CN112360645A - Tandem turbine/double-mode stamping combined engine mode conversion device - Google Patents
Tandem turbine/double-mode stamping combined engine mode conversion device Download PDFInfo
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- CN112360645A CN112360645A CN202011250157.1A CN202011250157A CN112360645A CN 112360645 A CN112360645 A CN 112360645A CN 202011250157 A CN202011250157 A CN 202011250157A CN 112360645 A CN112360645 A CN 112360645A
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- 238000006243 chemical reaction Methods 0.000 title claims abstract description 31
- 230000002902 bimodal effect Effects 0.000 claims abstract description 47
- 238000005192 partition Methods 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims description 15
- 230000009977 dual effect Effects 0.000 claims description 7
- 230000006835 compression Effects 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 6
- 230000007246 mechanism Effects 0.000 claims description 5
- 230000007423 decrease Effects 0.000 claims description 3
- 230000009466 transformation Effects 0.000 abstract description 5
- 230000008602 contraction Effects 0.000 abstract description 2
- 230000009347 mechanical transmission Effects 0.000 abstract description 2
- 230000008569 process Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
The invention relates to a tandem type turbine/bimodal ramjet combination engine modal conversion device, and belongs to the technical field of turbine/bimodal ramjet combination engines. The invention provides a tandem turbine/bimodal ramjet combination engine modal conversion device which adopts a threaded rod mechanical transmission to adjust the position of an air inlet cone device, and during modal conversion, inflow air is distributed according to a flow continuous criterion through the forward and backward movement of the adjustable air inlet cone device and the expansion and contraction of a partition plate, so that the high/low speed channel of a combination engine is controlled to work. The mode conversion of the series turbine/dual-mode stamping combined engine is realized by a simpler mechanical structure, and the continuous and stable power output of the engine under the wide-range working condition of Ma0-7 is ensured. The invention can effectively reduce the realization difficulty of the modal transformation and reduce the number of components of the modal transformation system.
Description
Technical Field
The invention belongs to the technical field of turbine/bimodal ramjet combined engines, and particularly relates to a tandem type turbine/bimodal ramjet combined engine modal conversion device.
Background
The turbine/bimodal ramjet combined engine can be used as an ideal power device of an aerospace plane, can be reused within the range of Ma0-7 and the height of 0-30km, is a new research direction of an aero-engine, works in a low-speed channel below Ma2, and generates thrust by entering incoming air into a gas compressor through an air inlet channel and organizing and burning through a combustion chamber of the turbine engine; after the air is accelerated to Ma2, mode conversion is needed, the flowing air is guided into a high-speed channel and is compressed into a combustion chamber of the dual-mode ramjet engine through the high-speed channel to be combusted, and thrust is generated. The turbine/bimodal ramjet combined engine integrates the advantages of zero-speed starting of the turbine engine and high-altitude high-speed working of the bimodal ramjet engine, and avoids the defects that the turbine engine cannot work at high altitude and high speed and the bimodal ramjet engine cannot be started automatically, so that the turbine/bimodal ramjet combined engine is the core research direction of a new generation of high-speed airplane power device. The turbine/double-mode stamping combined engine is divided into a parallel type and a series type. The engine with the series layout has a compact structure, but the mode conversion process is more complex compared with the mode conversion process with the parallel layout, which is a technical difficulty of the application of the engine.
When the serial turbine/dual-mode ramjet combined engine performs mode conversion, the air inlet channel needs to simultaneously supply air flow to the turbine engine and the ramjet engine, the mode conversion is completed by matching with the engine, the continuous change of the flow and the smooth change of the thrust of the engine need to be ensured, the opening degree of the mode conversion device needs to be adjusted, and the flow passage area needs to be continuously adjusted during the movement of the mode conversion device.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: how to design a mode conversion scheme of the serial turbine/dual-mode stamping combined engine can effectively reduce the structural complexity and the realization difficulty of a mode conversion device.
