Air inlet channel for double-combustion-chamber scramjet engine and air inlet control method

A technology of scramjet and dual combustion chambers, which is applied in the direction of ramjet engines, machines/engines, gas turbine devices, etc., can solve problems such as difficulty in adapting to the working Mach number range, flow channel and structure design, and parallel arrangement of turbine channels. Achieve the effects of reducing the adjustment of additional mass, broadening the range of working Mach number, and facilitating the combustion organization

Active Publication Date: 2017-08-04
BEIJING POWER MACHINERY INST +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Existing twin-chamber scramjet engines have an axisymmetric configuration, and adopt axisymmetric inlet ports, which are more suitable for axisymmetric layouts. In terms of flow channel and structural design, it is difficult to achieve a parallel arrangement with the turbine channel and share the intake system, and The existing technology uses a fixed geometry inlet, which is difficult to adapt to a wider range of operating Mach numbers

Method used

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  • Air inlet channel for double-combustion-chamber scramjet engine and air inlet control method
  • Air inlet channel for double-combustion-chamber scramjet engine and air inlet control method
  • Air inlet channel for double-combustion-chamber scramjet engine and air inlet control method

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Embodiment 1

[0044] This embodiment provides a dual-combustion chamber transcendental ramjet intake port, figure 1 Schematic diagram of the layout of the inlet channel of the dual-combustion chamber transcendental ramjet provided by the embodiment of the present invention; figure 2 It is a schematic diagram of the air inlet channel adjustment scheme in the embodiment of the present invention; image 3 A schematic diagram illustrating the flow channel adjustment parameters is shown. The inlet port adopts a binary inlet port configuration, and is divided into sub-combustion channel B and super-combustion channel A and C by a support plate along the flow direction. The B channel is an intermediate channel, connecting the subsonic combustion The A and C flow channels are distributed on both sides of the B flow channel to connect with the supersonic combustion chamber.

[0045] Further, according to the modular arrangement of the engine, the above-mentioned flow channel layout can also be in...

Embodiment 2

[0066] The present embodiment provides the above-mentioned air intake control method of the scramjet intake port of a dual combustion chamber scramjet, including:

[0067]When the flight Mach number reaches the first Mach number, the inner constriction section adjustment surface and the expansion section adjustment surface of the sub-combustion runner and the super-combustion runner are respectively close to the inner contraction section surface and the expansion section surface, and the sub-combustion runner The sonic combustion chamber and the supersonic combustion chamber start to ignite to maintain the total thrust to meet the needs of the aircraft, and the subsonic combustion chamber and the supersonic combustion chamber are both sub-combustion modes;

[0068] When the flight Mach number reaches the second Mach number, the inner constriction section adjustment surface and the expansion section adjustment surface of the sub-combustion flow channel and the super-combustion f...

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Abstract

The invention aims to overcome defects in the prior art, provides an air inlet channel for a double-combustion-chamber scramjet engine and an air inlet control method, and solves the technical problem about air inlet of wide-range non-axisymmetric double-combustion-chamber scramjet engines. The air inlet channel adopts the two-dimensional air inlet channel configuration and is divided by supporting plates in the flow direction to form at least one subsonic combustion flow channel and at least two supersonic combustion flow channels; the at least two supersonic combustion flow channels are evenly distributed on two sides of the at least one subsonic combustion flow channel; inner contraction section adjusting profiles and expansion section adjusting profiles are added in various flow channel designs, so that the area of a throat of the air inlet channel is controlled, the requirements of various combustion chambers for air with different compression degrees are met, the working Mach number range of the engine is broadened, the performance of the engine is improved, and the problem of difficulty in relaying with a turbine engine is solved.

Description

technical field [0001] The invention belongs to the technical field of aerospace engines, and relates to an air inlet of a dual combustion chamber scramjet engine and an air inlet control method. 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"...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/057F02C7/042F02K7/14
CPCF02C7/042F02C7/057F02K7/14
Inventor 马军侯金丽费立森赵文胜郭泽会王勇
Owner BEIJING POWER MACHINERY INST
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