Hybrid exhaust aircraft engine

Abstract

The invention relates to a hybrid exhaust aircraft engine with a rear-mounted fan. The hybrid exhaust aircraft engine comprises an engine rotor, an inner housing, an outer housing, a main combustion chamber and an interstage combustion chamber which are formed in an inner culvert, and the rear-mounted fan, wherein an outer culvert is formed between the inner housing and the outer housing, and the inner culvert is formed in the inner housing; the engine rotor comprises a front-mounted fan rotor and a high-pressure compressor rotor which are positioned in front of the main combustion chamber, a high-pressure turbine rotor positioned between the main combustion chamber and the interstage combustion chamber, and a low-pressure turbine rotor positioned in the rear of the interstage combustion chamber; the rear-mounted fan is arranged in the rear of the low-pressure turbine rotor in the flowing direction of fluid, and comprises a plurality of fan blades and turbine blades which are arranged circumferentially and an annular margin plate connected with the turbine blades and the fan blades; and the fan blades are positioned in the outer culvert, and the turbine blades are positioned in the inner culvert.

Description

technical field [0001] The invention relates to a rear fan mixed exhaust aero-engine, in particular to a rear fan mixed exhaust aero-engine with an interstage combustion chamber. Background technique [0002] At present, only the F22 fighter jet can truly achieve supersonic cruise flight among military aircraft, although the bomber XB-70, attack aircraft A-12, and reconnaissance aircraft SR-71 can achieve supersonic flight with a Mach number up to 3 in the afterburner state , but according to the fourth-generation fighter standards, the use of the afterburner greatly reduces the stealth performance of the aircraft. The improvement of the performance of the aero-engine mainly depends on increasing the total pressure ratio of the compressor and increasing the temperature before the turbine. At present, the total pressure ratio of the F100-PW229 engine is close to 34, and the temperature before the turbine of the F119 can reach 2050K. Under the current technical conditions, fu...

AI Technical Summary

Problems solved by technology

The problems existing in the above inventions are the same as the CF700 engine. The fan blades are in the atmospheric environment, and the ambient temperature at high altitude is about minus 50 degrees, while the internal turbine blades have to withstand high temperatures above 500 degrees, so relatively high thermal stress is generated in the radial direction of the blades. At the same time Engines with separate exhaust usually have relatively large ducts, so the blades are longer. The centrifugal force generated during high-speed rotation will overwhelm the lower turbine blades. This is the reason why the CF700 has not been popularized, and it is also the reason why the separated exhaust engine adopts a rear fan structure. significant deficiency of

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