CN220582497U - Rotary detonation combustion chamber with accurately controllable detonation wave propagation direction - Google Patents
Rotary detonation combustion chamber with accurately controllable detonation wave propagation direction Download PDFInfo
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- CN220582497U CN220582497U CN202321519000.3U CN202321519000U CN220582497U CN 220582497 U CN220582497 U CN 220582497U CN 202321519000 U CN202321519000 U CN 202321519000U CN 220582497 U CN220582497 U CN 220582497U
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- detonation
- combustion chamber
- wedge plate
- deflection wedge
- detonation combustion
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- 238000005474 detonation Methods 0.000 title claims abstract description 107
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 58
- 238000001816 cooling Methods 0.000 claims abstract description 42
- 239000000446 fuel Substances 0.000 claims abstract description 6
- 238000000889 atomisation Methods 0.000 claims description 6
- 230000000712 assembly Effects 0.000 claims description 2
- 238000000429 assembly Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 7
- 239000007789 gas Substances 0.000 description 14
- 230000035939 shock Effects 0.000 description 9
- 238000010586 diagram Methods 0.000 description 5
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000010348 incorporation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000010791 quenching Methods 0.000 description 1
- 230000000171 quenching effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
Abstract
A rotary detonation combustion chamber with accurately controllable detonation wave propagation direction comprises an air inlet channel, an oil circuit component, an igniter and a detonation combustion chamber; the oil path component is communicated with the air inlet channel and is used for providing fuel for the detonation combustion chamber; the igniter is arranged at the front end of the detonation combustion chamber and is used for igniting the fuel-air mixed gas entering the detonation combustion chamber to form rotary detonation combustion; the deflection wedge plate is positioned in the detonation combustion chamber, the angle between the deflection wedge plate and the horizontal direction is 45 degrees, and the deflection wedge plate comprises a film cooling hole and a cooling flow channel; the air film cooling hole penetrates through the deflection wedge plate along the thickness direction of the deflection wedge plate, the cooling flow passage is arranged along the width direction of the deflection wedge plate, and the cooling flow passage is communicated with the air film cooling hole inside. The utility model has simple principle and reliable structure, and can accurately control the propagation direction of detonation waves in the working process of the rotary detonation combustion chamber, thereby realizing the optimal matching of the rotary detonation combustion chamber and the turbine component.
Description
Technical Field
The utility model relates to the field of rotary detonation engines, in particular to a rotary detonation combustion chamber with accurately controllable detonation wave propagation direction.
Background
Combustion can be divided into two different modes: knocking and knocking. Compared to knocking, knocking not only has higher thermal efficiency and energy release rate, but also can realize total pressure gain. By replacing the detonation combustion chamber in a traditional aeroengine with a detonation combustion chamber, further improvements in the overall performance of the engine are expected. Currently, detonation combustors are mainly of three types: pulse detonation combustors, oblique detonation combustors, and rotary detonation combustors. The rotary knocking combustion chamber has the characteristics of compact structure, stable thrust, continuous operation only by one-time ignition and the like, and is expected to realize engineering practical application at first.
The incorporation of a gas turbine engine into a rotary detonation gas turbine engine is one of the technical applications of rotary detonation combustors. Compared with the traditional gas turbine engine, the rotary detonation gas turbine engine can reduce the number of stages of a compressor, simplify the engine structure and reduce the weight of the engine. Meanwhile, the rotary detonation gas turbine engine has the advantages of low fuel consumption, high thrust weight ratio and the like. However, the gas at the outlet of the rotary detonation combustor is in a high-frequency pulsation state, and the pulsation characteristic can influence the stability of the output power of the turbine, aggravate the pneumatic load born by the blades, and reduce the service life and reliability of the turbine. And the propagation direction of the knock wave affects the occurrence of the above phenomenon. Experimental results show that in the process of rotating detonation combustion wave propagation, various propagation modes can occur, including a clockwise propagation mode, a counterclockwise propagation mode, a multi-wave reverse collision mode and the like. This uncertainty in the direction of propagation of the detonation wave is very detrimental to the stable operation of the turbine. Therefore, the control of the propagation direction of the detonation wave is realized, and the method has important significance for the technical development of the propelling rotary detonation gas turbine engine.
