Turbine/shock wave convergence detonation combination engine

Abstract

The invention provides a turbine / shock wave convergence detonation combination engine which comprises a binary-phase-shift geometric mixed pressure supersonic inlet (1), a gas turbine engine, a shockwave convergence detonation combustion chamber / engine (5) and a gas path adjusting system. The gas turbine engine comprises adjustable inlet guide vanes (2), a gas compressor (3), an adjusting plate (4), a gas distribution valve (6), a free turbine (7) and a spray pipe (8), the gas path adjusting system comprises the inlet (1), adjustable inlet guide vanes (2), an adjusting plate (4) and a gas distribution valve (6), structures and connecting modes of all portions of the gas turbine engine are usually used, and the gas turbine engine and the gas path adjusting system have common portions. Whenthe engine is at a low speed, the turbine drives the gas compressor to boost, and high-pressure air is provided for the detonation combustion chamber, namely, a shock wave convergence detonation turbine mixed engine mode is implemented. When the engine is at a high speed, the ram inlet provides high-pressure air for the detonation combustion chamber, the gas turbine engine quits working, and an air-breathing shock wave convergence detonation engine mode is implemented.

Description

technical field [0001] The invention belongs to the field of aero-engine combined design, in particular to a turbine / shock wave converging detonation combined engine, which is suitable for aviation combined power design. Background technique [0002] In order to meet the needs of high-speed flying weapons and equipment in near space, its power plant must be able to work normally within the range of Mach 0 to 4.5. As the main power plant of conventional aircraft equipment, the gas turbine engine can only work at Mach number below 2.5, and the sub-combustion and scramjet engines can only work at supersonic or hypersonic speeds. At present, there is no engine that can independently complete Horizontal take-off and landing, reusable propulsion missions for high-speed vehicles in near space. Internationally, the combination of two or more engines as the power for high-speed aircraft in near space has been studied for many years. The turbine-based ramjet combined engine (TBCC) i...

AI Technical Summary

Problems solved by technology

However, TBCC still has a series of problems that need to be studied and solved, such as high fuel consumption (low specific impulse), discontinuous thrust of turbine / ram mode conversion and low thrust-to-weight ratio, and TBCC under flight conditions of Ma=2~3 It is difficult to control the turbine / ram mode transition process, which makes it difficult to ensure continuous engine thrust

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