A jet device suitable for intake air precooling of high Mach number engines
A high Mach number, jet device technology, applied in the cooling of the engine, engine components, turbine/propulsion device, etc., can solve the problems affecting the normal flight of the aircraft, the shape change of the aircraft, the decrease of structural strength and rigidity, etc., and achieve improvement The effect of engine performance, simple internal structure, and good applicability to working conditions
Active Publication Date: 2019-12-24
HARBIN ENG UNIV
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Problems solved by technology
The heating degree of the high-temperature airflow to the aircraft increases with the increase of the flight speed. The high temperature is likely to cause the shape of the aircraft to change, and the structural strength and rigidity to decrease, thereby affecting the normal flight of the aircraft.
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[0019] The present invention is described in more detail below in conjunction with accompanying drawing example:
[0020] Referring to Figures 1-3, when the aero-engine is flying at a high Mach number, due to the gas viscosity and mutual friction, a high-temperature airflow 4 will be generated. At this time, the high-temperature airflow 4 enters the compressor 2 from the inlet 1. In order to reduce the incoming flow temperature, the fluidic device 3 is put into operation at this moment, as shown in Fig. 1 . Here, the fluidic device 3 is vertically arranged, and it is composed of two identical expansion joints up and down, and the number of joints of each expansion joint is two joints 8, 9, as shown in Fig. 2 . The high-speed, high-temperature airflow 4 enters the wall surfaces 10, 11 of the outer straight tube expansion part of the jet device 3, and enters the inner space of the jet device 3 through the air inlet 16; and the pre-cooling medium 14 is fixed downward through the ...
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The invention aims to provide a jet-flow device applicable to pre-cooling of fed air of a high-mach number engine. The jet-flow device comprises jet-flow units, wherein each jet-flow unit comprises anouter straight tube telescopic part and an inner straight tube telescopic part; the inner straight tube telescopic parts are positioned inside the outer straight tube telescopic parts and are coaxially arranged with the outer straight tube telescopic parts; both the outer straight tube telescopic parts and the inner straight tube telescopic parts are of telescopic structures of two or more sections; air inlets are formed in the walls of the outer straight tube telescopic parts; jet-flow holes are formed in the walls of the inner straight tube telescopic parts; a pre-cooling medium is introduced into the middle of each inner straight tube telescopic part in an axial direction of the inner straight tube telescopic part; every two jet-flow units form a group of jet-flow mechanisms; the jet-flow mechanisms are arranged inside an air feeding channel and positioned in front of an air compressor; the two jet-flow units of each group of the jet-flow mechanisms are arranged in the circumferential direction of the air feeding channel. By adopting the jet-flow device, situations that a very intense interference action is caused by direct contact of a pre-cooling medium jet-flow with a main air flow, and the jet-flow holes are blocked when the cooling medium is subjected to jet flow, can be avoided, and very good working condition applicability can be achieved.
Description
technical field [0001] The invention relates to an aero-engine device, in particular to an aero-engine air intake device. Background technique [0002] Facing the strategic needs of the 21st century, hypersonic flight technology is in a period of great development due to its potential huge strategic, tactical and economic value, and the demand for engines flying at high Mach numbers is gradually emerging. The aviation turbine engine can be considered as an ideal aircraft power under low Mach number flight conditions. It can use hydrocarbon fuels and has the advantages of high specific impulse, mature technology and high reliability. It is a very feasible way to carry out research on high Mach number flight based on aero turbine engine and air intake precooling technology. [0003] With the improvement of flight range and flight speed, aero-engines are facing a more demanding service environment. During the flight, each airflow layer with different velocity gradients produc...
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IPC IPC(8): F02C7/16
CPCF02C7/16
Inventor 张海林阿强郑群杨璐
Owner HARBIN ENG UNIV