Variable-geometry supersonic velocity combustion chamber

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...

AI Technical Summary

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-mode scramjet scheme (PIAF shifting cover variable geometry ramjet concept), this solution brings difficulties to the design of the fixing device and the design of the cooling structure because the lower wall can move back and forth up and down

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