Anti-icing device and method for aviation gas turbine
A gas turbine and anti-icing device technology, which is applied in the cooling of gas turbine devices, jet propulsion devices, turbine/propulsion devices, etc., can solve problems such as low safety and reliability, poor anti-icing effect, and environmental pollution, so as to prevent Effects of freezing, saving resources, and increasing temperature
Active Publication Date: 2017-02-01
AECC COMML AIRCRAFT ENGINE CO LTD
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The disadvantage of method 4 is: the development process of the hydrophobic coating will bring environmental pollution, and the anti-icing effect is not good, a small amount of ice will fall off and hit the fan blades, the safety and reliability are low
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[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention. Embodiments of the present invention will be described in detail b...
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The invention relates to an anti-icing device and method for an aviation gas engine. The anti-icing device comprises a cover body, a first gas collection pipeline and a gas feeding pipeline. The cover body covers the outer side wall of a high-pressure turbine case, and the cover body and the high-pressure turbine case jointly form a sealing cavity. The first gas collection pipeline is provided with a gas collection opening and a gas outlet. The gas collection opening is formed in the downstream part of an outlet of an outer duct. The gas outlet is communicated with the sealing cavity. The gas feeding pipeline is provided with a gas inlet and a gas blowing opening. The gas inlet is communicated with the sealing cavity. The gas blowing opening penetrates a supporting plate and is arranged towards a cover hood. According to the anti-icing device and method, the working efficiency of an engine is not affected, waste gas is utilized again, waste is recycled, and resources are saved.
Description
technical field [0001] The invention relates to an aviation gas turbine, in particular to an anti-icing device and method for the aviation gas turbine. Background technique [0002] The air in the outer duct of the traditional large duct than the aviation gas turbine only passes through the fan, and the flow rate is slow and low temperature, so the inlet part is easy to freeze. The parts that are easy to freeze at the inlet part mainly include the cap, fan blades, and outer duct guides. Blades and struts etc. Icing can disrupt airflow, adversely affect gas turbine performance and efficiency, and, if displaced, damage gas turbine components. In order to prevent the inlet part of the aviation gas turbine from icing, the following methods are usually used at present: [0003] 1. Guide the hot air discharged from the outlet of the high-pressure compressor in the core machine into the cap to heat the outer surface of the cap. [0004] 2. Guide the hot air from the final stage ...
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IPC IPC(8): F02C7/047F02C7/18
Inventor 解亚东庞黎刚陈秋宏陈涛苏伟
Owner AECC COMML AIRCRAFT ENGINE CO LTD