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Turbine band anti-chording flanges

一种凸缘、燃气涡轮的技术，应用在发动机制造、机器/发动机、发动机功能等方向，能够解决弦长长、损害导叶喷嘴节段耐久性等问题

Active Publication Date: 2017-02-22
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the long chord length of the belt and mounting structure can compromise the durability of multiple vane nozzle segments

Method used

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  • Turbine band anti-chording flanges
  • Turbine band anti-chording flanges
  • Turbine band anti-chording flanges

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0184] exist figure 1 A portion of an exemplary aircraft turbofan gas turbine engine 10 enclosed about a longitudinal or axial centerline axis 12 is schematically shown in . The engine 10 includes a fan 14 in continuous flow communication, a multi-stage axial high pressure compressor 16, an annular combustor 18, a high pressure turbine nozzle 20, a single stage high pressure turbine rotor 22, and one or more stages of a low pressure turbine nozzle 24 and a low pressure turbine nozzle 24. Turbine rotor 26. The high pressure turbine rotor 22 is coupled to the compressor 16 by a first shaft 21 and the low pressure turbine rotor 26 is coupled to the fan 14 by a coaxial second shaft 25 . During operation, ambient air 8 flows downstream through fan 14 , compressor 16 , exits compressor 16 as compressed air 28 , and then flows into combustor 18 . Compressed air 28 is mixed with fuel in combustor 18 and ignited to produce hot combustion gases 30 which flow downstream through turbine...

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PUM

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Abstract

The invention relates to a turbine band anti-chording flanges. A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.

Description

technical field [0001] The present invention relates generally to gas turbine engine turbine segments having flanges attached to bands, such as nozzle segments and shroud segments, and more particularly to the use of bands in such turbine segment shrouds. Chording. Background technique [0002] In a typical gas turbine engine, air is compressed in a compressor and mixed with fuel and ignited in a combustor to produce 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, a shroud, 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, shrouds, and LPT rotor blades. HPT and LPT turbine nozzles include a plurality of circumferentially spaced fixed nozzle vanes extending radially between outer and inner bands. Typically, each nozzle vane is a hollow airfoil through which ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F01D25/24F01D25/10
CPCF01D9/02F01D25/10F01D25/24F01D9/04F01D25/246F05D2240/11F05D2260/941F05D2240/91F01D9/041F01D25/005F05D2220/32F05D2240/128F05D2250/185F05D2260/2212F05D2260/22141F05D2300/50212
Inventor V.H.S.科雷亚B.K.科塞蒂M.布鲁默
Owner GENERAL ELECTRIC CO