A method and device for automatically deicing fan blades of an aviation turbofan engine
A turbofan engine and engine technology, applied in the direction of machines/engines, gas turbine devices, jet propulsion devices, etc., can solve the problems of increasing aircraft manufacturing and maintenance costs, eliminate the need for sensors and related circuits, increase reliability, reduce The effect of manufacturing and maintenance costs
Active Publication Date: 2021-05-04
COMAC +1
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- Description
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- Application Information
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Problems solved by technology
This device needs to add an additional sensor in the engine air intake. Due to the harsh environment near the air intake, the reliability and performance requirements of this additional sensor are very high, and additional electrical circuits, etc. need to be added accordingly, which increases the Overall manufacturing and maintenance costs of the aircraft
Method used
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[0018] The method and device for automatic de-icing of an aviation turbofan engine fan according to the present invention will be specifically described below in conjunction with the accompanying drawings, wherein the same components are marked with the same reference numerals.
[0019] figure 1 The prior art arrangement of the icing sensor 2 on the fuselage of the aircraft is shown. The icing sensor 2 is a device for the aircraft to detect icing. When the aircraft is flying under icing conditions, the vibration frequency of the probe will change greatly after the ice on the surface of the probe reaches the icing threshold. The icing threshold is typically about 0.5 mm (0.02 in), for example, but other values can also be selected according to external weather conditions or the aircraft's own parameters. At this time, the icing sensor 2 will send an icing signal to warn the driver to take anti-icing measures. In the embodiment shown, the aircraft is provided with two indepe...
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The invention relates to a method for automatically deicing a fan of an aviation turbofan engine. This method sends an instruction to adjust the engine N1 speed to the engine FADEC based on the signal of the icing sensor installed on the aircraft itself and the variation of the engine N1 vibration value, so as to automatically remove the ice accumulation on the fan blades. During the deicing process, when the specific stop conditions are met, the fan automatic deicing device sends an instruction to the engine FADEC to stop adjusting the thrust, so as to stop the engine fan from automatically deicing. This method reduces the burden on the pilot, and by using the existing icing sensor on the aircraft, the manufacturing and maintenance costs are reduced, and the reliability of the aircraft is increased. The present invention also relates to an automatic deicing device for an aviation turbofan engine fan. The device performs the deicing procedure according to the above method based on the change of the engine N1 vibration value and the icing signal sent by the original icing sensor on the aircraft.
Description
technical field [0001] The invention belongs to the field of aero-engines, and relates to a method and a device for automatically deicing a fan of an aero-turbofan engine, which is applicable to the scene where the fan blades of an aero-engine are icy. Background technique [0002] In aviation, when an aircraft encounters icing conditions in the air, engine fans may accumulate ice. When the engine fan freezes, it will not only directly lead to the destruction of the aerodynamic shape of the intake port, reduce the thrust of the engine, increase the flight load, but also may cause mechanical damage to the compressor, and even cause damage to the entire engine in severe cases, directly causing flight accident. [0003] The current technology is that when encountering icing conditions, the pilot always pays attention to the vibration value (that is, the amplitude of vibration) of the low-pressure rotor (hereinafter referred to as N1) of the engine. When the engine is running s...
Claims
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IPC IPC(8): F02C9/00
CPCF02C9/00
Inventor 尚洋何必海吴佳均吴君凤赵振可刘楠
Owner COMAC