CN113153568A - Microminiature turboprop engine with novel spray pipe layout - Google Patents
Microminiature turboprop engine with novel spray pipe layout Download PDFInfo
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- CN113153568A CN113153568A CN202110491447.3A CN202110491447A CN113153568A CN 113153568 A CN113153568 A CN 113153568A CN 202110491447 A CN202110491447 A CN 202110491447A CN 113153568 A CN113153568 A CN 113153568A
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- 239000007921 spray Substances 0.000 title abstract description 25
- 238000002485 combustion reaction Methods 0.000 claims description 10
- 239000003638 chemical reducing agent Substances 0.000 claims description 7
- 230000007704 transition Effects 0.000 claims 6
- 238000013461 design Methods 0.000 abstract description 10
- 230000000717 retained effect Effects 0.000 abstract 1
- 238000007789 sealing Methods 0.000 description 5
- 230000002093 peripheral effect Effects 0.000 description 4
- 230000010354 integration Effects 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009434 installation 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
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
Abstract
The invention discloses a microminiature turboprop engine with a novel spray pipe layout, which comprises a core machine, an intermediate casing and an engine low-pressure part, wherein two ends of the intermediate casing are respectively connected with the core machine and the engine low-pressure part, the engine low-pressure part comprises an integrated turboprop, and a culvert spray pipe is arranged on one side, far away from the intermediate casing, of the integrated turboprop. According to the invention, through the combined design of the rear-mounted blade tip propeller and the low-pressure turbine, the normal arrangement of the spray pipe is ensured, and the connotative thrust is retained, and the design also ensures that the connotative exhaust gas cannot flow into the rear-mounted propeller, so that the interference between the high-temperature gas discharged by the spray pipe and the forward inflow air of the propeller is avoided, and the propeller can work normally; through the combined design of the low-pressure turbine and the blade tip propeller, the length of the engine is shortened, the mass of the engine is reduced, and the structural complexity is reduced.
Description
Technical Field
The invention relates to the field of aviation turbine engines, in particular to a microminiature turboprop engine with a novel spray pipe layout.
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 invention patent of publication number CN108518283A proposes a novel micro-miniature turboshaft engine, which adopts the structural layout of a rear output shaft, so that there is no mechanical interference between a core crankshaft and a power turbine shaft, and the design and manufacturing problems of adopting a shaft sleeve shaft on the micro-miniature turboshaft engine are avoided.
However, the main disadvantage of the conventional micro turboprop engine is that the thrust of the tail nozzle is wasted, resulting in a reduction in available power; the adopted free turbine type rear output structure greatly increases the length of the turboprop engine and increases the installation volume and the mass of the turboprop engine; the high-temperature tail gas discharged by the tail spray pipe brings the distortion of the pressure and the temperature of the air inlet of the propeller, and influences the working stability and the performance of the propeller. Therefore, a microminiature turboprop with a novel nozzle layout is provided.
Disclosure of Invention
The purpose of the invention is as follows: the prior art is less related to the technical scheme of the microminiature turboprop engine, and has the following problems: 1. the rear output type culvert spray pipe of the free turbine is difficult to arrange, so that the thrust loss is caused, and the length and the volume of the engine are too long and too large; 2. the shaft sleeve shaft front output structure is difficult to realize in a micro turboprop engine, the technical difficulty and the research and development cost are high; 3. the fixed turbine type microminiature turbine engine has inherent defects and poor performance.
The invention provides a microminiature turboprop engine with a novel spray pipe layout, wherein the spray pipe can be arranged behind a propeller, the connotative thrust is preserved, the interference between high-temperature gas discharged by the spray pipe and the forward flow air of the propeller is avoided, the normal work of the propeller is ensured, the problems in the scheme can be effectively solved, and the microminiature turboprop engine has good remodelling design potential.
The technical purpose of the invention is realized by the following technical scheme:
the utility model provides a microminiature turboprop engine with novel spray tube overall arrangement, includes core machine, intermediary's machine casket, engine low pressure part, intermediary's machine casket both ends are connected with core machine, engine low pressure part respectively, engine low pressure part is including integration turboprop, one side that intermediary's machine casket was kept away from to integration turboprop is provided with the connotation spray tube.