Disclosure of Invention
The utility model aims to solve the problems in the prior art and provide the rotary detonation combustion chamber with the detonation wave propagation direction accurately controllable, which has the advantages of simple principle and reliable structure, and can accurately control the detonation wave propagation direction in the working process of the rotary detonation combustion chamber, thereby realizing the optimal matching of the rotary detonation combustion chamber and turbine components.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a rotary detonation combustion chamber with accurately controllable detonation wave propagation direction comprises an air inlet channel, an oil circuit component, an igniter and a detonation combustion chamber;
the oil circuit component is communicated with the air inlet channel and is used for providing fuel for the knocking combustion chamber;
the igniter is arranged at the front end of the detonation combustion chamber and is used for igniting fuel-air mixed gas entering the detonation combustion chamber to form rotary detonation combustion;
the detonation combustion chamber is arranged at the rear of the air inlet channel and comprises an inner wall surface, an outer wall surface and a deflection wedge plate; the inner wall surface and the outer wall surface form a cavity, the deflection wedge plate is positioned in the cavity and is arranged on the inner wall surface, and the deflection wedge plate comprises a film cooling hole and a cooling flow channel; the air film cooling holes penetrate through the deflection wedge plate along the thickness direction of the deflection wedge plate, the cooling flow channels are arranged along the width direction of the deflection wedge plate, the cooling flow channels are communicated with the air film cooling holes inside, and the outer end parts of the cooling flow channels are communicated with the outside; the cooling air is injected into the deflection wedge plate through the cooling flow passage and then flows out of the film cooling holes.
The angle between the deflection wedge plate and the horizontal direction is 45 degrees; the bottom of the deflection wedge plate is provided with a mounting hole, and the deflection wedge plate is connected with the inner wall surface through the mounting hole.
The oil circuit assembly comprises an oil supply pipeline and an atomization nozzle arranged at the end part of the oil supply pipeline, and the atomization nozzle is positioned in the air inlet channel.
And the oil circuit assemblies are uniformly distributed in a plurality of groups along the circumferential direction of the engine.
The igniters are uniformly arranged along the circumferential direction of the engine.
The deflection wedge plates are uniformly arranged along the circumferential direction of the detonation combustion chamber.
Compared with the prior art, the technical scheme of the utility model has the beneficial effects that:
the rotary detonation combustion chamber with the accurately controllable detonation wave propagation direction can automatically realize the accurate control of the detonation wave propagation direction in the operation process of the rotary detonation combustion chamber by utilizing the interaction between the deflection wedge plate and the detonation wave induced oblique shock wave, and has simple principle and reliable structure.
Drawings
Fig. 1 is a schematic structural view of the present utility model.
Fig. 2 is a schematic cross-sectional view of the present utility model.
Fig. 3 is a schematic diagram of an oil circuit assembly.
Fig. 4 is a schematic view of the structure of the deflection wedge plate.
FIG. 5 is a schematic diagram showing weak reflection of oblique shock waves at the deflection wedge plate when the propagation direction of the detonation wave is consistent with a preset direction.
FIG. 6 is a schematic diagram of normal injection of premixed gas when the propagation direction of detonation wave is consistent with a preset direction.
FIG. 7 is a schematic diagram showing the strong reflection of oblique shock waves at the deflection wedge plate when the propagation direction of the detonation wave is inconsistent with the preset direction.
FIG. 8 is a schematic diagram showing suppression of premixed gas injection when the propagation direction of detonation waves is inconsistent with a preset direction.
Reference numerals: the device comprises a 1 air inlet channel, a 2 oil circuit component, a 21 oil supply pipeline, a 22 atomizer, a 3 igniter, a 4 detonation combustion chamber, a 41 inner wall surface, a 42 outer wall surface, a 43 deflection wedge plate, a 431 air film cooling hole and a 432 cooling flow channel.
