Heat exchanger assembly for a gas turbine engine

A gas turbine and heat exchanger technology, applied in indirect heat exchangers, heat exchanger types, heat exchanger shells, etc., can solve problems affecting engine performance, etc.

Inactive Publication Date: 2008-05-14
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this approach has an obvious disadvantage in that it creates an obstacle to smooth airflow, causing turbulence and pressure drop that negatively affects engine performance

Method used

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  • Heat exchanger assembly for a gas turbine engine
  • Heat exchanger assembly for a gas turbine engine
  • Heat exchanger assembly for a gas turbine engine

Examples

Experimental program
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Effect test

Embodiment Construction

[0017] FIG. 1 is a schematic diagram illustrating an exemplary gas turbine plant 10 having a longitudinal axis 11 . The gas turbine plant 10 includes a fan plant 12 and a central gas turbine 13 . The central gas turbine includes a high pressure compressor 14 , a combustor 16 , and a high pressure turbine 18 . In the example embodiment, the gas turbine plant 10 may also include a low pressure turbine 20 . The fan assembly 12 includes a series of fan blades 24 extending radially outward from a rotor disk 26 . Engine 10 has an inlet side 28 and an outlet side 30 . Gas turbine assembly 10 also includes a series of bearing assemblies (not shown in FIG. 1 ) that provide rotational and axial support for, for example, fan assembly 12 , compressor 14 , high pressure turbine 18 , and low pressure turbine 20 .

[0018] In operation, air flows through the fan assembly 12 and a first portion 50 of the airflow is directed through the compressor 14 where it is further compressed and input...

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PUM

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Abstract

The invention relates to heat exchanger device (130) for a gas turbine (10). The invention comprises a fan (12), a fan cover (42) which is used for basically limiting the fan, a central gas turbine (13), and a current divider (44) which is used for basically limiting the central gas turbine. Therefore, a by-pass pipe (40) is limited between the fan cover and a separator. The heat exchanger comprises an arc longitudinal inner plate (360), and an arc longitudinal outer plate (270) which is connected with the longitudinal inner plate. Therefore, a cavity (364) is formed between the longitudinal inner plate and the longitudinal outer plate, and at least part of an arc heat exchanger (300) is connected with the cavity. Therefore, the heat exchanger is connected with the fan cover, and the heat exchanger is positioned upstream or downstream from the fan.

Description

technical field [0001] The present invention relates generally to gas turbines, and more particularly to methods and apparatus for operating gas turbines. Background technique [0002] A gas turbine generally includes an inlet, a fan, low and high pressure compressors, a combustor and at least one turbine. The compressor compresses air, which is introduced into the combustion chamber where it is mixed with fuel. The mixture is then ignited to produce hot gas. The gas is introduced into a turbine which extracts energy from the gas to drive a compressor and generate useful work for propelling an aircraft in flight or for an electrical load such as a generator. [0003] When the engine is running, enormous amounts of heat are generated that raise the temperature of the engine system to unacceptable levels. These systems must be cooled to increase their life and reliability. One example is the use of lubrication systems to facilitate the lubrication of components in gas turb...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/14
CPCY02T50/675F02K3/06F02K3/115F01D25/125F02C7/14F28D1/0246F28F3/02F28F3/12F28F9/0075F28D7/005F28F1/022F28F1/04F28D2021/0049F28D2021/0021F28D1/024Y02T50/60
Inventor M·R·斯托拉奇K·R·利米B·尼尔
Owner GENERAL ELECTRIC CO
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