As a still further scheme of the invention: the core machine comprises an engine casing, a combustion chamber is arranged in the engine casing, a rotor shaft is arranged in the combustion chamber, one end of the rotor shaft is fixedly connected with a gas compressor, and one end, far away from the gas compressor, of the rotor shaft is fixedly connected with a turbine.
As a still further scheme of the invention: the integrated turboprop is characterized in that a low-pressure rotor shaft penetrates through the center of the integrated turboprop, the low-pressure rotor shaft is connected to one side, facing the intermediary casing, of the low-pressure rotor shaft in a rotating mode and is connected with a front bearing of the low-pressure rotor shaft, and the low-pressure rotor shaft is connected to one side, facing the connotative nozzle, of the low-pressure rotor shaft in a rotating mode and is connected with a rear bearing of the low-pressure rotor shaft.
As a still further scheme of the invention: the integrated turbine propeller comprises a low-pressure turbine disc, wherein the peripheral surface of the low-pressure turbine disc is fixedly connected with a plurality of low-pressure turbine blades, one end of each low-pressure turbine blade, far away from the low-pressure turbine disc, is fixedly connected with a low-pressure turbine blade shroud, and a plurality of blade tip propellers are uniformly distributed in the peripheral circumferential direction of the low-pressure turbine blade shroud.
As a still further scheme of the invention: the low-pressure rotor air inlet cover is arranged in the intermediate casing, a low-pressure turbine front support plate is arranged between the low-pressure rotor air inlet cover and the inner wall of the intermediate casing, and the inner side and the outer side of the low-pressure turbine front support plate are respectively connected with the low-pressure rotor air inlet cover and the inner wall of the intermediate casing in a sealing mode.
As a still further scheme of the invention: the low-pressure rotor shaft front bearing comprises a low-pressure rotor shaft front bearing and a low-pressure rotor shaft front support rod, wherein the two sides of the low-pressure rotor shaft front bearing are fixedly connected with the low-pressure rotor shaft front support rod, and one end, far away from the low-pressure rotor shaft front bearing, of the low-pressure rotor shaft front support rod is fixedly connected with the inner wall of a low-pressure rotor air inlet cover.
As a still further scheme of the invention: the low-pressure rotor shaft rear bearing is characterized in that two sides of the low-pressure rotor shaft rear bearing are fixedly connected with low-pressure rotor shaft rear supporting rods, and one end, far away from the low-pressure rotor shaft rear bearing, of each low-pressure rotor shaft rear supporting rod is fixedly connected with a low-pressure turbine exhaust cone.
As a still further scheme of the invention: the outer side wall of the low-pressure turbine exhaust cone is fixedly provided with a low-pressure turbine rear supporting plate, and the inner side and the outer side of the low-pressure turbine rear supporting plate are respectively connected with the low-pressure turbine exhaust cone and the inner wall of the culvert spray pipe in a sealing mode.
As a still further scheme of the invention: and the center of the low-pressure turbine disc is connected with the low-pressure rotor shaft in a penetrating way.
As a still further scheme of the invention: and the low-pressure rotor shaft rear bearing and the low-pressure rotor shaft front bearing are symmetrically arranged on two sides of the low-pressure turbine disc.
The invention has the beneficial effects that:
1. by breaking the structural design of a shaft sleeve shaft of the traditional turboprop engine and adopting a mode of separately placing a low-pressure rotor and a high-pressure rotor, namely a turbine and an integrated turboprop, the microminiature turboprop engine has the feasibility of development and good modification design potential;
2. the combined design of the rear-mounted blade tip propeller and the low-pressure turbine ensures that the spray pipe can be normally arranged, so that the connotation thrust is reserved, the design also ensures that the connotation exhaust gas cannot flow into the rear-mounted propeller, and the interference between the high-temperature gas discharged by the spray pipe and the forward inflow air of the propeller is avoided, so that the propeller can normally work;
3. through the combined design of the low-pressure turbine and the blade tip propeller, the length of the engine is shortened, the mass of the engine is reduced, and the structural complexity is reduced.
