A system for reducing the temperature of aero-engine film cold air by injecting external air

Abstract

The present invention proposes a system for reducing the temperature of air-film cold air in an aero-engine by injecting culvert air, including a high-pressure cooling medium storage container; a buffer mixing chamber; a suction port arranged on the wall of the engine outer duct; and located in the buffer mixing chamber The air film cold air inlet on the outlet pipeline is respectively connected with the air film cold air inlet of the hot end part of the engine; The port is connected with the buffer mixing chamber, and a regulating valve and a pressure and temperature sensor are installed on the pipeline connecting the outlet of the high-pressure cooling medium storage container and the high-pressure inlet of the ejector, and a pressure sensor is installed on the pipeline connecting the low-pressure inlet of the ejector and the suction port. There is a solenoid valve; a first controller connected to the regulating valve, pressure and temperature sensors, and a temperature sensor; and a second controller connected to the solenoid valve. The invention utilizes the ejector to realize the cooling of the hot-end components at the rear of the engine only by cooling the working medium at normal temperature.

Description

technical field [0001] The invention relates to a cooling system for a hot end part of an aero-engine, in particular to a cooling system suitable for film cold air of a hot-end part in an aero-engine. Background technique [0002] Aircraft infrared stealth is a problem that must be solved for future advanced aviation aircraft. Primary sources of infrared signals include hot parts of engines, exhaust plumes from nozzles, and the fuselage of the aircraft. Therefore, the current main method is to suppress the infrared signal by covering the heat-generating parts of the engine, cooling the exhaust, shrinking the plume, and using low-radiation surface coatings. [0003] The infrared signal from the rear end of the aircraft is mainly caused by the "hot parts" of the engine, that is, the center body of the nozzle, the inner wall and the rear end surface of the low-pressure turbine. The temperature of these components is between 450 and 700 °C. Especially when the engine is under ...

AI Technical Summary

Problems solved by technology

[0005] Although the use of liquid nitrogen cooling can quickly reduce the exhaust temperature and the temperature of the tail nozzle, but because the cold source is completely from low-temperature liquid nitrogen, the mass required to be carried is relatively large, and because the liquid nitrogen is in an extremely low-temperature state, the storage and maintenance costs are high

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