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Gas Turbine Engine Bearing Oil Sump

A technology of gas turbine and bearing oil tank, which is applied in the direction of gas turbine devices, engine components, engine functions, etc., and can solve problems such as inconsistencies in the operating range of lubricating oil

Active Publication Date: 2019-12-03
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, the inventors of the present disclosure have discovered that there is an inconsistency between the maximum operating range of one or more bearings (derived as a function of the hardness of the material of the bearing or bearings) and the operating range of the lubricating oil

Method used

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  • Gas Turbine Engine Bearing Oil Sump
  • Gas Turbine Engine Bearing Oil Sump
  • Gas Turbine Engine Bearing Oil Sump

Examples

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Embodiment Construction

[0104] Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the figures. Similar or similar reference numerals in the drawings and description are used to indicate similar or similar parts of the present invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one element from another, and are not intended to denote the position or location of individual elements. importance.

[0105] Referring now to the drawings, wherein like numerals indicate like elements throughout, figure 1 is a schematic cross-sectional view of a gas turbine engine according to an exemplary embodiment of the present disclosure. More specifically, for figure 1 In one embodiment, the gas turbine engine is a high-bypass turbofan jet engine 10, referred to here...

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Abstract

A gas turbine engine has a core engine (16). The core engine (16) includes an inlet, a compressor section, a combustion section, a turbine section, and an exhaust port. The gas turbine engine also includes a bearing sump (104) disposed in the core engine (16) for containing a lubricant, the bearing sump (104) and the lubricant having an operating range of between at least about 0°F and about 550°F.

Description

technical field [0001] The subject matter generally relates to bearing sumps for gas turbine engines. Background technique [0002] A gas turbine engine generally includes a fan and a core arranged in flow communication with each other. The core of a gas turbine engine generally includes, in sequential order, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, at least a portion of the air passing over the fan is provided to the inlet of the core. This portion of the air is gradually compressed by the compressor section until it reaches the combustion section. Fuel is mixed with compressed air and incinerated in the combustion section to provide combustion gases. Combustion gases are sent from the combustion section through the turbine section to drive one or more turbines within the turbine section. One or more turbines within the turbine section may be coupled to one or more compressors of the compressor section via resp...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/06
CPCF02C7/06F01D25/16F05D2260/6022F01D25/18F05D2240/50F05D2260/98F01D25/125F01D25/20F01D25/183F02C7/28F02C3/04
Inventor K.R.斯诺B.W.米勒D.H.安斯蒂J.A.希茨M.E.H.森诺恩方宁
Owner GENERAL ELECTRIC CO