, far away from the fuel gas generator, of the power output device is connected with the propeller through the output shaft.
As a still further scheme of the invention: the gas generator comprises a core casing, a combustion chamber is arranged in the core casing, a turbine shaft is arranged in the center of the inner portion of the combustion chamber, a gas compressor penetrates through one end of the turbine shaft, an air inlet cone is fixedly connected to the end face of the turbine shaft, and a turbine is rotatably connected to one end, far away from the gas compressor, of the turbine shaft.
As a still further scheme of the invention: the power output device comprises an outer transition section casing, a transition support plate is fixed on the inner wall of the outer transition section casing, a multi-stage free turbine is arranged on one side, away from the turbine, of the transition support plate, tail spray pipes are symmetrically arranged on one side, away from the transition support plate, of the multi-stage free turbine, and a free turbine casing is arranged on the periphery of the multi-stage free turbine.
As a still further scheme of the invention: the propeller comprises a propeller disc, propeller blades are symmetrically arranged on two sides of the propeller disc, and the propeller disc is fixedly connected with the output shaft.
As a still further scheme of the invention: an igniter is arranged in the combustion chamber and fixed on the inner wall of the core casing.
As a still further scheme of the invention: and two ends of the transition section outer casing are respectively and fixedly connected with the core casing and the free turbine casing.
As a still further scheme of the invention: the multi-stage free turbine is formed by combining a plurality of free turbines in series.
The invention has the beneficial effects that:
1. the invention relates to a method for improving the engine performance, which comprises the steps of leading an output shaft to directly drive a propeller to generate thrust by elaborately designing components, namely adopting a multi-stage free turbine, saving a speed reducer component, reducing the quality of an engine, reducing the failure rate of the engine, prolonging the service life of the engine, saving accessories such as an independent lubricating system and the like introduced for lubricating the speed reducer, ensuring that the stage load is within a certain range due to too large stage load and low turbine efficiency, reducing the workload of each stage of turbine by adopting the multi-stage free turbine, reducing the rotating speed of the turbine under the condition of ensuring that the stage load of the turbine is not changed, and further achieving the purposes of canceling the speed reducer and mechanisms and systems for corresponding lubrication, measurement and monitoring, and greatly simplifying the engine design.
2. The invention can also be used together with a speed reducer, and the size of the propeller can be further improved, so that the propelling efficiency and the propelling force of the engine are further improved, and the oil consumption is reduced.
3. The invention creates a new idea and a new method for developing a turboprop engine.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic view of the overall structure of a micro turboprop engine without an external speed reducer;
fig. 2 is a detailed view of the overall structure of a micro turboprop engine without an external speed reducer.
In the figure:
1. a gas generator; 11. a core case; 12. a combustion chamber; 13. a turbine shaft; 14. a compressor; 15. an air inlet cone; 16. a turbine; 17. an igniter;
2. a power output device; 21. a transition section outer casing; 22. a transition support plate; 23. a tail nozzle; 24. a free turbine case; 25. a multi-stage free turbine; 26. an output shaft;
3. a propeller; 31. a propeller blade; 32. a propeller disc.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the detailed description and specific examples, while indicating the preferred embodiment of the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, an overall structure schematic diagram of a microminiature turboprop engine without an external speed reducer is shown, in the prior art, the turboprop engine is connected with the external speed reducer through a turbine shaft 13 to achieve the purpose that the rotating speed of a propeller 3 is matched with that of the engine, in order to reduce the quality of the engine and reduce the failure rate of the engine, a gas generator 1, a power output device 2 and the propeller 3 are arranged in a segmented mode, one end face of the power output device 2 is attached to the end face of the gas generator 1, and the other end of the power output device is connected with the propeller 3 through an output shaft 26, so that the whole device is more simplified.
Referring to the overall structure detail diagram of a microminiature turboprop engine without an external speed reducer shown in fig. 2, a gas generator 1 mainly comprises a gas compressor 14, a turbine shaft 13, a combustion chamber 12, a turbine 16 and a core casing 11, wherein the turbine shaft 13 penetrates through the gas compressor 14 and the turbine 16 and is fixedly connected with the gas compressor 14 and the turbine 16. The structure is a traditional single-shaft turbojet engine structure, but the structure of the tail nozzle 23 does not exist, jet thrust is not generated, and high-temperature and high-pressure fuel gas is generated.