(II) technical scheme
In order to solve the above technical problem, the present invention provides a tandem turbine/dual-mode ramjet combined engine mode conversion device, comprising: the adjustable partition plate device 3, the adjustable air inlet cone device 4 and the adjustable air inlet cone device equipment cabin 7;
the adjustable air inlet cone device 4 comprises a high-speed channel pre-compression surface 5, an adjustable air inlet cone 6 and an adjustable air inlet cone threaded rod 8;
the adjustable clapboard device 3 is of a cylindrical structure and is positioned in a low-speed turbine channel 1 of the turbine/bimodal ramjet combined engine, namely the turbine engine channel;
the high-speed channel precompression surface 5 is connected with the adjustable inlet cone 6, the adjustable inlet cone 6 is a movable part and is in surface contact with an adjustable inlet cone device cabin 7, the adjustable inlet cone device cabin 7 is a fixed part, one end of an adjustable inlet cone threaded rod 8 is positioned in the adjustable inlet cone 6, and the other end of the adjustable inlet cone threaded rod is screwed into the adjustable inlet cone device cabin 7; the adjustable air inlet cone device cabin 7 is powered by an air inlet cone moving power device, and then drives the adjustable air inlet cone threaded rod 8 to rotate forwards or reversely, so that the high-speed channel pre-compression surface 5 and the adjustable air inlet cone 6 are driven to move forwards or backwards together, and the adjustable air inlet cone device 4 is driven to move forwards or backwards; the adjustable air inlet cone device cabin 7 is fixed on the inner surface of the low-speed turbine channel 1 of the turbine/bimodal ramjet combined engine;
when the aircraft flies below Ma2, the adjustable inlet cone device 4 can extend backwards to be in contact with the adjustable inlet cone device equipment cabin 7, and the adjustable partition plate device 3 can extend forwards to block the inlet of the high-speed stamping channel 2 of the turbine/dual-mode stamping combined engine, wherein the two devices are in line contact;
when the aircraft accelerates to a position above Ma2, the adjustable air inlet cone device 4 can extend forwards to block the inlet of the low-speed turbine channel 1 of the turbine/bimodal ramjet combined engine, and the two are in line contact;
preferably, the inner surface of the low-speed turbine channel 1 of the turbine/bimodal ramjet combination engine is provided with a limiting device for fixing the position of the adjustable air inlet cone device 4.
Preferably, the adjustable air cone assembly 4 slidably controls the dual path air flow, and is of an arcuate design.
Preferably, the adjustable diaphragm device 3 has a hydraulic actuating mechanism as a power device to control the opening degree of the low-speed turbine channel 1 of the turbine/dual-mode ramjet combined engine.
The invention also provides a working method of the device, which is realized based on the following principle:
the high-speed stamping channel 2 of the turbine/bimodal stamping combined engine does not work in a low-speed state, an adjustable clapboard device 3 is adopted to seal the inlet of the channel 2 of the stamping engine, the aircraft only depends on the low-speed turbine channel 1 of the turbine/bimodal stamping combined engine to provide thrust, an adjustable air inlet cone device 4 for controlling the air flow of two channels is positioned at the rearmost end, the opening degree of the low-speed turbine channel 1 of the turbine/bimodal stamping combined engine is fully opened, a power device hydraulic actuating mechanism of the adjustable clapboard device 3 controls the opening degree of the low-speed turbine channel 1 of the turbine/bimodal stamping combined engine, and the switching control of the channel 1 of the turbine engine is realized.
Preferably, in the method, the method is further implemented based on the following principle: when the mode is converted, the adjustable clapboard device 3 is completely opened, the flow of the double channels is only controlled by the adjustable air inlet cone device 4, the adjustable air inlet cone device 4 moves forwards, the air flow of the low-speed turbine channel 1 of the turbine/dual-mode ramjet combined engine continuously decreases, the turbine engine changes the working state and is switched from a slow-turning state to a windmill state, the flow loss increases at the moment of conversion, the thrust is suddenly reduced, the adjustable air inlet cone device 4 further moves forwards, the air flow of the high-speed ramjet channel 2 of the turbine/dual-mode ramjet combined engine increases, the thrust is recovered until the mode conversion is completed, and the power of the aircraft is provided by the ramjet engine.
