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Strong pre-cooling aircraft propulsion system based on composite cooling of coolant and fuel

A technology of propulsion system and composite cooling, applied in the cooling of engines, jet propulsion, turbine/propulsion, etc., can solve the problems of high temperature, waste of fuel and low fuel quality, etc., and achieve the effect of being conducive to cooling

Active Publication Date: 2020-05-05
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In view of this, the present invention provides a strong pre-cooling aircraft propulsion system based on the composite cooling of coolant and fuel to solve the problem that when the aircraft flies at hypersonic speed, due to the high heat of the incoming airflow, the fuel cannot fully meet the cooling requirements as a heat sink The resulting waste of fuel, as well as the use of hydrogen and other low-volume heat sink fuels to carry coolant and fuel in a limited space, and the problems of low fuel quality and high temperature of combustion chambers, exhaust pipes and other components

Method used

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  • Strong pre-cooling aircraft propulsion system based on composite cooling of coolant and fuel
  • Strong pre-cooling aircraft propulsion system based on composite cooling of coolant and fuel
  • Strong pre-cooling aircraft propulsion system based on composite cooling of coolant and fuel

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Embodiment 1

[0069] The invention discloses a strong precooling aircraft propulsion system based on composite cooling of coolant and fuel. Wherein, the propulsion system of the aircraft includes a strong pre-cooling propulsion system, an air inlet 2 and a coolant cooling system.

[0070] The coolant cooling system includes a coolant pump 301 , a coolant regulating valve 302 and a front end cooler 303 .

[0071] The outlet of the air inlet 2 is in communication with the air inlet of the front end cooler 303, and the incoming air passes through the air inlet 2 and stagnates in temperature.

[0072] The inlet of the coolant regulating valve 302 is connected to the outlet of the coolant pump 301, the coolant inlet of the front end cooler 303 is connected to the outlet of the coolant regulating valve 302, and the coolant outlet of the front end cooler 303 is connected to the strong precooling propulsion system The central nozzle 102 of the front end cooler 303 is also connected to the main com...

Embodiment 2

[0076] like figure 1 As shown, in the second embodiment provided by the present invention, the strong precooling aircraft propulsion system based on the composite cooling of coolant and fuel in this embodiment and the strong precooling based on composite cooling of coolant and fuel in Embodiment 1 The structure of the propulsion system of the aircraft is similar, so the similarities will not be repeated, and only the differences will be introduced.

[0077] In this embodiment, a strong pre-cooling aircraft propulsion system based on composite cooling of coolant and fuel is specifically disclosed, which specifically includes an air inlet 2, a strong pre-cooling propulsion system and a coolant cooling system, wherein the strong pre-cooling system adopts an open In the circulation system, the strong precooling propulsion system includes the first fuel pump 103, the first regulating valve 104, the first circulation pump 105, the first strong precooler 106, the first strong precool...

Embodiment 3

[0087] like figure 2 As shown, in the third embodiment provided by the present invention, the strong precooling aircraft propulsion system based on the composite cooling of coolant and fuel in this embodiment and the strong precooling based on composite cooling of coolant and fuel in Embodiment 1 The structure of the propulsion system of the aircraft is similar, so the similarities will not be repeated, and only the differences will be introduced.

[0088] In this embodiment, a strong pre-cooling aircraft propulsion system based on composite cooling of coolant and fuel is specifically disclosed, which specifically includes an air inlet 2, a strong pre-cooling propulsion system and a coolant cooling system, wherein the strong pre-cooling system adopts a closed cycle system. The strong precooling propulsion system also includes a second fuel pump 112, a second regulating valve 113, a cooler 114, a pre-combustion chamber 115, a high temperature heat exchanger 116, a second stro...

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Abstract

The invention discloses a strong precooling aircraft propulsion system based on composite cooling of a coolant and fuel, and the strong precooling aircraft propulsion system is mainly used for hypersonic velocity flight with the Mach number being within the range of 0-6. According to the strong precooling aircraft propulsion system based on the composite cooling of the coolant and the fuel, a coolant cooling system is added in strong precooling propulsion systems of different types, a bypass stamping system is added according to operational requirements, a strong precooling / stamping-strong precooling combined circulation with the coolant and the fuel performing cooling in a composite manner is formed, so that the problems that the fuel is wasted due to the fact that the heat quantity of incoming air flow is large and the fuel serving as heat sink cannot fully satisfy the cooling demand in the hypersonic velocity flight, and the mass of the coolant and the fuel carried in a confined space is small due to the fact that hydrogen and other heat sink fuel of low specific volume are adopted are effectively solved, and meanwhile the coolant can also cool a combustion chamber, a tail jet tube and other high temperature components. By means of the strong precooling aircraft propulsion system based on the composite cooling of the coolant and the fuel, the performance of a precooling engine can be effectively improved, the speed domain range of the precooling engine can be effectively broadened, and efficient and reliable power is provided for a high speed aircraft with the flight Mach number being within the range of 0-6.

Description

technical field [0001] The invention relates to the technical field of hypersonic aircraft, in particular to a strong precooling aircraft propulsion system based on composite cooling of coolant and fuel used in the flight Mach number range of 0-6. Background technique [0002] The development of hypersonic aircraft is an important direction of aircraft development. When the aircraft flies at hypersonic speed, the temperature of the incoming air is too high after stagnating through the inlet, and due to the limitation of the compressor material, the compressor cannot directly compress the incoming air. At this time, the general Brayton cycle is no longer available. It is suitable for the aerodynamic thermal cycle of hypersonic engines. Therefore, humans try to change the aerodynamic thermal cycle mode in the engine to increase the flight Mach number, thrust, and specific impulse, and expand its flight envelope. Pre-cooling technology has thus been used. [0003] The hydrogen...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/12F02C7/141
CPCF02C7/12F02C7/141
Inventor 邹正平王一帆梁科陈懋章
Owner BEIHANG UNIV