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Methods and apparatus for mounting a gas turbine engine

A technology for fastening devices and connecting rods, which is applied in gas turbine devices, safety devices, jet propulsion devices, etc., can solve the problems of increasing the total weight of the engine and reducing the overall efficiency of the engine.

Active Publication Date: 2005-01-26
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, increasing the strength of the connector assembly may undesirably increase the overall weight of the engine and / or reduce the overall efficiency of the engine when the engine is operating substantially without rotor imbalance

Method used

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  • Methods and apparatus for mounting a gas turbine engine
  • Methods and apparatus for mounting a gas turbine engine
  • Methods and apparatus for mounting a gas turbine engine

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0021] figure 1 is a perspective view of an exemplary gas turbine 10 including a known connector assembly 12 . Engine 10 includes an axial center axis extending from intake end 16 to exhaust end 18 . Engine 10 includes a fan assembly 20 , a high pressure compressor 22 and a combustor 24 . Engine 10 also includes a high pressure turbine (or turbine or turbine) 26 and a low pressure turbine 28 .

[0022] Connector assembly 12 includes a thrust link 30 and a pair of mounting lugs or yokes (or yokes) 32 and 34 . The upstream end 36 of the thrust link 30 is connected to the forward fan frame 38 by the mounting lug 32 , while the downstream end of the thrust link 30 is connected to the aft turbine frame 42 by the mounting lug 34 . Each mounting lug 32 and 34 includes a ball bearing (not shown) received in a clevis 44 formed at each thrust link end 36 and 40 . More specifically, the ball bearings enable the transfer of the engine's thrust load from the front fan frame 38 through ...

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PUM

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Abstract

A connector assembly (100) comprises a thrust link (102) and a clevis (120). The thrust link comprises a first end (124), a second end, and a body extending therebetween. The clevis is telescopically coupled to at least one of the thrust link first end and the second end such that a fuse element (168) extends between the clevis and the thrust link. The fuse element is positioned within a structural load path between the clevis and the thrust link, and is configured to fail when subjected to a predetermined load.

Description

technical field [0001] The present invention relates generally to a connection assembly, and more particularly to a method and apparatus for connecting a thrust link to a mounting lug. Background technique [0002] At least some known connection assemblies include a thrust link connected to a mounting lug or yoke to support the secondary structure. For example, the connection assembly may be used to support auxiliary structures such as a gear train or a turbine. The thrust links provide a load path through which engine thrust is transmitted to the aircraft pylon / wing structure. More particularly, the thrust link includes a clevis end sized to receive a ball bearing extending from the mounting lug. [0003] A gas turbine typically includes a rotor assembly, a compressor and a turbine. The rotor assembly includes a fan including a set of fan blades extending radially from the rotor shaft. The rotor shaft transmits power and rotational motion from the turbine to the compres...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/20B64D27/26F01D21/04F01D25/28F02C7/32F02K1/80
CPCY02T50/671B64D27/26Y10T403/32221Y10T403/32213F01D25/28F02C7/32F01D21/045F05B2240/9151F05B2260/3011B64D2027/268F02C7/20Y02T50/60
Inventor T·T·华莱士N·D·吉本斯M·J·皮尔斯C·H·戴克惠岑
Owner GENERAL ELECTRIC CO