Detailed Description
In order to make the technical problems, technical schemes and beneficial effects to be solved more clear and obvious, the utility model is further described in detail below with reference to the accompanying drawings and embodiments.
Referring to fig. 1 to 4, the rotary detonation combustion chamber with accurately controllable detonation wave propagation direction comprises an air inlet channel 1, an oil circuit component 2, an igniter 3 and a detonation combustion chamber 4;
the detonation combustion chamber 4 is arranged behind the air inlet channel 1 and comprises an inner wall surface 41, an outer wall surface 42 and a deflection wedge plate 43; the inner wall surface 41 and the outer wall surface 42 form a chamber, the deflection wedge plate 43 is positioned in the chamber and is arranged on the inner wall surface 41, the angle between the deflection wedge plate 43 and the horizontal direction is 45 degrees, and the deflection wedge plate 43 comprises a film cooling hole 431 and a cooling flow passage 432; the film cooling hole 431 penetrates through the deflection wedge plate 43 along the thickness direction of the deflection wedge plate 43, the cooling flow channel 432 is arranged along the width direction of the deflection wedge plate 43, the cooling flow channel 432 is communicated with the film cooling hole 431 internally, and the outer end part of the cooling flow channel 432 is communicated with the outside; wherein, cooling air is injected into the deflection wedge plate 43 through the cooling flow passage 432, and then the cooling air flows out from a plurality of air film cooling holes 431 uniformly distributed on the surface of the deflection wedge plate 43;
the oil circuit assembly 2 is controlled to be communicated with the air inlet channel 1 and is used for providing fuel for the detonation combustion chamber 4, and comprises an oil supply pipeline 21 and an atomization nozzle 22 arranged at the end part of the oil supply pipeline 21, wherein the atomization nozzle 22 is positioned in the air inlet channel 1;
the igniter 3 is disposed at a front end in the detonation combustion chamber 4 for igniting the fuel-air mixture entering the detonation combustion chamber 4 to form rotary detonation combustion.
In the embodiment, 12 groups of oil circuit components 2 are uniformly distributed along the circumferential direction of the engine, and 8 groups of igniters 3 are uniformly distributed along the circumferential direction of the engine so as to realize smooth detonation and stable combustion of the detonation combustion chamber 4. The fuel is fed through the oil feed pipeline 21, atomized by the atomizer 22, mixed with the incoming air in the air inlet channel 1, and then flows into the detonation combustion chamber 4, and is ignited by the igniter 3 to form rotary detonation combustion.
In the embodiment, 8 deflection wedge plates are circumferentially and uniformly distributed, and a plurality of air film cooling holes 431 are uniformly distributed on each deflection wedge plate. Specifically, the bottom of the deflection wedge plate is provided with a mounting hole, and the deflection wedge plate is mounted on the inner wall surface through the mounting hole.
While the rotary detonation combustion chamber 4 performs detonation combustion, cooling gas is introduced from the outside and injected into the deflection wedge plate 43 through the cooling flow passage 432, and then the cooling gas flows out of the gas film cooling holes 431, so that high-temperature gas is isolated from being in direct contact with the deflection wedge plate 43, and the purpose of heat protection is achieved.
The deflection wedge plate in the rotary detonation combustion chamber with the accurately controllable detonation wave propagation direction can accurately control the detonation wave propagation direction, and the control process is as follows:
1. referring to fig. 5, when the propagation direction of the detonation wave is anticlockwise, the simulation result obtained by Fluent software is shown in fig. 6, at this time, the oblique shock wave induced by the detonation wave is in a relatively vertical state with the deflection wedge plate, the oblique shock wave only slightly reflects at the deflection wedge plate, and the generated weak reflected wave does not have obvious influence on the detonation combustion state;
2. referring to fig. 7, when the propagation direction of the detonation wave is clockwise, the simulation result is as shown in fig. 8, the detonation wave induced oblique shock wave is in a relatively parallel state with the deflection wedge plate, and the oblique shock wave can generate strong shock wave reflection on the surface of the deflection wedge plate. When the high-intensity reflected shock wave is transmitted back to the detonation wave, the injection of fresh premixed gas can be obviously inhibited, and the height of a premixed gas filling area is reduced;
3. in the next propagation period, the continuous self-sustaining propagation of the detonation wave cannot be maintained due to the fact that the height of the premixing zone is too low, the detonation wave is annihilated, the rotary detonation combustion chamber enters the quenching period, and the combustion chamber can not enter a stable running state until the next detonation generates rotary detonation wave with the opposite propagation direction, so that the accurate control of the propagation direction of the detonation wave is realized.