Preferably, in the method, when the aircraft flies below Ma2, the low-speed turbine channel 1 of the turbine/dual-mode ram combined engine is opened, air enters the combustor of the turbine engine from the low-speed turbine channel 1 of the turbine/dual-mode ram combined engine, and the high-speed ram channel 2 of the turbine/dual-mode ram combined engine is closed. At the moment, the adjustable clapboard device 3 is in an extending state and extends forwards to block the inlet of the high-speed stamping channel 2 of the turbine/bimodal stamping combined engine, and the adjustable clapboard device and the high-speed stamping channel 2 are in line contact, so that airflow is prevented from entering the high-speed stamping channel 2 of the turbine/bimodal stamping combined engine, and the flow coefficient of an air inlet channel of a low-speed turbine engine is ensured.
Preferably, when the aircraft accelerates to above Ma2, the low-speed turbine engine is required to be driven from a slow vehicle to a windmill, the high-speed dual-mode ramjet engine is ignited to work, at the moment, the adjustable partition plate device 3 is retracted, the high-speed ram channel 2 of the turbine/dual-mode ramjet combined engine is opened, and the adjustable air inlet cone device 4 moves forwards until the adjustable air inlet cone device 4 is in contact with the inner wall surface of the low-speed turbine channel 1 of the turbine/dual-mode ramjet combined engine, so that the limiting device is triggered. At the moment, the adjustable air inlet cone device 4 seals the low-speed turbine channel 1 of the turbine/dual-mode ramjet combined engine, all air flows into the high-speed ramjet channel 2 of the turbine/dual-mode ramjet combined engine, the dual-mode ramjet engine is ignited, the turbine engine is flamed out, and mode conversion is completed.
The invention further provides an application of the device in a turbine/bimodal ramjet combined engine.
The invention also provides an application of the device in a power device of an aerospace plane.
(III) advantageous effects
The invention provides a tandem turbine/bimodal ramjet combination engine modal conversion device which adopts a threaded rod mechanical transmission to adjust the position of an air inlet cone device, and during modal conversion, inflow air is distributed according to a flow continuous criterion through the forward and backward movement of the adjustable air inlet cone device and the expansion and contraction of a partition plate, so that the high/low speed channel of a combination engine is controlled to work. The mode conversion of the series turbine/dual-mode stamping combined engine is realized by a simpler mechanical structure, and the continuous and stable power output of the engine under the wide-range working condition of Ma0-7 is ensured. The invention can effectively reduce the realization difficulty of the modal transformation and reduce the number of components of the modal transformation system.
Drawings
FIG. 1 is a schematic illustration of a series turbine/dual mode ramjet combination engine employing the apparatus of the present invention;
FIG. 2 is a schematic diagram of a tandem turbine/dual mode ramjet combination mode conversion device of the present invention;
fig. 3 is a schematic diagram of an adjustable air inlet cone device as a moving structure and an equipment compartment of the adjustable air inlet cone device in the invention.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
As shown in fig. 2 and fig. 3, the tandem turbine/dual-mode ramjet combined engine modal transformation provided by the invention comprises an adjustable partition plate device 3, an adjustable inlet cone device 4 and an adjustable inlet cone device equipment cabin 7;
the adjustable air inlet cone device 4 comprises a high-speed channel pre-compression surface 5, an adjustable air inlet cone 6 and an adjustable air inlet cone threaded rod 8;
the adjustable clapboard device 3 is of a cylindrical structure and is positioned in a low-speed turbine channel 1 (namely a turbine engine channel) of the turbine/bimodal ramjet combined engine;
the high-speed channel precompression surface 5 is connected with the adjustable inlet cone 6, the adjustable inlet cone 6 is a movable part and is in surface contact with an adjustable inlet cone device cabin 7, the adjustable inlet cone device cabin 7 is a fixed part, one end of an adjustable inlet cone threaded rod 8 is positioned in the adjustable inlet cone 6, and the other end of the adjustable inlet cone threaded rod is screwed into the adjustable inlet cone device cabin 7; the adjustable air inlet cone device cabin 7 is powered by an air inlet cone moving power device, and then drives the adjustable air inlet cone threaded rod 8 to rotate forwards or reversely, so that the high-speed channel pre-compression surface 5 and the adjustable air inlet cone 6 are driven to move forwards or backwards together, and the adjustable air inlet cone device 4 is driven to move forwards or backwards;