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 an overall structure of a micro turboprop engine with a novel nozzle layout;
FIG. 2 is a schematic view of a core engine of a micro turboprop engine with a novel nozzle layout;
FIG. 3 is a cross-sectional view of an integrated turboprop with a novel nozzle layout of a micro turboprop engine;
FIG. 4 is a cross-sectional view A of an integrated turboprop with a novel nozzle layout of a micro turboprop engine;
fig. 5 is a sectional view B of an integrated turboprop of a micro turboprop engine having a novel nozzle layout.
In the figure: 1. a core machine; 2. an intermediary case; 3. an integrated turboprop; 4. a culvert spray pipe; 5. a low pressure turbine rear support plate; 6. a low pressure turbine exhaust cone; 7. a low pressure rotor shaft rear bearing; 8. a low pressure rotor shaft rear support bar; 9. a low pressure rotor shaft front support bar; 10. a low pressure turbine front support plate; 11. a low pressure rotor shaft front bearing; 12. a low-pressure rotor shaft; 13. a low pressure rotor inlet shroud; 14. a low-pressure portion of the engine; 15. a compressor; 16. an engine case; 17. a combustion chamber; 18. a rotor shaft; 19. a turbine; 20. a low pressure turbine disk; 21. a low pressure turbine blade; 22. a low pressure turbine shroud; 23. a blade tip propeller.
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.
With reference to fig. 1 and 3, in the existing turboprop engine technology, a tail nozzle is arranged in front of an output structure, resulting in thrust loss and reduction of available work, and meanwhile, high-temperature tail gas discharged by the tail nozzle brings pressure and temperature distortion of air inlet of a propeller, and affects working stability and performance of the propeller. In order to reduce thrust loss and improve power, the invention adopts the arrangement of the core machine 1, the intermediate casing 2 and the low-pressure part 14 of the engine, two ends of the intermediate casing 2 are respectively connected with the core machine 1 and the low-pressure part 14 of the engine, the low-pressure part 14 of the engine comprises an integrated turboprop 3, one side of the integrated turboprop 3, which is far away from the intermediate casing 2, is provided with a culvert spray pipe 4, and the culvert spray pipe 4 is arranged behind the integrated turboprop 3, thereby effectively improving the utilization of gas thrust.
Referring to a schematic structural diagram of a core machine 1 of a micro turboprop engine with a novel spray pipe layout shown in fig. 2, the core machine 1 consists of a gas compressor 15, an engine casing 16, a combustion chamber 17, a rotor shaft 18 and a turbine 19, the core machine can be the part left after a tail spray pipe of a conventional micro turboprop engine is removed, and the core machine 1 is mainly used as a gas generator for providing high-temperature and high-pressure gas working media and belongs to the conventional technology.
Referring to a structural schematic diagram of a low-pressure part 14 of a micro turboprop engine with a novel nozzle layout shown in fig. 3, an end face of one end of an intermediate casing 2 is fixedly connected with a core machine 1, a low-pressure rotor air inlet cover 13 is fixedly connected inside the intermediate casing 2 through a low-pressure turbine front support plate 10, the low-pressure turbine front support plate 10 is of an annular structure, the inner side and the outer side of the low-pressure rotor air inlet cover 13 and the intermediate casing 2 are respectively in sealing connection, the inner wall of the low-pressure rotor air inlet cover 13 is fixedly connected with a low-pressure rotor shaft front bearing 11 through a low-pressure rotor shaft front support rod 9, one side of an integrated turboprop 3 away from the intermediate casing 2 is provided with an inner culvert nozzle 4, the inner wall of the inner culvert nozzle 4 is fixedly connected with a low-pressure turbine exhaust cone 6 through a low-pressure turbine rear support plate 5, the inner wall of the low-pressure turbine exhaust cone 6 is fixedly connected with a low-pressure rotor shaft rear bearing 7 through a low-pressure rotor shaft rear support rod 8, the low-pressure rotor shaft front bearing 11 and the low-pressure rotor shaft rear bearing 7 are symmetrically distributed on two sides of the integrated turboprop 3, and the low-pressure rotor shaft 12 sequentially penetrates through the low-pressure rotor shaft front bearing 11, the integrated turboprop 3 and the low-pressure rotor shaft rear bearing 7.
