Ramjet Combustion Chamber Stabilizer and Flame Stabilization Method

A technology of ramjet engine and combustion chamber, which is applied in the direction of combustion method, combustion chamber, continuous combustion chamber, etc., can solve the problems of large aerodynamic loss of mechanical flame stabilizer, inability to meet the requirements of high efficiency and stable flame, and low working reliability, so as to achieve increased The effect of jet penetration depth and mixing effect, improving atomization effect and improving flame stabilization effect

Active Publication Date: 2020-11-06
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology

[0005] In order to solve the problems of large aerodynamic loss and narrow flame stabilization range of existing mechanical flame stabilizers, which lead to low reliability and cannot meet the requirements of high efficiency flame stabilization at high Mach numbers, the present invention provides a ramjet combustion chamber stabilizer and stabilizer The flame method, the swept back arc support plate has small high-speed flow resistance loss, the jet flow is controllable, and the jet flow enhances the mixing effect, which can meet a wide range of high-efficiency flame stabilization requirements

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  • Ramjet Combustion Chamber Stabilizer and Flame Stabilization Method

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Embodiment Construction

[0038] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0039] A ramjet combustion chamber stabilizer is characterized in that it includes a swept back arc-shaped support plate 1, and the swept-back arc-shaped support plate 1 includes a bottom surface 11, two end surfaces 15 and two side profiles 12; The cross-section of the swept-back arc support plate 1 is triangular; the front parts of the two side profiles 12 are connected, and the two side profiles 12 are respectively concaved to form arc side profiles. The existence of the arc at the rear of the surface 12 has a large enough deflection angle for the incoming flow, and can generate a large recirculation zone with a small blocking ratio, which is conducive to uniform mixing of fuel, stable flame, and high-efficiency combustion. The intersection of the two side profiles 12 is a smooth transition.

[0040] A blind hole 13 extending to the other ...

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Abstract

The invention relates to a ramjet combustion chamber, and provides a ramjet combustion chamber stabilizer and a flame stabilization method. The problems that existing mechanical flame stabilizers havelarge pneumatic loss and narrow flame stabilization range, and consequently the working reliability is low, and the requirement of efficient flame stabilization under the high Mach number cannot be met are solved. The ramjet combustion chamber stabilizer includes a sweepback arc-shaped supporting plate, the sweepback arc-shaped supporting plate includes a bottom face, two end faces and two side profiles, the cross section of the sweepback arc-shaped supporting plate is triangle-like, the front parts of the two side profiles are connected, and the two side profiles are concaved to form an arcside profile.

Description

technical field [0001] The invention relates to a ramjet combustion chamber, in particular to a ramjet combustion chamber stabilizer and a flame stabilizing method. Background technique [0002] The combustion chamber of the ramjet engine is under the condition of high-speed incoming flow. In order to ensure the stable combustion of the flame in the combustion chamber of the ramjet engine, it is necessary to establish a local low-speed recirculation zone in the combustion chamber, so that the flame propagation speed is equal to the incoming flow speed and the fuel residence time is greater than the ignition delay. Time and other conditions to maintain the continuous existence and spread of the flame in the entire combustion chamber. [0003] An existing sub-combustible ramjet has a very wide working range (Ma2~Ma5), far exceeding the working range of a more mature type of sub-combustible ramjet at present, and the problem of high efficiency and stable flame in a wide range i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/20
CPCF23R3/20
Inventor 任加万梁俊龙李光熙周杰付莉莉许军民陈开拓杨振鹏
Owner XIAN AEROSPACE PROPULSION INST
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