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

A variable-cycle engine and low-pressure turbine technology, which is applied in the direction of machines/engines, gas turbine devices, mechanical equipment, etc., can solve the problems that the engine layout has not appeared and is announced, and achieve the goal of increasing thrust, reducing fuel consumption and improving economy Effect

Active Publication Date: 2022-08-05
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Claims
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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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  • Wide-speed-range variable-cycle engine for driving low-pressure turbine rotor based on interstage combustion chamber

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Embodiment Construction

[0030] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are a part of the embodiments of the present invention, but not all of the embodiments, and are intended to be used to explain the present invention and should not be construed as a limitation of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0031] like figure 1 As shown, the wide-speed-range variable-cycle engine bas...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/04F02C3/14
CPCF02K3/04F02C3/14Y02T50/60
Inventor 张坤龚建波李丹杨光伟杜宇飞徐纲
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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