Referring to fig. 4 and 5, a sectional view of an integrated turboprop 3 of a micro turboprop engine with a novel nozzle layout is shown, the integrated turboprop 3 is composed of a low-pressure turbine disk 20, low-pressure turbine blades 21, a low-pressure turbine blade shroud 22 and a blade tip propeller 23, the blade tip propeller 23 is equidistantly distributed on the outer side of the low-pressure turbine blade shroud 22, the root of the blade tip propeller 23 is fixedly connected with the low-pressure turbine blade shroud 22, the low-pressure turbine blade shroud 22 is of an annular structure, the inner wall of the low-pressure turbine blade shroud 22 is equidistantly connected with a plurality of low-pressure turbine blades 21, one end of each low-pressure turbine blade 21, which is far away from the corresponding low-pressure turbine blade shroud 22, is fixed on the corresponding low-pressure turbine disk 20, the center of the corresponding low-pressure turbine disk 20 is connected with a low-pressure rotor shaft 12 in a penetrating manner, the integrated turboprop 3 can be driven to rotate after a gas working medium impacts the corresponding low-pressure turbine blades 21, the gas working medium is decompressed and expanded by the corresponding inner nozzle 4, the contained thrust is generated, and meanwhile, the rotating blade tip propeller 23 sucks in free inflow air in the front, and the free inflow air is exhausted in an accelerated mode to generate the thrust.
The invention provides a micro turboprop engine with a novel spray pipe layout, which comprises a core machine 1, an intermediate machine case 2 and an engine low-pressure part 14, wherein two ends of the intermediate machine case 2 are respectively connected with the core machine 1 and the engine low-pressure part 14, the engine low-pressure part 14 comprises an integrated turboprop 3, and a culvert spray pipe 4 is arranged on one side, far away from the intermediate machine case 2, of the integrated turboprop 3.
The core machine 1 comprises an engine casing 16, a combustion chamber 17 is arranged inside the engine casing 16, a rotor shaft 18 is arranged inside the combustion chamber 17, one end of the rotor shaft 18 is fixedly connected with a gas compressor 15, and one end, far away from the gas compressor 15, of the rotor shaft 18 is fixedly connected with a turbine 19.
The center of the integrated turboprop 3 is connected with a low-pressure rotor shaft 12 in a penetrating way, one side of the low-pressure rotor shaft 12 facing the intermediary casing 2 is rotatably connected with a low-pressure rotor shaft front bearing 11, and one side of the low-pressure rotor shaft 12 facing the connotative nozzle 4 is rotatably connected with a low-pressure rotor shaft rear bearing 7.
The low-pressure rotor gas inlet cover 13 is arranged inside the intermediary casing 2, a low-pressure turbine front support plate 10 is arranged between the low-pressure rotor gas inlet cover 13 and the inner wall of the intermediary casing 2, and the inner side and the outer side of the low-pressure turbine front support plate 10 are respectively connected with the low-pressure rotor gas inlet cover 13 and the inner wall of the intermediary casing 2 in a sealing mode.
And two sides of the low-pressure rotor shaft front bearing 11 are fixedly connected with low-pressure rotor shaft front supporting rods 9, and one end, far away from the low-pressure rotor shaft front bearing 11, of each low-pressure rotor shaft front supporting rod 9 is fixedly connected with the inner wall of the low-pressure rotor air inlet cover 13.
The low-pressure turbine exhaust cone device is characterized in that two sides of the low-pressure rotor shaft rear bearing 7 are fixedly connected with a low-pressure rotor shaft rear supporting rod 8, and one end of the low-pressure rotor shaft rear supporting rod 8, far away from the low-pressure rotor shaft rear bearing 7, is fixedly connected with a low-pressure turbine exhaust cone 6.
The outer side wall of the low-pressure turbine exhaust cone 6 is fixedly provided with a low-pressure turbine rear supporting plate 5, and the inner side and the outer side of the low-pressure turbine rear supporting plate 5 are respectively connected with the low-pressure turbine exhaust cone 6 and the inner wall of the culvert spray pipe 4 in a sealing mode.
The low pressure turbine disk 20 is connected with the low pressure rotor shaft 12 through the center.
