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A Rotating Detonation Combustion Method for Eliminating Gyro Moments During Flight

A technology of gyro torque and flight process, which is applied in the direction of combustion method, deflagration combustion chamber, combustion chamber, etc., can solve the problems that cannot be adopted, increase the complexity of flight control, etc., and achieve the effect of reducing gyro torque

Active Publication Date: 2021-12-10
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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  • A Rotating Detonation Combustion Method for Eliminating Gyro Moments During Flight
  • A Rotating Detonation Combustion Method for Eliminating Gyro Moments During Flight
  • A Rotating Detonation Combustion Method for Eliminating Gyro Moments During Flight

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 method 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 The following conditions:#

[0062] 1. Combustion chamber length

[0063] 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 method of the engine combustion chamber, the length of the combustion chamber must meet the following conditions:

[0064] 0.75d 2 ≤l 1 ≤1.2d 2

[0065] 0.375(d 3 +d 4 )≤l 2 ≤0.625(d 3 +d 4 )

[0066] 0.375(d 2i+1 +d 2i+2 )≤l i+1 ≤0.625(d 2i+1 +d 2i+2 )

[0067] 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 th...

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PUM

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Abstract

The invention proposes a rotary detonation combustion method for eliminating gyro torque during flight, which includes a rotary detonation combustion chamber body, an ignition system, a supply and mixing system and an exhaust system. By adopting the structural layout of two or more coaxial annular combustion chambers, each combustion chamber is used as an independent unit, and the fuel and oxidant are respectively injected by the nozzle installed on the head. The inert medium nozzle is installed on the ignition position side, and the inert medium is injected Note slightly earlier than ignition, stop injecting inert medium after detonation is triggered, and the detonation wave can only propagate in the direction away from the inert medium, so as to realize the control of the rotation direction of the detonation wave. The propagation direction of the detonation wave in different combustion chambers is different, making different combustion The torques in the chamber cancel each other out. The invention can effectively eliminate the gyro moment of the rotary detonation engine during flight, and can improve the working stability of the engine. The invention can be used in the fields of the rotary detonation engine and the like.

Description

technical field [0001] The invention relates to the field of rotary detonation engines, in particular to a rotary detonation combustion method 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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Patent Type & Authority Patents(China)
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