CN111348196B - Air-entraining combustion distributed power aeroengine of tiltrotor aircraft - Google Patents
Air-entraining combustion distributed power aeroengine of tiltrotor aircraft Download PDFInfo
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- CN111348196B CN111348196B CN201911163310.4A CN201911163310A CN111348196B CN 111348196 B CN111348196 B CN 111348196B CN 201911163310 A CN201911163310 A CN 201911163310A CN 111348196 B CN111348196 B CN 111348196B
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- engine
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 18
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 7
- 230000010354 integration Effects 0.000 claims description 4
- 238000009434 installation Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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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
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention discloses an air-entraining combustion distributed power aeroengine of a tiltrotor, which comprises a fuselage, tail wings, landing gear, a tilting structure, a tilting main shaft, tilting wings, a rotor wing and a main engine, wherein the tail wings are fixedly arranged at the rear end of the fuselage, the landing gear is fixedly arranged at the rear part of the lower end of the fuselage, the tilting structure in the horizontal direction is fixedly arranged at the left end and the right end of the middle part of the fuselage, one end of the tilting structure far away from the fuselage is rotationally connected with the tilting main shaft in the horizontal direction, one end of the tilting main shaft far away from the tilting structure is rotationally connected with the tilting wings in the horizontal direction, the front end of the tilting wings is rotationally connected with the rotor wing in the horizontal direction, and the main engine in the horizontal direction is fixedly arranged at the inner side of the middle part of the fuselage.
Description
Technical Field
The invention relates to a bleed air combustion distributed power aeroengine of a tiltrotor aircraft.
Background
The tiltrotor aircraft is a novel aircraft integrating a fixed-wing aircraft and a helicopter, and has the capability of vertical take-off, landing and hovering of a common helicopter and the capability of high-speed cruising flight of a turboprop. Tiltrotor aircraft is a unique performance rotorcraft. The aircraft is characterized in that a rotor tilting system assembly capable of rotating between a horizontal position and a vertical position is respectively arranged at two wing tips of a wing of a similar fixed-wing aircraft, when the aircraft vertically takes off and lands, a rotor shaft is vertical to the ground, is in a horizontal helicopter flight state, and can hover in the air, fly forwards and backwards and fly sideways. Due to the special demands of tiltrotor power, there are currently some limitations to power.
Disclosure of Invention
The invention aims to provide a bleed air combustion distributed power aeroengine of a tiltrotor aircraft, so as to solve the technical problems.
The invention adopts the following technical scheme for realizing the purposes:
The utility model provides a distributed power aeroengine of bleed air burning of gyroplane, includes fuselage, fin, undercarriage, tilting structure, tilting main shaft, tilting wing, rotor, main engine high pressure compressor, wing support integration pipeline structure, auxiliary engine axis of rotation, the fin is fixed with in the installation of fuselage rear end, the undercarriage is fixed with in installation of fuselage lower extreme rear portion, the tilting structure of horizontal direction is fixed with in both ends installation about the fuselage middle part, tilting structure keeps away from the one end of fuselage and rotates and be connected with tilting main shaft of horizontal direction, tilting main shaft keeps away from tilting structure's one end and rotates and be connected with tilting main wing of horizontal direction, tilting main wing front end rotates and is connected with the rotor of horizontal direction, the inboard fixed mounting in fuselage middle part has the main engine of horizontal direction, main engine front end is connected with the main engine high pressure compressor of horizontal direction, both ends fixedly connected with horizontal direction's wing support integration pipeline structure about the fuselage upper portion, wing support integration pipeline structure keeps away from one end of main engine and auxiliary engine axis of rotation, auxiliary engine front end and auxiliary engine front end are connected with auxiliary engine axis of rotation, auxiliary engine front end is kept away from fixedly connected with the auxiliary engine axis of rotation.
On the basis of the technical scheme, the front part of the inner side of the machine body is provided with the flight control system.
On the basis of the technical scheme, the auxiliary engine comprises an auxiliary engine backflow combustion chamber and an auxiliary engine power vortex, and the rear end of the auxiliary engine backflow combustion chamber is fixedly connected with the auxiliary engine power vortex in the horizontal direction.
On the basis of the technical scheme, the flight control system is connected with the main engine through a control wire.
The main engine is a conventional high pressure ratio turbine engine.