The power output device 2 mainly comprises a transition section supporting plate, a transition section outer casing 21, a multi-stage free turbine 25, a free turbine shaft 13, a free turbine casing 24 and a tail nozzle 23. The multistage free turbine 25 is a core component of the invention, and the traditional microminiature turboprop engine mostly adopts a one-stage high-load free turbine, so that the free turbine is usually designed to have higher rotating speed and smaller size; the multi-stage large-size free turbine is adopted, the size is increased, the single-stage load is reduced, so that the rotating speed of the free turbine is reduced, the acting capacity of the single-stage free turbine can be achieved through acting superposition of the multi-stage large-size free turbine, the low-speed power output shaft 26 can be directly connected with the propeller 3, the power requirement of the propeller 3 can be guaranteed, the multi-stage free turbine 25 is generally formed in a mode that the center of the 2-5 stage free turbine is penetrated by the free turbine shaft 13, and the multi-stage free turbine and the free turbine are fixedly connected.
The invention provides a microminiature turboprop engine without an external speed reducer, which comprises a gas generator 1, a power output device 2 and a propeller 3, wherein a multi-stage free turbine 25 is arranged in the power output device 2, an output shaft 26 is connected in the multi-stage free turbine 25 in a penetrating manner, the end face of one end of the power output device 2 is fixedly connected with the gas generator 1, and one end of the power output device 2, which is far away from the gas generator 1, is connected with the propeller 3 through the output shaft 26.
The gas generator 1 comprises a core casing 11, a combustion chamber 12 is arranged in the core casing 11, a turbine shaft 13 is arranged in the center of the combustion chamber 12, a gas compressor 14 penetrates through one end of the turbine shaft 13, an air inlet cone 15 is fixedly connected to the end face of the turbine shaft 13, and a turbine 16 is rotatably connected to one end, far away from the gas compressor 14, of the turbine shaft 13.
The power output device 2 comprises an outer transition section casing 21, a transition support plate 22 is fixed on the inner wall of the outer transition section casing 21, a multi-stage free turbine 25 is arranged on one side, away from the turbine 16, of the transition support plate 22, a tail nozzle 23 is symmetrically arranged on one side, away from the transition support plate 22, of the multi-stage free turbine 25, and a free turbine casing 24 is arranged on the periphery of the multi-stage free turbine 25.
The propeller 3 comprises a propeller disc 32, propeller blades 31 are symmetrically arranged on two sides of the propeller disc 32, and the propeller disc 32 is fixedly connected with the output shaft 26.
An igniter 17 is arranged in the combustion chamber 12, and the igniter 17 is fixed on the inner wall of the core case 11.
Two ends of the transition section outer casing 21 are respectively and fixedly connected with the core casing 11 and the free turbine casing 24.
The multi-stage free turbine 25 is formed by combining a plurality of free turbines in series.
The working principle is as follows: air flows into the compressor 14 through the air inlet cone 15, is compressed, enters the combustion chamber 12 after being compressed in the compressor 14, is combusted, and is expanded by the turbine 16 to do work, so that the high-temperature and high-pressure gas is converted, wherein the expansion work absorbed by the turbine 16 is mainly used for driving the compressor 14 to do work through the turbine shaft 13. The high-temperature and high-pressure gas is guided to flow into the multistage free turbine 25 through the streamline convergent channel to drive the multistage free turbine 25 to rotate, so that power is generated, the multistage free turbine 25 is composed of multistage turbines with large sizes and low loads, the rotating speed of the multistage free turbine 25 is low and is 30-60% of that of a free turbine of a traditional microminiature turboprop engine, the power is transmitted to the propeller 3 through the output shaft 26, and the propeller 3 can be directly connected with the output shaft 26 to absorb the power transmitted by the multistage free turbine 25 due to the fact that the rotating speed of the multistage free turbine 25 is low, and rotates at the same rotating speed as the multistage free turbine 25 to generate thrust.
The foregoing is merely exemplary and illustrative of the present invention and various modifications, additions and substitutions may be made by those skilled in the art to the specific embodiments described without departing from the scope of the invention as defined in the following claims.
