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Variable-structure dual-mode ramjet combustion chamber

A ram combustion chamber, dual-mode technology, applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve the problems of aircraft loss of control, thrust and momentum changes, etc., to reduce performance requirements, broaden the working Mach number, expand Effect of operating Mach number range

Active Publication Date: 2021-07-20
XIAMEN UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This would cause a sudden change in thrust and momentum on the vehicle, possibly causing loss of control of the vehicle

Method used

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  • Variable-structure dual-mode ramjet combustion chamber
  • Variable-structure dual-mode ramjet combustion chamber
  • Variable-structure dual-mode ramjet combustion chamber

Examples

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Embodiment Construction

[0030] The preferred embodiments of the present invention will be described below in conjunction with the accompanying drawings, that is, the preferred embodiments described here are only used to illustrate and explain the present invention, and are not intended to limit the present invention.

[0031] Such as Figure 1~4 As shown, the embodiment of the present invention includes a variable structure dual-mode combustion chamber consisting of an isolation section 1, a sudden expansion section 4, a concave cavity 15, a lower wall surface 16 of the combustion chamber, a first adjustable variable section 5, and a second adjustable variable section. Section 17 and the third adjustable variable section 12 are jointly formed. The isolation section 1 and the sudden expansion section 4 are connected by bolts. Pioneer hydrogen injection modules 2, 13 on the upper and lower walls and upper and lower kerosene injection modules 3, 13 are fixed on the sudden expansion section 4 by bolts, ...

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Abstract

The invention discloses a variable-structure dual-mode ramjet combustion chamber, and relates to an aero-engine combustion chamber. The variable-structure dual-mode ramjet combustion chamber comprises an isolation section, a concave cavity, a sudden expansion section, an adjustable variable section, a pioneer hydrogen injection module, a kerosene injection module, a connecting rod and a hydraulic drive, the molded surface of the combustion chamber is driven and adjusted through the hydraulic connecting rod, so that the combustion chamber works in different modes under different flight Mach numbers, when Ma is greater than 2 and less than A Mat; 4, hydraulic drive changes the position of an adjustable variable section through the connecting rod and a connecting block to adjust the molded surface of the combustion chamber into an equal straight section and a divergent section, and an exhaust nozzle is a latile nozzle, when Ma is greater than or equal to 4 and less than 6, the hydraulic drive changes the position of the adjustable variable section through the connecting rod and the connecting block to adjust the molded surface of the combustion chamber into an equal straight section, a diffusion section and an equal straight section, and when Ma is larger than or equal to 6.0, the hydraulic drive changes the position of the adjustable variable section through the connecting rod and the connecting block to adjust the molded surface of the combustion chamber into the equal straight section, the diffusion section and a pure expansion spray pipe. Working performance of the combustion chamber under the wide Mach number is improved, heat efficiency and fuel specific impulse are improved, boosting oil consumption is reduced, and the flight range is improved.

Description

technical field [0001] The invention relates to an aero-engine combustion chamber, in particular to a variable-structure dual-mode ram combustion chamber with an adjustable combustion chamber profile. Background technique [0002] When the flight Mach number Ma>3, the performance of the ramjet engine is the best, and when the flight Mach number Ma=3~6, the performance of the sub-combustion ramjet engine is better than that of the scramjet engine, and when the flight Mach number Ma>6 When , the performance of scramjet engine is better than that of subcombustion ramjet engine (Weber R J, Mackay J S. An Analysis of Ramjet Engines Using Supersonic Combustion [R]. NASA TN 4386, 1958). For optimum performance, ramjets must operate in a bimodal manner. During the acceleration process of a hypersonic vehicle with a dual-mode ramjet as a propulsion device, the heat release and its distribution in the combustion chamber must be adjusted accordingly to convert the engine from th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28F23R3/44
CPCF23R3/286F23R3/44
Inventor 黄玥沈吴冰懿易理哲赵书苗尤延铖吴智锋
Owner XIAMEN UNIV
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