the inner surface of the low-speed turbine channel 1 of the turbine/bimodal ramjet combined engine is provided with a limiting device for fixing the position of the adjustable air inlet cone device 4. The adjustable air inlet cone device 4 and the low-speed channel flow control device formed by the adjustable air inlet cone device cabin 7 are designed in a two-stage mode, the adjustable air inlet cone device 4 at the front section can control the air flow of double channels in a sliding mode, an arc design is adopted, the adjustable air inlet cone device cabin 7 at the rear section has two functions of a high-speed channel precompression surface and a closed low-speed channel, the inner surface of the low-speed turbine channel 1 of the turbine/bimodal ramjet combined engine is fixed to the adjustable air inlet cone device cabin 7 at the rear section, and an adjustable air inlet cone threaded rod 8 in the adjustable air inlet cone device 4 at the front section is nested in the adjustable air inlet. The device uses adjustable air inlet cone threaded rod 8, which is exposed in a low-speed channel, has low requirement on thermal protection, and has simple and reliable mechanical structure and easy realization.
When the aircraft flies below Ma2, the adjustable inlet cone device 4 can extend backwards to be in contact with the adjustable inlet cone device equipment cabin 7, and the adjustable partition plate device 3 can extend forwards to block the inlet of the high-speed stamping channel 2 of the turbine/dual-mode stamping combined engine, wherein the two devices are in line contact;
when the aircraft accelerates to a position above Ma2, the adjustable air inlet cone device 4 can extend forwards to block the inlet of the low-speed turbine channel 1 of the turbine/bimodal ramjet combined engine, and the two are in line contact;
the working principle of the invention is as follows:
firstly, the high-speed stamping channel 2 of the turbine/bimodal stamping combined engine does not work in a low-speed state, an adjustable clapboard device 3 is adopted to seal the inlet of the channel 2 of the stamping engine, the aircraft only depends on the low-speed turbine channel 1 of the turbine/bimodal stamping combined engine to provide thrust, an adjustable air inlet cone device 4 for controlling the air flow of two channels is positioned at the rearmost end, and the opening degree of the low-speed turbine channel 1 of the turbine/bimodal stamping combined engine is fully opened. The adjustable clapboard device 3 adopts an interlayer push-pull structure, and a power device hydraulic actuating mechanism of the adjustable clapboard device 3 controls the opening of the low-speed turbine channel 1 of the turbine/bimodal ramjet combined engine to realize the on-off control of the turbine engine channel 1.
And secondly, the adjustable partition plate device 3 is completely opened during mode conversion, the flow of double channels is only controlled by the adjustable air inlet cone device 4, the adjustable air inlet cone device 4 moves forwards, the air flow of the low-speed turbine channel 1 of the turbine/dual-mode ramjet combined engine continuously decreases, the turbine engine changes the working state and is switched from a slow-turning state to a windmill state, the flow loss increases at the moment of conversion, the thrust is caused to drop suddenly, the adjustable air inlet cone device 4 further moves forwards, the air flow of the high-speed ramjet channel 2 of the turbine/dual-mode ramjet combined engine increases, the thrust is recovered until the mode conversion is completed, and the power of the aircraft is provided by the ramjet engine.
Based on the above principle, the working process of the device of the invention is as follows:
when the aircraft flies below Ma2, the low-speed turbine channel 1 of the turbine/dual-mode ram combined engine is opened, air enters the combustor of the turbine engine from the low-speed turbine channel 1 of the turbine/dual-mode ram combined engine, and the high-speed ram channel 2 of the turbine/dual-mode ram combined engine is closed. At the moment, the adjustable clapboard device 3 is in an extending state and extends forwards to block the inlet of the high-speed stamping channel 2 of the turbine/bimodal stamping combined engine, the adjustable clapboard device and the high-speed stamping channel 2 are in line contact, airflow is prevented from entering the high-speed stamping channel 2 of the turbine/bimodal stamping combined engine, and the flow coefficient of an air inlet channel of a low-speed turbine engine is ensured.
