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Nacelle cooling and air inlet passage ice preventing compound device and turbofan engine

A compound device and air intake technology, which is applied in the direction of engine components, jet propulsion devices, gas turbine devices, etc., can solve the problems of engine performance degradation and achieve the effect of solving engine performance degradation

Active Publication Date: 2017-04-05
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, hot gas anti-icing must be bleed from the core of the engine, which will inevitably lead to a reduction in engine performance

Method used

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  • Nacelle cooling and air inlet passage ice preventing compound device and turbofan engine
  • Nacelle cooling and air inlet passage ice preventing compound device and turbofan engine
  • Nacelle cooling and air inlet passage ice preventing compound device and turbofan engine

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Embodiment Construction

[0033] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Apparently, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0034] In describing the present invention, it is to be understood that the terms "central", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", The orientations or positional relationships indicated by "top", "bottom", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rathe...

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Abstract

The invention relates to a nacelle cooling and air inlet passage ice preventing compound device and a turbofan engine. The nacelle cooling and air inlet passage ice preventing compound device comprises a circulation pipeline distributed in an air inlet passage cabin and a nacelle. Heat exchange liquid is arranged in the circulation pipeline in advance, flows in the circulation pipeline, sucks heat in the nacelle to lower the temperature in the nacelle and releases heat in the air inlet passage cabin to prevent the air inlet passage from being frozen. The nacelle cooling and air inlet passage ice preventing compound device can conduct ice preventing on the air inlet passage and can also conduct cooling fire preventing on the nacelle, in addition, the problem that the performance of the engine is reduced due to the fact that a heat air source of an engine core machine is extracted in the hot air ice preventing process of a traditional air inlet passage is solved, the problem that the performance of the engine is reduced due to the fact that outer culvert gas of the engine is extracted during ventilating cooling of a traditional nacelle is solved, and meanwhile the power supply load of the engine cannot be increased.

Description

technical field [0001] The invention relates to the field of turbofan engines, in particular to a composite device for nacelle cooling and air inlet anti-icing and the turbofan engine. Background technique [0002] The civil turbofan engine is installed in the nacelle. When working in icy weather conditions, because the air is in the state of suction in the intake passage, the airflow is decelerated and pressurized, and the static temperature is lowered, making the component extremely easy to freeze. The icing of the intake duct will change the aerodynamic characteristics of the intake system, reduce the thrust of the engine, increase the flow resistance, make the distribution of the intake air field uneven, increase the distortion of the flow field, and may cause engine surge in severe cases; the ice layer of the intake duct After falling off, it will be sucked into the engine with the air flow, which will not only damage the pressure fan and compressor blades, but even cau...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/047F02C7/14
Inventor 陈俊
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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