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Combustion chamber of an rbcc engine with ramped rocket layout and its design method

A combustion chamber and slope-type technology, which is applied in the direction of combustion methods, combustion chambers, combustion equipment, etc., can solve the problem of unconstrained intake port type, so as to avoid the problem of starting multi-channel supersonic internal flow, and the combustion chamber channel is smooth and the channel smooth effect

Active Publication Date: 2020-10-16
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem solved by the present invention is: to overcome the contradiction that the rocket layout of the combustion chamber of the existing RBCC engine cannot take into account the high temperature and high enthalpy active jet flow of the rocket to realize the combustion chamber ignition and flame stability and the contradiction of the type of the inlet port. Based on the sloped rocket layout of the RBCC engine combustion chamber, the high-temperature, high-enthalpy active jet of the rocket can be used to realize the ignition of the combustion chamber, the dual flame stabilization scheme of the rocket jet and the rocket step, and is suitable for all types of inlets

Method used

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  • Combustion chamber of an rbcc engine with ramped rocket layout and its design method
  • Combustion chamber of an rbcc engine with ramped rocket layout and its design method
  • Combustion chamber of an rbcc engine with ramped rocket layout and its design method

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Embodiment 1

[0038] For RBCC combustion chambers in the Ma0-7 range:

[0039] (1) According to the design results of the air inlet, determine the combustion chamber inlet height H = 50mm, width W = 200mm;

[0040] (2) According to the entrance height H of the combustion chamber, the length of the isolation section is selected as L1 = 500mm; according to the calculation result of the boundary layer correction of the isolation section, the expansion angle of the isolation section is selected as α1 = 1.0°.

[0041] (3) According to the rocket thrust chamber size provided by the overall engine, determine the rocket installation slope length L2=200mm, compression angle ε1=11.4°, expansion angle ε2=11.4°;

[0042] (4) According to the length L2 of the rocket slope, the compression angle ε1, and the expansion angle ε2, the installation expansion angle α2 of the rocket slope is determined to be 5.7°;

[0043] (5) Determine the first-stage expansion section length L3=500mm, expansion angle α3=2.3 ac...

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Abstract

The invention discloses a rocket based combined cycle (RBCC) combustion chamber adopting a slope-type rocket layout mode, and a design method of the RBCC combustion chamber. The combustion chamber issequentially provided with an isolation section, a rocket slope mounting section and an expansion section from an air inlet to an outlet of gas generated by combustion. The isolation section, the rocket slope mounting section and the expansion section are sequentially arranged from the air inlet to the outlet of the gas generated by combustion. A rocket thrust chamber is mounted at the rocket slope mounting section, so that a rocket jet flow is in three-side contact with a stamping main flow and is located in front of a front peak of a fire flame of the expansion section, ignition and flame stability of the combustion chamber are achieved through the rocket jet flow, and the problem that through a step rocket layout mode, rocket high-temperature and high-enthalpy activity jet flow ignitionand flame stability cannot be effectively utilized is avoided.

Description

technical field [0001] The invention relates to a combustion device for a combined power system of a hypersonic vehicle, in particular to a combustion device for a rocket-based combined cycle (Rocket Based Combined Cycle, RBCC) engine to realize efficient conversion of fuel chemical energy into airflow internal energy. Background technique [0002] The layout of the rocket has an important influence on the structure, working range and performance of the combustion chamber of the RBCC engine. At present, there are two types of RBCC engine combustion chamber rocket layouts used at home and abroad: 1) stepped rocket layout, the rocket is arranged on one side of the combustion chamber, the rocket jet is in contact with the ram main stream on one side, and the two air flows are relatively decoupled aerodynamically , so that the design of the combustion chamber and the design of the intake port are relatively independent, which reduces the difficulty of designing the combustion ch...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/28
Inventor 刘昊张玫刘晓伟蔡锋娟张忠利豆飞龙张留欢
Owner XIAN AEROSPACE PROPULSION INST
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