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Rotary detonation combustion scheme for eliminating gyroscopic moment in flight process

A technology of gyro torque and flight process, applied in the combustion method, deflagration combustion chamber, combustion chamber, etc., can solve the problems of inability to use, increase the complexity of flight control, etc., and achieve the effect of reducing gyro torque

Active Publication Date: 2020-12-11
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This part of the circumferential momentum acts on the wall of the combustion chamber during flight to cause the main shaft to precess relative to the inertial space, generating gyro torque and increasing the complexity of flight control
Ideally, a rotating detonation engine does not have any rotating parts, making it impossible to use the relevant measures in conventional turbojet engines

Method used

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  • Rotary detonation combustion scheme for eliminating gyroscopic moment in flight process
  • Rotary detonation combustion scheme for eliminating gyroscopic moment in flight process
  • Rotary detonation combustion scheme for eliminating gyroscopic moment in flight process

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0043] see figure 1 , in this example, the inner combustion chamber is an annular combustion chamber, a plug nozzle is installed at the tail, and a Laval nozzle is installed in the outer combustion chamber. For shock wave intensity and stable propagation, the design criteria should meet the following conditions:

[0044] 1. Combustion chamber length

[0045] The combustion chamber should be able to provide sufficient length to meet the needs of fuel evaporation and combustion response time. According to the structural scheme of the engine combustion chamber, the length of the combustion chamber must meet the following conditions:

[0046] 0.375(d 1 +d 2 )≤l 1 ≤0.625(d 1 +d 2 )

[0047] 0.375(d 3 +d 4 )≤l 2 ≤0.625(d 3 +d 4 )

[0048] 0.375(d 2i+1 +d 2i+2 )≤l i+1 ≤0.625(d 2i+1 +d 2i+2 )

[0049] In the formula, d 1 is the column diameter in the combustion chamber, d 2 is the inner diameter of the outer ring of the inner combustion chamber, d 3 is the outer ...

Embodiment 2

[0061] see figure 2 , in this example, the inner combustion chamber is an empty barrel-shaped combustion chamber, and only the outermost combustion chamber is a Laval nozzle, which can improve the space utilization of the combustion chamber and reduce the heat load on the inner wall of the engine. The design criteria should be Satisfy the following conditions: 1. Combustion chamber length

[0062] The combustion chamber should be able to provide sufficient length to meet the needs of fuel evaporation and combustion response time. According to the structural scheme of the engine combustion chamber, the length of the combustion chamber must meet the following conditions:

[0063] 0.75d 2 ≤l 1 ≤1.2d 2

[0064] 0.375(d 3 +d 4 )≤l 1 ≤0.625(d 3 +d 4 )

[0065] 0.375(d 2i+1 +d 2i+2 )≤l i+1 ≤0.625(d 2i+1 +d 2i+2 )

[0066] In the formula, d 2 is the inner diameter of the outer ring of the inner combustion chamber, d 3 is the outer diameter of the outer ring of the i...

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PUM

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Abstract

The invention provides a rotary detonation combustion scheme for eliminating a gyroscopic moment in the flight process. The rotary detonation combustion scheme for eliminating the gyroscopic moment inthe flight process comprises a rotary detonation combustion chamber body, an ignition system, a supply and mixing system and an exhaust system. The structural layout of two or more coaxial annular combustion chambers is adopted, each combustion chamber serves as an independent unit, a nozzle installed at the head is used for injecting fuel and an oxidizing agent, an inert medium nozzle is installed on one side of an ignition position, inert medium injection is slightly earlier than ignition, inert medium injection is stopped after detonation is triggered, and detonation waves can only be transmitted in the direction away from an inert medium, so that the control over the rotation direction of the detonation waves is achieved, the transmission directions of the detonation waves in the different combustion chambers are different, and torques in the different combustion chambers are counteracted. The gyroscopic moment of a rotary detonation engine in the flight process can be effectivelyeliminated, so that the working stability of the engine can be improved. The rotary detonation combustion scheme for eliminating the gyroscopic moment in the flight process provided by the inventioncan be applied to the fields of rotary detonation engines and the like.

Description

technical field [0001] The invention relates to the field of rotary detonation engines, in particular to a rotary detonation combustion scheme for eliminating gyro torque during flight. Background technique [0002] The Rotating Detonation Engine (RDE) is a new type of jet power device that uses rotating detonation combustion to generate thrust. Its thermal cycle efficiency is much higher than that of a conventional jet engine based on isobaric combustion. Its heat release rate is fast and it can achieve supercharged combustion. It is expected to save heavy and complicated rotating parts and greatly simplify the engine structure. Based on the above advantages, relevant researches on rotating detonation combustion and rotating detonation engines have been carried out at home and abroad. [0003] Although the rotary detonation engine has broad application prospects, it still needs to break through a series of technical obstacles to achieve engineering applications. For examp...

Claims

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Application Information

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IPC IPC(8): F23R7/00
CPCF23R7/00
Inventor 王可于潇栋赵明皓王致程朱亦圆郭俊睿
Owner NORTHWESTERN POLYTECHNICAL UNIV