The low-pressure rotor shaft rear bearing 7 and the low-pressure rotor shaft front bearing 11 are symmetrically arranged on two sides of the low-pressure turbine disc 20.
The working principle is as follows:
the core machine 1 sucks in inflow air through an air inlet cone, after the inflow air is compressed by an air compressor 15, the inflow air is combusted, heated and expanded in a combustion chamber 17, gas is compressed by a turbine 19 to generate high-temperature, high-pressure and high-speed gas working media, the gas working media flow into low-pressure turbine blades 21 through a flow channel formed by a low-pressure rotor air inlet cover 13 and a middle machine box 2 to drive the low-pressure turbine blades 21 to rotate, namely, the whole integrated turbine propeller 3 is driven to rotate, and the gas working media are discharged from a culvert jet pipe 4 after being decompressed and expanded by the low-pressure turbine blades 21 to generate culvert thrust; meanwhile, the rotating blade tip propeller 23 sucks in free inflow air in front, and the free inflow air is exhausted in an accelerated manner 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 (7)
1. The utility model provides a need not micro-miniature turboprop of external reduction gear, includes gas generator (1), power output device (2) and screw (3), its characterized in that, power output device (2) inside is provided with multistage free turbine (25), the inside through connection of multistage free turbine (25) has output shaft (26), power output device (2) one end terminal surface and gas generator (1) fixed connection, the one end that gas generator (1) was kept away from in power output device (2) is passed through output shaft (26) and is connected with screw (3).
2. The microminiature turboprop engine without an external speed reducer according to claim 1, wherein the gas generator (1) comprises a core casing (11), a combustion chamber (12) is arranged inside the core casing (11), a turbine shaft (13) is arranged in the center inside the combustion chamber (12), a 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 of the turbine shaft (13) far away from the compressor (14).
3. The microminiature turboprop engine without an external speed reducer according to claim 2, characterized in that the power output device (2) comprises an outer transition casing (21), a transition support plate (22) is fixed on the inner wall of the outer transition casing (21), a multi-stage free turbine (25) is arranged on one side of the transition support plate (22) far away from the turbine (16), a tail nozzle (23) is symmetrically arranged on one side of the multi-stage free turbine (25) far away from the transition support plate (22), and a free turbine casing (24) is arranged on the periphery of the multi-stage free turbine (25).
4. 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).
5. The microminiature turboprop engine without an external speed reducer according to claim 2, characterized in that 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).
6. The microminiature turboprop engine without an external speed reducer according to claim 3, 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.
7. The microminiature turboprop engine without an external speed reducer according to claim 1, characterized in that the multistage free turbine (25) is composed of a plurality of free turbines combined in series.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110491447.3A CN113153568A (en) | 2021-05-06 | 2021-05-06 | Microminiature turboprop engine with novel spray pipe layout |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110491447.3A CN113153568A (en) | 2021-05-06 | 2021-05-06 | Microminiature turboprop engine with novel spray pipe layout |
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| CN113153568A true CN113153568A (en) | 2021-07-23 |
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| CN202110491447.3A Pending CN113153568A (en) | 2021-05-06 | 2021-05-06 | Microminiature turboprop engine with novel spray pipe layout |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108506111A (en) * | 2018-05-04 | 2018-09-07 | 西北工业大学 | A kind of microminiature fanjet |
| CN111706432A (en) * | 2020-05-28 | 2020-09-25 | 中国航发湖南动力机械研究所 | Novel paddle fan engine and propulsion device with same |
| CN113006940A (en) * | 2021-05-06 | 2021-06-22 | 中国航发湖南动力机械研究所 | Micro turboprop engine without external speed reducer |
-
2021
- 2021-05-06 CN CN202110491447.3A patent/CN113153568A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108506111A (en) * | 2018-05-04 | 2018-09-07 | 西北工业大学 | A kind of microminiature fanjet |
| CN111706432A (en) * | 2020-05-28 | 2020-09-25 | 中国航发湖南动力机械研究所 | Novel paddle fan engine and propulsion device with same |
| CN113006940A (en) * | 2021-05-06 | 2021-06-22 | 中国航发湖南动力机械研究所 | Micro turboprop engine without external speed reducer |
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Application publication date: 20210723 |
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