When the aircraft accelerates to above Ma2, the low-speed turbine engine is required to be ignited to work from a slow vehicle to a windmill, and the high-speed dual-mode ramjet engine is required to be ignited to work. At the moment, the adjustable clapboard device 3 is retracted, the high-speed stamping channel 2 of the turbine/bimodal stamping combined engine is opened, the adjustable air inlet cone device 4 moves forwards until the adjustable air inlet cone device 4 is contacted with the inner wall surface of the low-speed turbine channel 1 of the turbine/bimodal stamping combined engine, and the limiting device is triggered. At the moment, the adjustable air inlet cone device 4 seals the low-speed turbine channel 1 of the turbine/dual-mode ramjet combined engine, all air flows into the high-speed ramjet channel 2 of the turbine/dual-mode ramjet combined engine, the dual-mode ramjet engine is ignited, the turbine engine is flamed out, and mode conversion is completed.
The invention utilizes the movable air inlet cone and the clapboard mode under the wide-area working condition to regulate the air flow entering the high/low speed channel according to the flow continuous rule to complete the mode conversion of the series turbine/dual-mode ramjet combined engine.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A tandem turbine/dual-mode ramjet combination modality conversion apparatus, comprising: the adjustable partition plate device (3), the adjustable air inlet cone device (4) and the adjustable air inlet cone device equipment cabin (7);
the adjustable air inlet cone device (4) comprises a high-speed channel pre-compression surface (5), an adjustable air inlet cone (6) and an adjustable air inlet cone threaded rod (8);
the adjustable clapboard device (3) is of a cylindrical structure and is positioned in a low-speed turbine channel (1), namely a turbine engine channel, of the turbine/bimodal ramjet combined engine;
the high-speed channel precompression surface (5) is connected with the adjustable air inlet cone (6), the adjustable air inlet cone (6) is in surface contact with the adjustable air inlet cone device cabin (7), the adjustable air inlet cone device cabin (7) is a fixed part, one end of an adjustable air inlet cone threaded rod (8) is positioned in the adjustable air inlet cone (6), and the other end of the adjustable air inlet cone threaded rod is screwed into the adjustable air inlet cone device cabin (7); the adjustable air inlet cone device cabin (7) is powered by an air inlet cone moving power device, so that an adjustable air inlet cone threaded rod (8) is driven to rotate forwards or reversely, a high-speed channel pre-compression surface (5) and an adjustable air inlet cone (6) are driven to move forwards or backwards together, and the adjustable air inlet cone device (4) can move forwards or backwards; the adjustable air inlet cone device cabin (7) is fixed on the inner surface of the low-speed turbine channel (1) of the turbine/bimodal ramjet combined engine;
when the aircraft flies below Ma2, the adjustable inlet cone device (4) can extend backwards to be in contact with the adjustable inlet cone device equipment cabin (7), the adjustable partition plate device (3) can extend forwards to block the inlet of the high-speed stamping channel (2) of the turbine/dual-mode stamping combined engine, and the adjustable inlet cone device and the adjustable partition plate device are in line contact;
when the aircraft accelerates to a position above Ma2, the adjustable air inlet cone device (4) can extend forwards to block the inlet of the low-speed turbine channel (1) of the turbine/bimodal ramjet combined engine, and the adjustable air inlet cone device and the low-speed turbine channel are in line contact.
2. The device according to claim 1, characterized in that the inner surface of the low speed turbine channel (1) of the combined turbine/bimodal ramjet engine is provided with a limiting device for fixing the position of the adjustable air cone device (4).
3. The device according to claim 1, characterized in that said adjustable cone means (4) slidably controls the dual channel air flow, with an arc design.
4. An arrangement according to claim 1, characterized in that the adjustable diaphragm means (3) has a hydraulic actuating mechanism as a power means for controlling the opening of the low speed turbine channel (1) of the combined turbo/bi-modal ramjet engine.
