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Method and system for providing separation means for improved recovery of compressor discharge casing

A compressor exhaust and separation device technology, which is applied to components of pumping devices for elastic fluids, combustion methods, gas turbine devices, etc., and can solve problems such as low pressure recovery and acceleration

Active Publication Date: 2014-10-22
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compression of air produces localized acceleration and weak diffuse air flow, which causes low pressure recovery

Method used

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  • Method and system for providing separation means for improved recovery of compressor discharge casing
  • Method and system for providing separation means for improved recovery of compressor discharge casing
  • Method and system for providing separation means for improved recovery of compressor discharge casing

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Embodiment Construction

[0044] The methods and systems described herein facilitate improved compressor discharge casing (CDC) pressure recovery by generally aligning a fluid vortex about a longitudinal axis of a gas turbine engine.

[0045] As used herein, the terms "axial" and "axially" refer to directions and orientations extending generally parallel to the longitudinal axis of the gas turbine engine. Additionally, the terms "radial" and "radially" refer to directions and orientations extending generally perpendicular to the longitudinal axis of the gas turbine engine.

[0046] figure 1 is a side perspective view of an exemplary gas turbine engine 100 . In the exemplary embodiment, gas turbine engine 100 includes a compressor 102 , a combustor assembly 104 including a plurality of combustors 106 , and a turbine 108 arranged in series. The combustors 106 are spaced in an annular array extending about a shaft 110 extending between the compressor 102 and the turbine 108 and rotatably coupling the co...

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Abstract

A compressor assembly includes a compressor discharge casing (CDC) (114) including an annular wall (142) that extends generally axially along at least a portion of the CDC, the CDC configured to house a first combustor and a second combustor, and a splitter (148) extending from the annular wall between the first and second combustors, the splitter comprising a first surface (154) configured to direct fluid towards the first combustor and a second surface (158) configured to direct fluid towards the second combustor.

Description

technical field [0001] The subject matter disclosed herein relates generally to gas turbine engines, and more particularly to gas turbine engines including compressor assemblies with splitters. Background technique [0002] At least some known gas turbine engines direct air via a compressor assembly, and more specifically, via a compressor discharge casing (CDC) that encloses the combustor array. When air is directed through a CDC, the air is compressed between adjacent combustors and a vortex is formed along the meridian plane of the CDC. Compression of the air produces localized acceleration and weak diffuse air flow, which causes low pressure to return. Accordingly, a more efficient method and / or system for directing air through a compressor assembly is desired. Contents of the invention [0003] In one aspect, a method for assembling a gas turbine engine is provided. The method includes providing a compressor discharge casing (CDC) including an annular wall extendin...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/04F02C3/04
CPCF01D25/24F05D2240/12F05D2240/126F05D2250/712F05D2240/35F23R3/04F01D9/023F23R3/46F05D2250/33F02C3/145F02C3/14
Inventor M·M·耶尔穆尔C·G·肖特
Owner GENERAL ELECTRIC CO
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