Wide-speed-range variable-cycle engine for driving low-pressure turbine rotor based on interstage combustion chamber

Abstract

According to the wide-speed-range variable-cycle engine for driving the low-pressure turbine rotor based on the interstage combustion chamber, firstly, the interstage combustion chamber is opened, a turbofan interstage afterburning cycle mode is started, the thrust of the engine is greatly increased, meanwhile, all the first mode selection valves are opened, and the second mode selection valve is closed; therefore, more air flow with high oxygen content enters the internal duct afterburner, an internal duct afterburner mode is started, and Ma0-2.5 + flight is realized. When Ma reaches 2.5-6, a turbine engine core engine is closed, meanwhile, first modal selection valves are all opened, a duct second modal selection valve at an inlet of an interstage combustion chamber is gradually opened, a part of air pressurized by a fan enters the interstage combustion chamber I through the second modal selection valve, a low-pressure turbine is driven to drive a fan A to rotate and pressurize, and the fan A is driven to rotate and pressurize; after air flow pressurized by the engine fan A enters the outer duct, the dual-mode ramjet engine is started and enters a stamping mode, and Ma2.5-6 flight is achieved.

Description

technical field [0001] The invention belongs to the field of aircraft power design, in particular to a supersonic aircraft power system with a wide flight envelope range, in particular to a wide-speed-range variable-cycle engine based on an interstage combustion chamber to drive a low-pressure turbine rotor. Background technique [0002] Existing traditional Brayton cycle / variable cycle turbine engines do not have high Mach number (Ma>2.5) flight capability due to flight envelope restrictions; the flight speed range of strong pre-cooling engines can meet the requirements of Ma0~6, but "backward" The problem of "dead weight" is prominent, the thrust-to-weight ratio is low, the technical difficulty is large, and the progress is slow; the sub-combustion / scramjet engine cannot meet the ground level take-off and landing requirements of the hypersonic aircraft; the rocket engine has a low specific impulse, cannot supersonic cruise, and is difficult to reuse; Turbine-based combi...

AI Technical Summary

Problems solved by technology

However, at present, the interstage supplementary combustion technology is still in the academic research stage at home and abroad, which is limited to the conceptual research, numerical calculation, and component test verification of the relevant components of the interstage combustion chamber. The variable cycle engine has not yet been developed, and its corresponding engine layout has not appeared and been published

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