Variable-geometry supersonic velocity combustion chamber

A technology of supersonic combustion chamber and combustion chamber, which is applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of difficult sealing, complex structure, design of fixing device and cooling structure, etc.

Inactive Publication Date: 2018-09-28
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

But its structure is complex and difficult to seal
In 2003, F.Falempin et al. from MBDA of France and M.Goldfeld et al. from the Russian Institute of Theoretical and Applied Mechanics proposed a new simple fully variable geometry dual-mo...

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  • Variable-geometry supersonic velocity combustion chamber
  • Variable-geometry supersonic velocity combustion chamber
  • Variable-geometry supersonic velocity combustion chamber

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[0019] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS: The geometry of the combustion chamber is all expansion type within the range of Mach number 3.0-8.0. When the incoming flow velocity is lower, such as when the flight Mach number is 3.0, the center body on the lower wall is located at the rear of the combustion chamber, and there is a large expansion space between the center body and the isolation section. Due to the pressure increase caused by combustion in the combustion chamber, the airflow passes through the intake port and forms a normal shock wave in the isolation section. After the normal shock wave, the airflow decelerates to subsonic speed, and the combustion chamber is in a sub-combustion mode. The gas flow is accelerated to supersonic speed through the thermodynamic throat at the corner of the center body. At low flight Mach number, the center body of the lower wall is located in the rear position, so that there is a large expansion space for the combustion ...

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Abstract

The invention discloses the scheme of a variable-geometry supersonic velocity combustion chamber. In the range that the flight Mach number is 3.0-8.0, a combustion chamber geometrical configuration isvariable. Along with increasing of the flight Mach number, a combustion chamber center body forwards horizontally moves, the volume of a combustion chamber is reduced, and the pressure ratio is increased. On the contrary, along with reducing of the flight Mach number, the center body backwards horizontally moves, the volume of the combustion chamber is increased, and the pressure ratio is reduced. The situation that the inner pressure of the combustion chamber is increased, forward disturbance happens, and consequently, an air inlet way is not started is avoided.

Description

technical field [0001] The invention relates to the field of hypersonic engines, in particular to a concept of a variable geometry supersonic combustion chamber. Background technique [0002] At present, the research on hypersonic vehicles has been paid more and more attention by various countries, and has gradually become a hot field of research by major aerospace powers. As one of the options for hypersonic vehicles, the parallel TBCC combined engine has many advantages such as horizontal take-off and landing, reusability, etc. It can flexibly adjust the required thrust during the acceleration and cruise phases, and has a good application background. One of the main challenges is the efficient connection of speed and thrust between turbine engines and scramjets. At present, the upper limit of the maximum operating Mach number of the spot turbine engine is usually 2.2-2.5, and there are many challenges in raising the upper limit of its operation; while the lower limit of t...

Claims

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Application Information

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IPC IPC(8): F23R3/42
CPCF23R3/42
Inventor 李建平沈荻陈亮宋文艳金荣嘉焦贵谦周凤宇
Owner NORTHWESTERN POLYTECHNICAL UNIV
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