Hypersonic vehicle turbine engine compartment cooling method and structure

Abstract

The invention provides a hypersonic aircraft turbine engine compartment cooling method which comprises the steps that a path of cooling air is led to an aircraft air inlet channel of a turbine engine from the rear side of a ram air turbine of a ram turbine power generation system, when the flight speed of the hypersonic aircraft is larger than the preset Mach number and the turbine engine is shut down and does not provide flight power, cooling air led to the aircraft air inlet channel from the rear side of the ram air turbine enters the engine compartment along the aircraft air inlet channel, so that heat of the engine compartment is taken away, the temperature of the engine compartment is controlled, and the service life of the hypersonic aircraft is prolonged. And the engine compartment of the turbine engine is cooled. The turbine engine compartment is cooled through ram air obtained after the ram air turbine in the turbine power generation system expands and is cooled, it can be guaranteed that accessory cables and the like in the turbine engine compartment have a safe and reliable thermal environment, and failure or damage caused by the high-temperature environment is avoided.

Description

technical field [0001] The present application belongs to the technical field of aero-engine thermal managers, and in particular, relates to a method and structure for cooling a turbine engine compartment of a super aircraft. Background technique [0002] The engine compartment is the environmental space where the engine is installed on the aircraft. The temperature of the engine compartment will rise due to the heat release of the engine surface. Therefore, it is necessary to control the temperature in the engine compartment through cold air, so that the accessories and cables installed on the engine surface are safe. working environment, and at the same time, avoiding the engine transferring a lot of heat to the aircraft, a process known as engine compartment thermal management. [0003] figure 1 Shown is a schematic diagram of engine compartment cooling of a typical small and medium bypass ratio turbine engine. The engine compartment 12 is cooled by the inlet ram air in ...

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Problems solved by technology

[0006] 1) The existing scheme of using ram air at the engine inlet to cool the turbine nacelle can only be used when the flying Mach number is below Ma3. Permissible temperature ranges for external accessories and cables, such as figure 2 shown;

[0007] 2) When the hyper-vehicle flies at high speed, the temperature of the incoming flow reaches a very high level due to the ramming effect. Although the inlet of the turbine engine is closed at this time, it is inevitable that leaked air enters the flow path of the turbine engine. At this time, the inside of the turbine engine The components of the fan part are in high temperature, which seriously endangers its life and safety

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