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Gas turbine engine turbine nozzle bifurcated impingement baffle

一种隔板、分叉的技术，应用在燃气轮机发动机涡轮机喷嘴分叉冲击隔板领域，能够解决限制喷嘴段使用寿命等问题

Inactive Publication Date: 2011-11-23
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There is also a need for a turbine nozzle segment that avoids increased stress in the trailing edge vanes of paired vanes or other multi-blade nozzle segments that limit the service life of the nozzle segment

Method used

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  • Gas turbine engine turbine nozzle bifurcated impingement baffle
  • Gas turbine engine turbine nozzle bifurcated impingement baffle
  • Gas turbine engine turbine nozzle bifurcated impingement baffle

Examples

Experimental program
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Embodiment Construction

[0023] figure 1 An exemplary second stage turbine nozzle 4 of a high pressure turbine 2 of an aircraft gas turbine according to the present invention is shown in FIG. The nozzle 4 is arranged around a longitudinal or axial center axis 6 and comprises an annular housing 14 from which a plurality of nozzle segments 10 are mounted cantilevered. The nozzle section 10 is arranged between the rotor blades 18 of the first stage of the high-pressure turbine of the immediately upstream row and the rotor blades of the second stage of the turbine of the immediately downstream row 9 . First and second shrouds 97, 99 surround the first and second stage turbine rotor blades 18 and 9, respectively, and are supported by first and second shroud supports 77 and 79, which extend along the Radially inwardly is suspended by and connected to an annular casing 14 . The nozzle segment 10 is hooked to the first shroud support 77 by forward hooks 107 and cantilevered from the second shroud support 79...

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Abstract

A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.

Description

technical field [0001] The present invention relates to gas turbine engine turbine nozzle segments and, in particular, to nozzle segments having hollow vanes or airfoils with cavities for receiving cooling air distribution baffles. Background technique [0002] In a conventional gas turbine engine, air is compressed in a compressor and mixed with fuel in a combustor where it is ignited and combusted to produce hot gas. The generated gas flows down through a high pressure turbine (HPT) having one or more stages comprising one or more HPT turbine nozzles and rows of HPT rotor blades. The gas then flows to a low pressure turbine (LPT), which typically includes multiple stages with corresponding LPT turbine nozzles and LPT rotor blades. [0003] The HPT turbine nozzle includes a plurality of circumferentially spaced fixed hollow nozzle vanes secured between radially outer and inner band plates (or bands). Typically a single chamber impingement baffle is inserted into each holl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F01D5/08F01D5/18F01D9/00F01D9/04F01D25/12F02C1/02F02C7/16F02C7/18
CPCY02T50/676F05B2250/70F05D2250/70F05B2240/801F05D2260/201F05D2260/30F01D5/189F05B2260/201F01D9/041F05D2240/81F05B2260/30Y02T50/67Y02T50/60
Inventor J·J·彼得曼A·C·波维斯R·E·小麦克雷J·P·克拉克R·A·弗雷德里克E·E·吉布勒B·D·凯斯
Owner GENERAL ELECTRIC CO
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