Double-duct pulse detonation engine and aircraft provided with same
A technology of pulse detonation and engine, which is applied in the direction of engine cooling, engine components, machines/engines, etc. It can solve the problems that the heat energy of the combustion tube cannot be effectively used, and the detonation combustion tube is easy to overheat, so as to improve the thermal efficiency of the cycle and improve Thrust, the effect of a simple overall structure
Active Publication Date: 2020-08-21
AECC HUNAN AVIATION POWERPLANT RES INST
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[0013] The present invention provides a double-duct pulse detonation engine and an aircraft with it, to solve the technical problems of the existing "pure" pulse detonation engine that the detonation combustion tube is easy to overheat and the heat energy of the combustion tube cannot be effectively utilized
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[0036] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.
[0037] refer to Figure 4 , the preferred embodiment of the present invention provides a double-duct pulse detonation engine, comprising: an engine housing, the engine housing is provided with an air inlet 101, an outer duct 102 and a tail nozzle 103 arranged in sequence along its axial direction The outer duct 102 is provided with an inner duct 104 and a detonation combustion chamber 105 sequentially arranged along its axial direction, and the intake end of the air intake duct 101 communicates with the atmosphere for the air to enter. The intake end of the outer duct 102 and the intake end of the inner duct 104 communicate with the exhaust end of the inlet duct 101 respectively, so that the air flow enters the outer duct 102 and the inner duct 104 respectively, a...
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The invention discloses a double-duct pulse detonation engine and an aircraft provided with the same. The engine comprises an engine shell. An air inlet channel, an outer duct and a tail spray channelare formed in the engine shell. An inner duct and a detonation combustion chamber are arranged in the outer duct. The air inlet end of the air inlet channel communicates with the atmosphere. The airinlet end of the outer duct and the air inlet end of the inner duct communicate with the exhaust end of the air inlet channel. The air inlet end of the detonation combustion chamber communicates withthe exhaust end of the inner duct, sot that airflow enters the detonation combustion chamber to participate in detonating combustion. The outer duct is used for leading the airflow to the outer peripheral wall of the detonation combustion chamber so as to cool the detonation combustion chamber. The air inlet end of the tail spray channel communicates with the exhaust end of the outer duct, the exhaust end of the detonation combustion chamber stretches into the tail spray channel, and accordingly, under the injection effect of combustion gas flow sprayed out of the exhaust end of the detonationcombustion chamber, heated airflow formed in the outer duct after the detonation combustion chamber is cooled is mixed with the combustion gas flow in an accelerated manner, thus forming mixed airflow which is to be sprayed out of the exhaust end of the tail spray channel in an accelerated manner.
Description
technical field [0001] The invention relates to the field of aero-engines, in particular to a double-duct pulse detonation engine. In addition, the present invention also relates to an aircraft comprising the above-mentioned double-duct pulse detonation engine. Background technique [0002] The pulse detonation engine is a new type of high-performance engine that can be used as a power plant for aerospace vehicles. At present, the pulse detonation engine is in the stage of research and exploration. The pulse detonation engine has higher thermal cycle efficiency (the constant pressure thermal cycle efficiency of the constant pressure engine is 27%, the constant volume thermal cycle efficiency of the constant volume engine is 47%, and the pulse detonation thermal cycle efficiency of the pulse detonation engine is 48%, pulse detonation engine (PDE) cycle, isovolumic cycle, isobaric cycle temperature entropy change comparison of ideal thermodynamic cycle as shown in the attache...
Claims
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IPC IPC(8): F02K7/02F02K3/00F02K1/06F02C7/04F02C7/14F02C7/22F02C7/266F01D25/26F01D9/02F01D15/10
CPCF01D9/02F01D15/10F01D25/26F02C7/04F02C7/14F02C7/22F02C7/266F02K1/06F02K3/00F02K7/02
Inventor 张坤陈亚农徐友良谭云杰王亮
Owner AECC HUNAN AVIATION POWERPLANT RES INST