Claims (4)
1. A microminiature turboprop engine without an external speed reducer comprises a gas generator (1), a power output device (2) and a propeller (3), and is characterized in that a multi-stage free turbine (25) is arranged inside the power output device (2), an output shaft (26) penetrates through the inside of the multi-stage free turbine (25), the end face of one end of the power output device (2) is fixedly connected with the gas generator (1), and one end, far away from the gas generator (1), of the power output device (2) is connected with the propeller (3) through the output shaft (26);
the gas generator (1) comprises a core casing (11), a combustion chamber (12) is arranged in the core casing (11), a turbine shaft (13) is arranged in the center of the combustion chamber (12), a gas compressor (14) penetrates through one end of the turbine shaft (13), an air inlet cone (15) is fixedly connected to the end face of the turbine shaft (13), and a turbine (16) is rotatably connected to one end, far away from the gas compressor (14), of the turbine shaft (13);
the power output device (2) comprises a transition section outer casing (21), a transition support plate (22) is fixed on the inner wall of the transition section outer casing (21), a multi-stage free turbine (25) is arranged on one side, far away from the turbine (16), of the transition support plate (22), tail nozzles (23) are symmetrically arranged on one side, far away from the transition support plate (22), of the multi-stage free turbine (25), and a free turbine casing (24) is arranged on the periphery of the multi-stage free turbine (25);
the multi-stage free turbine (25) is formed by combining a plurality of free turbines in series;
the multi-stage free turbine (25) consists of a plurality of stages of turbines with large size and low load, and the rotating speed of the turbines is slow;
the propeller (3) can absorb the power transmitted by the multi-stage free turbine (25) through being directly connected with the output shaft (26), and rotate at the same rotating speed as the multi-stage free turbine (25) so as to generate thrust.
2. The microminiature turboprop without an external speed reducer according to claim 1, characterized in that the propeller (3) includes a propeller disc (32), the propeller disc (32) is bilaterally symmetrically provided with propeller blades (31), and the propeller disc (32) is fixedly connected with the output shaft (26).
3. The micro turboprop engine without an external speed reducer according to claim 1, wherein an igniter (17) is provided inside the combustion chamber (12), and the igniter (17) is fixed to an inner wall of the core casing (11).
4. The microminiature turboprop engine without an external speed reducer, according to claim 1, characterized in that both ends of the transition section outer casing (21) are fixedly connected with the core casing (11) and the free turbine casing (24), respectively.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110492140.5A CN113006940B (en) | 2021-05-06 | 2021-05-06 | Micro turboprop engine without external speed reducer |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110492140.5A CN113006940B (en) | 2021-05-06 | 2021-05-06 | Micro turboprop engine without external speed reducer |
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| Publication Number | Publication Date |
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| CN113006940A CN113006940A (en) | 2021-06-22 |
| CN113006940B true CN113006940B (en) | 2022-03-29 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113153568A (en) * | 2021-05-06 | 2021-07-23 | 中国航发湖南动力机械研究所 | Microminiature turboprop engine with novel spray pipe layout |
| CN113847146B (en) * | 2021-08-30 | 2022-08-30 | 四川航天中天动力装备有限责任公司 | Shaft power output unit body based on pneumatic and structural matching design |
Citations (5)
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|---|---|---|---|---|
| CN101429892A (en) * | 2007-11-07 | 2009-05-13 | 涡轮梅坎公司 | Turboshaft engine including means for heating the air entering the power turbine |
| CN101652535A (en) * | 2007-04-06 | 2010-02-17 | 涡轮梅坎公司 | The auxiliary device that is used for instantaneous acceleration and decelerating phase |
| CN103375265A (en) * | 2012-04-26 | 2013-10-30 | 李吉光 | Turboshaft engine and use method thereof |
| CN205554565U (en) * | 2016-02-29 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN112696269A (en) * | 2020-11-18 | 2021-04-23 | 靳普 | Multi-rotor micro gas turbine and starting method thereof |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10604268B2 (en) * | 2017-02-22 | 2020-03-31 | Pratt & Whitney Canada Corp. | Autothrottle control for turboprop engines |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101652535A (en) * | 2007-04-06 | 2010-02-17 | 涡轮梅坎公司 | The auxiliary device that is used for instantaneous acceleration and decelerating phase |
| CN101429892A (en) * | 2007-11-07 | 2009-05-13 | 涡轮梅坎公司 | Turboshaft engine including means for heating the air entering the power turbine |
| CN103375265A (en) * | 2012-04-26 | 2013-10-30 | 李吉光 | Turboshaft engine and use method thereof |
| CN205554565U (en) * | 2016-02-29 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Screw, power component and aircraft |
| CN112696269A (en) * | 2020-11-18 | 2021-04-23 | 靳普 | Multi-rotor micro gas turbine and starting method thereof |
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