Anti-return air inlet structure of rotary detonation combustion chamber

A technology of air intake structure and combustion chamber, which is applied in the field of aero-engines, can solve the problems of large total pressure loss in the combustion chamber, and achieve the effect of increasing the total pressure gain and reducing the impact on performance

Active Publication Date: 2021-12-21
AIR FORCE UNIV PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to improve the problem of the large total pressure loss of the combustion chamber caused by the pressure return, the application provides an anti-backward intake structure for the rotating detonation combustion chamber

Method used

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  • Anti-return air inlet structure of rotary detonation combustion chamber
  • Anti-return air inlet structure of rotary detonation combustion chamber
  • Anti-return air inlet structure of rotary detonation combustion chamber

Examples

Experimental program
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Effect test

Embodiment 1

[0041] Such as figure 2 As shown, a rotary detonation combustor anti-backflow air intake structure includes a Tesla valve 3 communicating with the rotary detonation combustor 4 and snap-fitted at the inlet of the rotary detonation combustor 4 . The Tesla valve 3 includes a housing 31 and a flow channel 32. The housing 31 is coaxially clamped with the outer wall of the rotating detonation combustion chamber 4. The flow channel 32 is opened in the housing 31, and the inlet end of the flow channel 32 is used for introducing air. , the outlet end of the runner 32 communicates with the annular channel 41 of the rotary detonation combustion chamber 4 .

[0042] Such as figure 2 , image 3 As shown, the flow channel 32 includes an air intake channel 321, a connecting channel 322, an arc-shaped return channel 323 and an expansion channel 324; Including curved road 3231 and straight road 3232, the straight road 3232 is connected with the connecting channel 322 in a straight line. ...

Embodiment 2

[0055] Such as Figure 8 , Figure 9 As shown, the difference between this embodiment and Embodiment 1 is that the housing 31 includes a first connecting cylinder 311, a second connecting cylinder 312 and a deflector block 313, and the first connecting cylinder 311 is coaxially sleeved on the second connecting cylinder. Inside the barrel 312 , the deflector block 313 is coaxially fixed between the first connecting barrel 311 and the second connecting barrel 312 .

[0056] The implementation principle of embodiment 2 is the same as that of embodiment 1, and will not be repeated here.

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PUM

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Abstract

The invention relates to an anti-return air inlet structure of a rotary detonation combustion chamber. The anti-return air inlet structure comprises a Tesla valve which communicates with the rotary detonation combustion chamber and is arranged at an inlet of the rotary detonation combustion chamber, the Tesla valve comprises a shell body and a flow channel, the shell body is coaxially connected with the outer wall of the rotary detonation combustion chamber, the flow channel is arranged in the shell body, the inlet end of the flow channel is used for introducing air, and the outlet end of the flow channel communicates with an annular channel of the rotary detonation combustion chamber. By means of the characteristic of one-way circulation of the Tesla valve, a forward channel for air and fuel to enter the rotary detonation combustion chamber is separated from a reverse channel for pressure return, obstruction of pressure return to the air and the fuel entering in the forward direction is effectively reduced, detonation pressurization can make up for total pressure loss generated by upper air inlet, and therefore, the total pressure gain of the rotary detonation combustion chamber is improved.

Description

technical field [0001] The present application relates to the field of aero-engines, in particular to an anti-backward air intake structure for a rotating detonation combustion chamber. Background technique [0002] Detonation combustion is realized by compressing the detonable mixture with the leading fundamental wave to cause a high-speed chemical reaction; because detonation combustion has the advantages of large heat release intensity per unit time, self-pressurization, high combustion efficiency, and low pollutant emissions, based on The propulsion technology of detonation combustion is an important development trend of space technology in the future. The rotary detonation combustor is an annular combustor using a detonation combustion method, and the fuel is jointly supplied by multiple nozzles at the head of the combustor. [0003] Such as figure 1 As shown, in the related art, the intake structure of the rotary detonation combustion chamber includes an intake end 2...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/52F23R3/28
CPCF23R3/52F23R3/28F02C5/11F02K7/067F02K7/08F23R7/00F23R3/10F23D14/825F02C7/00
Inventor 宋飞龙吴云杨兴魁郭善广杨诏胥世达周剑平陈鑫
Owner AIR FORCE UNIV PLA
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