Compared with the prior art, the invention has the following advantages: the main engine bears most of the weight of the power system, while the auxiliary engines distributed are light in weight, but high in thrust/power, and the total pressure loss of bleed air transmission is controllable because the bleed air pressure is high, the density is high, the flow speed of the bleed air is relatively slow and the Mach number of the bleed air is smaller than that of the conventional turbofan engine. Because the auxiliary engine is not provided with the high-low pressure compressor, the related casing and the supporting mechanism, part of weight can be reduced; meanwhile, a guide device, a rotor and a matched casing in a high-pressure turbine and a low-pressure turbine of the engine are omitted, and the weight of the engine is reduced. At the same output power, the gas flow of the auxiliary engine is reduced by a large part compared with that of the conventional engine, and the weight of a combustion chamber of the auxiliary engine is also greatly reduced; although the number of stages of the power turbine is increased as compared with the original power turbine, the weight increase of the power turbine is limited due to the decrease of the gas flow. Therefore, under the same power/thrust, the auxiliary engine can reduce a large amount of weight, and by matching the power distribution and the weight distribution among the power, the efficient pneumatic flying integrated layout is realized, and the lift-drag ratio of the aircraft is improved. For the tilting rotor aircraft, the wing span of the aircraft is increased, so that the lift-drag ratio of the plane is increased, and the power distribution of the engines at the two sides of the main engine and the wing tip and the distributed driving of the propellers or fans are realized, so that the proper large bypass ratio is realized, and the propulsion efficiency of a power system is improved.
Drawings
Fig. 1 is a schematic view of a tiltrotor aircraft equipped with bleed air combustion distributed power according to the present invention in a first flight configuration.
Figure 2 is a schematic view of a second flight condition of the tiltrotor aircraft equipped with bleed air combustion distributed power according to the present invention.
In the figure: 1. fuselage, 2, fin, 3, undercarriage, 4, tilting structure, 5, tilting main shaft, 6, tilting wing, 7, rotor, 8, main engine, 9, main engine high-pressure compressor, 10, wing support integrated pipeline structure, 11, auxiliary engine, 12, auxiliary engine axis of rotation, 13, flight control system, 14, auxiliary engine backflow combustion chamber, 15, auxiliary engine power swirl.
Detailed Description
The invention is described in further detail below with reference to the drawings and the specific examples.
As shown in fig. 1-2, a bleed air combustion distributed power aeroengine of a tiltrotor aircraft comprises a fuselage 1, a tail wing 2, a landing gear 3, a tilting structure 4, a tilting main shaft 5, tilting wings 6, a rotor 7, a main engine 8, a main engine high-pressure compressor 9, a wing support integrated pipeline structure 10, an auxiliary engine 11 and an auxiliary engine rotating shaft 12, and is characterized in that: the utility model discloses a helicopter is characterized by comprising a fuselage 1, a fuselage 2 is fixedly installed at the rear end of the fuselage 1, a landing gear 3 is fixedly installed at the rear end of the lower end of the fuselage 1, a tilting structure 4 with the horizontal direction is fixedly installed at the left and right ends of the middle part of the fuselage 1, one end of the tilting structure 4, which is far away from the fuselage 1, is rotationally connected with a tilting main shaft 5 with the horizontal direction, one end of the tilting main shaft 5, which is far away from the tilting structure 4, is rotationally connected with a tilting wing 6 with the horizontal direction, the front end of the tilting wing 6 is rotationally connected with a rotor 7 with the horizontal direction, a main engine 8 with the horizontal direction is fixedly installed at the inner side of the middle part of the fuselage 1, a main engine high-pressure compressor 9 with the horizontal direction is connected with the front end of the main engine 8, a wing supporting integrated pipeline structure 10 with the horizontal direction is fixedly connected with the left and right ends of the upper part of the main engine 8, one end of the wing supporting integrated pipeline structure 10, which is far away from the main engine 8 is connected with an auxiliary engine 11, the front end of the auxiliary engine 11 is connected with an auxiliary engine rotating shaft 12 with the horizontal direction, and one end of the auxiliary engine rotating shaft 12, which is far away from the auxiliary engine 11 is fixedly connected with the inner part 7 with the auxiliary engine.
The front inside of the fuselage 1 is provided with an aircraft control system 13.
The auxiliary engine 11 is composed of an auxiliary engine return combustion chamber 14 and an auxiliary engine power vortex 15, and the rear end of the auxiliary engine return combustion chamber 14 is fixedly connected with the auxiliary engine power vortex 15 in the horizontal direction.
The flight control system 13 is connected with the main engine 8 through control wires.
The main engine 8 is a conventional high pressure ratio turbine engine.
The working principle of the invention is as follows: when flying, the main engine is controlled to start by the flight control system, and the main engine is used for carrying out rear bleed air from the high-pressure compressor and is transmitted to the auxiliary engine through a pipeline integrally designed with the wing supporting structure. The auxiliary engine drives the fan or the propeller to generate propelling force through the transmission shaft, when the aircraft vertically takes off and lands, the rotor shaft is perpendicular to the ground, is in a horizontal helicopter flight state, can hover in the air, fly back and forth and fly sideways, and when the aircraft runs in the air, the rotor shaft is parallel to the ground, and the running purpose is realized through rotor rotation.
