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Double-combustion-chamber scramjet engine and control method thereof

A scramjet, dual-combustion chamber technology, applied in ramjet engines, combined engines, machines/engines, etc., can solve the problems of combination and relay difficulties, reduce the adjustment of additional mass, widen the working Mach number range, reduce The effect of high temperature dynamic sealing requirements

Active Publication Date: 2017-08-04
BEIJING POWER MACHINERY INST +1
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  • Claims
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Problems solved by technology

[0005] The purpose of the present invention is to overcome the deficiencies of the prior art, provide a dual-combustion chamber scramjet, and solve the technical problem of the combination of a turbine engine and a dual-combustion chamber scramjet, and difficulty in relaying

Method used

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  • Double-combustion-chamber scramjet engine and control method thereof

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Embodiment 1

[0045] This embodiment provides a dual combustion chamber scramjet, figure 1 Its structure is shown, the engine is made up of intake port 1', subsonic combustion chamber 2', supersonic combustion chamber 3' and tail nozzle 4', and said subsonic combustion chamber 2' and supersonic combustion chamber 3' Use rectangular parallel layout;

[0046] see figure 2 and image 3 , figure 2 Schematic diagram of the layout of the double inlet runners provided by the embodiment of the present invention; image 3 It is a schematic diagram of the air inlet channel adjustment scheme in the embodiment of the present invention. The inlet channel 1' adopts a binary inlet channel configuration, and is divided into a sub-combustion channel B and a super-combustion channel A and C by a support plate along the flow direction. The B channel is an intermediate channel, which connects In the subsonic combustion chamber 2', the A and C flow channels are distributed on both sides of the B flow cha...

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Abstract

The invention aims at overcoming the defects in the prior art and provides a double-combustion-chamber scramjet engine and a control method thereof. Combustion chambers of the engine are in non-axismmetric layout, the combination difficulty of a ramjet and a turbine engine is lowered, and an air inlet way of the double-combustion-chamber scramjet engine is improved. Two-dimensional air inlet way configuration is adopted in the air inlet way, the air inlet way is divided into at least one subsonic combustion runner and at least two supersonic runners through supporting plates, wherein the supersonic combustion runners are evenly distributed on the two sides of the subsonic combustion runners. Due to the fact that inner shrinkage section adjusting molded surfaces and expansion section adjusting molded surfaces are additionally arranged in design of all the runners, the area of a throat of the air inlet way is controlled, the requirement for air in different compression degrees of the combustion chambers is met, the Mach number range of work of the engine is enlarged, and the performance of the engine is improved.

Description

technical field [0001] The invention belongs to the technical field of aerospace engines, and relates to a dual combustion chamber scramjet engine and a control method thereof. Background technique [0002] With the rapid development of hypersonic technology, adjacent space has become a new frontier for world powers to compete for, and a new strategic commanding height for national security. Hypersonic vehicles in adjacent space have gradually become the focus of national defense construction in various technologically advanced countries. Near space hypersonic vehicle is a reusable hypersonic vehicle powered by air-breathing combined engine, capable of horizontal take-off and landing, maneuvering in dense atmosphere, near space and near earth orbit. [0003] Among various air-breathing combined engines, the combined power scheme of a turbine engine and a wide-range ramjet engine has the most promising engineering application prospects, but the "thrust gap" is the biggest pro...

Claims

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Application Information

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IPC IPC(8): F02C3/14F02C7/042F02C7/057F02K7/16
CPCF02C3/14F02C7/042F02C7/057F02K7/16
Inventor 费立森马军侯金丽王辽张波
Owner BEIJING POWER MACHINERY INST
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