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Seal for a gas turbine engine

一种燃气涡轮、发动机的技术,应用在发动机的密封、发动机元件、燃气轮机装置等方向,能够解决弹性密封件破裂和破碎等问题

Pending Publication Date: 2021-05-11
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Prior art elastomeric seals such as W-seals suffer from failures such as cracking and crushing due to high temperature and pressure and relative displacement of adjacent components

Method used

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  • Seal for a gas turbine engine
  • Seal for a gas turbine engine
  • Seal for a gas turbine engine

Examples

Experimental program
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Embodiment Construction

[0022] Referring to the drawings, wherein like reference numerals refer to like elements throughout the various views, figure 1 An exemplary gas turbine engine 10 is shown. Although the example shown is a high bypass turbofan engine, the principles of the present invention are also applicable to other types of engines, such as low bypass turbofans, turbojets, turboprops, etc., and with any number of compressor turbines Spool of turbo engine. Engine 10 has a longitudinal centerline or axis 11 .

[0023] Note that as used herein, the terms "axial" and "longitudinal" both refer to a direction parallel to the centerline axis 11, while "radial" refers to a direction perpendicular to the axial direction, and "tangential" or "circumferential" Refers to directions that are mutually perpendicular to the axial and radial directions. As used herein, the term "forward" or "forward" refers to a relatively upstream location in the airflow through or around the component, and the term "re...

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PUM

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Abstract

A sealing apparatus for a gas turbine engine includes: a first component; a second component adjacent to the first component such that a cavity is defined between the first component and the second component; and a resilient seal disposed in the cavity to prevent gas flow between the first and second components. The resilient seal has a first contact surface contacting the first component and a second contact surface contacting the second component; wherein the resilient seal is configured to generate rolling movement in response to relative movement between the first and second components.

Description

technical field [0001] The present invention relates generally to seals in gas turbine engines, and more particularly to stationary seals in such engines. Background technique [0002] Gas turbine engines include multiple cavities between adjacent components that must be sealed to prevent gas leakage from one area to another within the engine. [0003] Oftentimes, adjacent components experience relative movement from a static position, for example due to thermal expansion. Typically, the cavity is sealed with an elastomeric seal comprising a relatively thin sheet of material formed into a cross-sectional shape having one or more bends. This type of seal is spring-like and flexible, and is able to deflect in response to component movement or pressure load to maintain ceiling contact. One known configuration of elastomeric seals has a W-shaped cross-section and is referred to as a "W-seal". [0004] Prior art elastomeric seals, such as W-seals, suffer from failures such as ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/28
CPCF02C7/28F16J15/0887F01D11/003F01D11/005F01D25/04F05D2240/59F05D2260/96F05D2240/55F05D2220/32
Inventor 拉温德拉·山卡尔·加尼格尔阿努斯瑞塔·雷乔杜里阿普斯特勒斯·卡拉菲利斯
Owner GENERAL ELECTRIC CO
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