5. A method of operating a device according to any of claims 1 to 4, characterized in that the method is implemented on the basis of the following principles:
the high-speed stamping channel (2) of the turbine/bimodal stamping combined engine does not work in a low-speed state, an adjustable clapboard device (3) is adopted to seal the inlet of the channel (2) of the stamping engine, an aircraft only depends on the low-speed turbine channel (1) of the turbine/bimodal stamping combined engine to provide thrust, an adjustable air inlet cone device (4) used for controlling air flow of two channels is located at the rearmost end, the opening degree of the low-speed turbine channel (1) of the turbine/bimodal stamping combined engine is fully opened, and a power device hydraulic actuating mechanism of the adjustable clapboard device (3) controls the opening degree of the low-speed turbine channel (1) of the turbine/bimodal stamping combined engine to realize on-off control of the turbine channel (1).
6. The method according to claim 5, characterized in that the method is implemented based on the following further principle: when the mode is switched, the adjustable clapboard device (3) is completely opened, the flow of the two channels is only controlled by the adjustable air inlet cone device (4), the adjustable air inlet cone device (4) moves forwards, the air flow of the low-speed turbine channel (1) of the turbine/dual-mode ramjet combined engine continuously decreases, the turbine engine changes the working state and is switched from a slow-turning state to a windmill state, the flow loss is increased at the switching moment, the thrust is suddenly reduced, the adjustable air inlet cone device (4) further moves forwards, the air flow of the high-speed ramjet channel (2) of the turbine/dual-mode ramjet combined engine increases, the thrust is recovered until the mode switching is completed, and the power of an aircraft is provided by the ramjet engine.
7. The method of claim 5, wherein in the method, when the aircraft flies below Ma2, the low-speed turbine passage (1) of the turbine/bimodal ramjet combination engine is opened, air enters the combustor of the turbine engine from the low-speed turbine passage (1) of the turbine/bimodal ramjet combination engine, the high-speed ramjet passage (2) of the turbine/bimodal ramjet combination engine is closed, the adjustable baffle plate device (3) is in an extended state and extends forwards to block the inlet of the high-speed ramjet passage (2) of the turbine/bimodal ramjet combination engine, and the adjustable baffle plate device and the high-speed ramjet passage are in line contact, so that air flow is prevented from entering the high-speed ramjet passage (2) of the turbine/bimodal ramjet combination engine, and the air inlet flow.
8. A method according to claim 6, characterised in that in the method, the low speed turbine engine is required to be turned from slow to windmilling when the aircraft is accelerated above Ma2, the high speed dual mode ramjet is fired, the adjustable diaphragm means (3) is retracted, the high speed ram channel (2) of the turbo/dual mode ramjet combination is opened and the adjustable inlet cone means (4) is moved forward until the adjustable inlet cone means (4) contacts the inner wall of the low speed turbine channel (1) of the turbo/dual mode ramjet combination to activate the position limiting means. At the moment, the adjustable air inlet cone device (4) seals a low-speed turbine channel (1) of the turbine/dual-mode ramjet combined engine, all air flows into the high-speed ramjet channel (2) of the turbine/dual-mode ramjet combined engine, the dual-mode ramjet engine is ignited, the turbine engine is flamed out, and mode conversion is completed.
9. Use of the device of any one of claims 1 to 4 in a turbo/bi-modal ramjet combined engine.
10. Use of a device according to any one of claims 1 to 4 in a space aircraft power plant.
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| CN202011250157.1A CN112360645A (en) | 2020-11-10 | 2020-11-10 | Tandem turbine/double-mode stamping combined engine mode conversion device |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114753930A (en) * | 2022-04-19 | 2022-07-15 | 南京航空航天大学 | Combined power mode conversion method based on axisymmetric air inlet channel configuration characteristics |
| CN115788683A (en) * | 2022-11-30 | 2023-03-14 | 中国航发控制系统研究所 | Modal conversion control method based on combined engine |
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Application publication date: 20210212 |