The rotary detonation combustion chamber with the accurately controllable detonation wave propagation direction can accurately control the detonation wave propagation direction in the working process of the rotary detonation combustion chamber, and has the advantages of simple principle, reliable structure and convenience for being applied to engineering practice.
Claims (6)
1. The utility model provides a rotatory detonation combustion chamber of accurate controllable of detonation wave propagation direction which characterized in that: comprises an air inlet channel, an oil circuit component, an igniter and a detonation combustion chamber;
the oil circuit component is communicated with the air inlet channel and is used for providing fuel for the knocking combustion chamber;
the igniter is arranged at the front end of the detonation combustion chamber and is used for igniting fuel-air mixed gas entering the detonation combustion chamber to form rotary detonation combustion;
the detonation combustion chamber is arranged at the rear of the air inlet channel and comprises an inner wall surface, an outer wall surface and a deflection wedge plate; the inner wall surface and the outer wall surface form a cavity, the deflection wedge plate is positioned in the cavity and is arranged on the inner wall surface, and the deflection wedge plate comprises a film cooling hole and a cooling flow channel; the air film cooling holes penetrate through the deflection wedge plate along the thickness direction of the deflection wedge plate, the cooling flow channels are arranged along the width direction of the deflection wedge plate, the cooling flow channels are communicated with the air film cooling holes inside, and the outer end parts of the cooling flow channels are communicated with the outside; the cooling air is injected into the deflection wedge plate through the cooling flow passage and then flows out of the film cooling holes.
2. A rotary detonation combustor with accurately controllable detonation wave propagation direction as defined in claim 1 wherein: the angle between the deflection wedge plate and the horizontal direction is 45 degrees; the bottom of the deflection wedge plate is provided with a mounting hole, and the deflection wedge plate is connected with the inner wall surface through the mounting hole.
3. A rotary detonation combustor with accurately controllable detonation wave propagation direction as defined in claim 1 wherein: the oil circuit assembly comprises an oil supply pipeline and an atomization nozzle arranged at the end part of the oil supply pipeline, and the atomization nozzle is positioned in the air inlet channel.
4. A rotary detonation combustor with accurately controllable detonation wave propagation direction as defined in claim 1 wherein: and the oil circuit assemblies are uniformly distributed in a plurality of groups along the circumferential direction of the engine.
5. A rotary detonation combustor with accurately controllable detonation wave propagation direction as defined in claim 1 wherein: the igniters are uniformly arranged along the circumferential direction of the engine.
6. A rotary detonation combustor with accurately controllable detonation wave propagation direction as defined in claim 1 wherein: the deflection wedge plates are uniformly arranged along the circumferential direction of the detonation combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321519000.3U CN220582497U (en) | 2023-06-14 | 2023-06-14 | Rotary detonation combustion chamber with accurately controllable detonation wave propagation direction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321519000.3U CN220582497U (en) | 2023-06-14 | 2023-06-14 | Rotary detonation combustion chamber with accurately controllable detonation wave propagation direction |
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| Publication Number | Publication Date |
|---|---|
| CN220582497U true CN220582497U (en) | 2024-03-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321519000.3U Active CN220582497U (en) | 2023-06-14 | 2023-06-14 | Rotary detonation combustion chamber with accurately controllable detonation wave propagation direction |
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| Country | Link |
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| CN (1) | CN220582497U (en) |
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2023
- 2023-06-14 CN CN202321519000.3U patent/CN220582497U/en active Active
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