The foregoing is a preferred embodiment of the present invention, and it will be apparent to those skilled in the art from this disclosure that changes, modifications, substitutions and alterations can be made without departing from the principles and spirit of the invention.
Claims (3)
1. The utility model provides a distributed power aeroengine of bleed air burning of gyroplane that verts, includes fuselage (1), fin (2), undercarriage (3), tilting structure (4), main shaft (5) that verts, tilting wing (6), rotor (7), main engine (8), main engine high pressure compressor (9), wing support integration pipeline structure (10), auxiliary engine (11), auxiliary engine axis of rotation (12), its characterized in that: the utility model discloses a helicopter is characterized in that an empennage (2) is fixedly arranged at the rear end of a fuselage (1), a landing gear (3) is fixedly arranged at the rear end of the lower end of the fuselage (1), a tilting structure (4) in the horizontal direction is fixedly arranged at the left and right ends of the middle part of the fuselage (1), a tilting main shaft (5) in the horizontal direction is rotationally connected with one end of the tilting structure (4) far away from the tilting structure (4), a tilting wing (6) in the horizontal direction is rotationally connected with one end of the tilting main shaft (5) far away from the tilting structure (4), a rotor (7) in the horizontal direction is rotationally connected with the front end of the tilting wing (6), a main engine (8) in the horizontal direction is fixedly arranged at the inner side of the middle part of the fuselage (1), a main engine high-pressure air compressor (9) in the horizontal direction is fixedly connected with the front end of the main engine (8), a wing support integrated pipeline structure (10) in the horizontal direction is fixedly connected with the left and right ends of the upper part of the main engine (8), one end of the wing support integrated pipeline structure (10) far away from the main engine (8) is connected with an auxiliary engine (11), the auxiliary engine (11) in the horizontal direction is fixedly connected with the auxiliary engine (12) in the front end of the main engine (11), the engine is characterized in that a flight control system (13) is arranged at the front part of the inner side of the engine body (1), the auxiliary engine (11) comprises an auxiliary engine backflow combustion chamber (14) and an auxiliary engine power vortex (15), and the rear end of the auxiliary engine backflow combustion chamber (14) is connected with the auxiliary engine power vortex (15) in the horizontal direction.
2. A tiltrotor aircraft bleed air combustion distributed power aircraft engine according to claim 1, wherein: the flight control system (13) is connected with the main engine (8) through a control wire.
3. A tiltrotor aircraft bleed air combustion distributed power aircraft engine according to claim 1, wherein: the main engine (8) is a conventional high pressure ratio turbine engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911163310.4A CN111348196B (en) | 2019-11-25 | 2019-11-25 | Air-entraining combustion distributed power aeroengine of tiltrotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911163310.4A CN111348196B (en) | 2019-11-25 | 2019-11-25 | Air-entraining combustion distributed power aeroengine of tiltrotor aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111348196A CN111348196A (en) | 2020-06-30 |
| CN111348196B true CN111348196B (en) | 2024-09-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911163310.4A Active CN111348196B (en) | 2019-11-25 | 2019-11-25 | Air-entraining combustion distributed power aeroengine of tiltrotor aircraft |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572407B (en) * | 2022-03-10 | 2023-12-29 | 中国航空发动机研究院 | Distributed variable-cycle engine and aircraft |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN211592935U (en) * | 2019-11-25 | 2020-09-29 | 西安空天能源动力智能制造研究院有限公司 | Air-entraining combustion distributed power aero-engine of tilt rotor aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9376206B2 (en) * | 2013-03-12 | 2016-06-28 | Bell Helicopter Textron Inc. | Tiltrotor aircraft with inboard wing mounted fixed engine arrangement |
| CN103786881A (en) * | 2014-02-28 | 2014-05-14 | 武汉蓝天翔航空科技有限公司 | Tilting rotor wing helicopter |
| CN108082466A (en) * | 2017-11-23 | 2018-05-29 | 北京航空航天大学 | A kind of tilting duct connection wing layout vertically taking off and landing flyer |
| US10906656B2 (en) * | 2018-05-01 | 2021-02-02 | Bell Textron Inc. | Hybrid tiltrotor drive system |
| CN110316370B (en) * | 2019-06-25 | 2021-07-06 | 北京航空航天大学 | Layout and control method of distributed power tilting wing aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN211592935U (en) * | 2019-11-25 | 2020-09-29 | 西安空天能源动力智能制造研究院有限公司 | Air-entraining combustion distributed power aero-engine of tilt rotor aircraft |
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| CN111348196A (en) | 2020-06-30 |
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