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Inter-stage cavity purge ducts

A pipeline and turbine stage technology, applied in the field of gas turbine engine sealing components, can solve problems such as reduced service life

Inactive Publication Date: 2019-09-24
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Such ingestion can also reduce service life and / or cause failure of components in and around the interstage cavity

Method used

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  • Inter-stage cavity purge ducts
  • Inter-stage cavity purge ducts
  • Inter-stage cavity purge ducts

Examples

Experimental program
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Embodiment Construction

[0176] figure 1 Schematically illustrated in is a partial cross-sectional view of a highly simplified schematic illustration of an exemplary gas turbine engine low pressure turbine section 10 disposed substantially concentrically about an engine centerline 12 and following a high pressure turbine section 16 . Low pressure turbine section 10 rotates a fan section (not shown) and other components of the engine via a rotor shaft (not shown). Turbine section 10 includes alternating annular rows of nozzle vanes 26 and rotor blades 28 which are airfoils for acting on the flow of hot gases. Nozzle vanes 26 are attached to radially outer band 32 and radially inner ring or platform 30 to form a non-rotating annular nozzle stage 36 . The nozzle stage is suitably attached to and supported by the annular outer engine casing 38 . Each of the rotor blades 28 is attached at its radially inner end to the periphery of a disk 40 which is connected to the rotor shaft 18 .

[0177] Disk 40 inc...

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Abstract

The present invention relates to inter-stage cavity purge ducts. The inter-stage seal assembly includes annular seal land mounted inwardly of and to seal support ring and pre-swirlers in purge duct extending through land. Purge duct may be bounded by spaced apart duct walls and pre-swirlers include turning vanes in outer exhaust section. Purge duct may include plurality of enclosed purge passages circumferentially disposed around engine centerline and pre-swirlers include curved section in passages. Seal land may be bifurcated having forward and aft seal land sections and purge duct may include purge duct inlet located therebetween. Seal support ring may include flange attached to or integrally and monolithically formed with inner platform attached to nozzle vanes extending across turbine flowpath and exhaust section may be flush with platform. Labyrinth seal teeth mounted to turbine rotor may engage land, purge duct may extend between annular inlets and outlets, inlet may be between adjacent couple of seal teeth.

Description

technical field [0001] The present invention relates generally to gas turbine engine seal assemblies between turbine stator airfoils and blades, and more particularly to sealing or limiting losses due to leakage between hot gas paths and interstage cavities. Background technique [0002] In a typical gas turbine engine, air is compressed in a compressor and mixed with fuel and ignited in a combustor for generating hot combustion gases. The gas flows downstream through a high pressure turbine (HPT) having one or more stages including one or more HPT turbine nozzles, shrouds, and rows of HPT rotor blades. The gas then flows to a low pressure turbine (LPT) having one or more stages of corresponding LPT turbine nozzles and LPT rotor blades. Hot working gas from the hot gas path being drawn into the interstage cavity between the disks of adjacent LPT stages reduces engine performance and efficiency. Such ingestion may also reduce service life and / or cause failure of components ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F01D11/00F01D25/00F02C7/04
CPCF01D9/041F01D11/003F01D25/00F02C7/04F01D5/06F01D5/081F01D9/065F01D11/001F01D11/005F01D11/02F01D11/10F01D11/12F01D11/20F01D25/246F05D2240/55F16J15/444Y02T50/60F01D5/18F05D2250/71
Inventor T.E.伯多夫斯基A.M.马列克M.P.里卡拉A.基西亚克M.马诺哈兰Z.M.沙波夫斯基M.卡瓦尔科夫斯基
Owner GENERAL ELECTRIC CO
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