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De-icing aircraft engine

A technology for aircraft engines and ice accumulation, applied in the direction of machines/engines, engine components, engine functions, etc., can solve problems such as adverse effects of system power, imbalance of engine components, quality changes, etc.

Active Publication Date: 2022-07-05
GULFSTREAM AEROSPACE CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This ice typically accumulates on rotating components, which can adversely affect system dynamics through increased ice mass
Also, because this ice buildup often releases unpredictably from time to time, and the mass changes, it can create an imbalance in the engine components, causing undesired vibrations

Method used

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  • De-icing aircraft engine
  • De-icing aircraft engine
  • De-icing aircraft engine

Examples

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Embodiment Construction

[0018] Example embodiments will now be described more fully with reference to the accompanying drawings. The present disclosure will now be described more fully with reference to the accompanying drawings, in which various embodiments of the invention are shown. The disclosed subject matter, however, may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. While embodiments of the present invention relate to engine configurations that include bypass flow around the engine, the expanded design space may include other rotating engine components subject to icing as well as engines configured to travel at supersonic and subsonic speeds.

[0019] refer to figure 1 , a propulsion system 10 is shown. The propulsion system 10 includes an engine 12 (in the figure 1 The middle cabin 8 is transparent). The engine 12 has rotatable blades or members 14 (such as figure 2 -5 best shown). The nacelle 8 includes a hood 13 whose ...

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PUM

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Abstract

In accordance with the present teachings, an aircraft engine configured to controllably de-ic during icing conditions is presented. The engine has a member operating at a first angular velocity, the member having a surface that is divided into a first ice accumulation surface configured to collect ice and a first protective surface configured to prevent ice collection. A first flange is provided between the first ice accumulation surface and the first protective surface.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS [0002] This application claims the benefit of US Provisional Patent Application No. 62 / 654,999, filed April 09, 2018, the disclosure of which is incorporated herein by reference in its entirety. technical field [0003] The present disclosure relates generally to aircraft engines, and more particularly to aircraft engines subject to icing, having structures that facilitate controlled shedding of icing. Background technique [0004] This section provides background information related to the present disclosure which is not necessarily prior art. Aircraft engines are subject to icing under predetermined loads, pressures and temperatures. This ice often accumulates on rotating components, which can adversely affect system dynamics through increased ice mass. In addition, because such ice deposits are often unpredictably released from time to time, and the masses vary, imbalances in engine components can result, resulting in und...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/70F04D29/00F04D29/38F02C7/00F01D25/02
CPCF04D29/703F04D29/002F04D29/38F02C7/00F01D25/02B64D15/16B64D2033/0233F05D2260/607F04D29/324F01D5/147
Inventor G·奥利维拉
Owner GULFSTREAM AEROSPACE CORP