Anti-icing system and anti-icing control method of inlet lip of engine

Abstract

The invention relates to an anti-icing system of an inlet lip of an engine. The system comprises an air guiding tube, a pressure adjusting shut-off valve, a first temperature sensor, a second first temperature sensor and a controller, wherein an air inlet of the air guiding tube is connected on a high-pressure compressor to lead-in hot air of the high-pressure compressor while an air outlet of the air guiding tube is formed in a circular chamber of the inlet lip to release the hot air; the pressure adjusting shut-off valve is distributed on the air guiding tube and is used for adjusting the flow of the hot air in the air guiding tube; the first temperature sensor is distributed in a predetermined hottest region of the inlet lip of the engine; the second temperature sensor is distributed in a predetermined coldest region of the inlet lip of the engine; and the controller is electrically connected with the first temperature sensor, the second temperature sensor and the pressure adjusting shut-off valve and can be used for adjusting the openness of the pressure adjusting shut-off valve according to the temperature T1 sensed by the first temperature sensor and the temperature T2 sensed by the second temperature sensor, so that a covering of the inlet lip is not damaged and is not frozen by the temperature of the inlet lip.

Description

technical field [0001] The invention relates to an anti-icing system and an anti-icing control method for an engine intake port lip. Background technique [0002] When the aircraft is flying in icy weather conditions, icing may occur, especially the engine inlet is more likely to freeze under the action of engine suction. The icing of the air intake will reduce the effective air intake area of ​​the engine air intake, which may cause the engine thrust to drop and surge. Ice falling off may damage the engine fan blades, and seriously cause the engine to stall, affecting flight safety. At present, the engine inlets of civil aircraft are anti-icing with hot gas. According to the distribution method of hot gas inside the engine inlet, the anti-icing of the engine inlets of civil aircraft in service can be divided into flute tube configuration and swirl nozzle configuration. [0003] The representative model of the flute tube configuration is the B737. In this configuration, the...

AI Technical Summary

Problems solved by technology

The icing of the intake port will reduce the effective intake area of ​​the engine intake port, which may cause the engine thrust to drop and surge. Icing off may damage the engine fan blades, and seriously cause the engine to stall, affecting flight safety.

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