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Method and apparatus for clearance control utilizing fuel heating

一种燃料、燃料管道的技术，应用在涡轮/推进装置的燃料加热、涡轮/推进装置的燃料控制、机械设备等方向，能够解决不具有调整冷却气体冷却容量等问题

Active Publication Date: 2015-10-14
GENERAL ELECTRIC TECH GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, passive controllers generally do not have the ability to adjust the cooling capacity of the cooling gas supplied to the turbine

Method used

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  • Method and apparatus for clearance control utilizing fuel heating
  • Method and apparatus for clearance control utilizing fuel heating
  • Method and apparatus for clearance control utilizing fuel heating

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0092] figure 1 A gas turbine 10 is shown having a compressor 12 , a combustor 14 and a turbine 16 . Inlet conduit 17 provides a passage for air entering the gas turbine and leading to the inlet to the compressor.

[0093] Gas turbines generate power by compressing air, mixing the compressed air with fuel 15 , combusting the mixture, and driving the turbine with the combustion gases. The turbine includes an annular casing 18 housing a row of turbine buckets 20 (also referred to as blades) rotating about an axis 23 . The buckets in each row are mounted on the turbine wheel 22 . Rows of stationary nozzles 24 (also referred to as guide vanes) are between rows of buckets. Hot combustion gases 27 (arrows visible) flow through the rows of buckets 20 and nozzles 24 in an annular hot gas passage 28 . The turbine casing 18 forms an outer surface of a hot gas passage 28 . The inner wall of passage 28 is close to the outer rim of impeller 22 .

[0094] A duct 23 for compressed air ...

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PUM

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Abstract

A clearance control apparatus providing compressed cooling air to a turbine casing in a gas turbine, the apparatus including: a cooling gas passage extending through an inner annular shell of the turbine casing; a cooling gas conduit connected to a compressor of the gas turbine and to the turbine casing, wherein the cooling gas conduit receives compressed air from the compressor and delivers the compressed air to the turbine casing, and wherein the cooling gas conduit is in fluid communication with the cooling gas passage, and a heat exchanger connected to the cooling gas conduit and to a fuel conduit delivering fuel to a combustor of the gas turbine, wherein the heat exchanger transfers heat from the cooling gas to the fuel.

Description

technical field [0001] The present invention relates to clearance control in turbines, such as gas turbines. Background technique [0002] Gaps in turbines typically refer to the size of the gap between the rotor and the stator housing surrounding the rotor. The rotor is typically an axial turbine having rows of buckets each mounted on a turbine wheel. The impeller is mounted on the shaft of the turbine. The stator housing houses the rotor and includes rows of stationary nozzles positioned between the rows of buckets. Gap generally refers to the annular gap between the tips of the buckets and the stator casing. [0003] The clearance is required to allow the buckets to rotate without rubbing against the stator casing. If the clearance is too large, combustion gases can leak over the tips of the buckets and not drive the rotation of the turbine. If the clearance is too small, the tip can rub against the stator housing and can cause vibrations that damage the turbine. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C9/28
CPCF01D11/24F02C7/185F02C7/224F02C6/08F05D2260/213F05D2260/221
Inventor H.G.小巴拉德D.F.比迪J.D.梅默
Owner GENERAL ELECTRIC TECH GMBH