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Improved high-temperature turbine nozzle with light decreasement by light reflection and manufactuirng process

A turbine nozzle and specular reflection technology, which is applied in the field of "passage", can solve the problems of easy failure and temperature rise of high-efficiency turbine nozzles, and achieve the effects of low average time, long component life, and shortened component life.

Inactive Publication Date: 2008-12-24
GENERAL ELECTRIC CO
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, even these tried and proven cooling methods reach their limits due to the continuously increasing temperature of the combustion process
In particular, the turbine nozzles of high-efficiency early-cycle turbine engines are prone to failure due to thermal degradation

Method used

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  • Improved high-temperature turbine nozzle with light decreasement by light reflection and manufactuirng process
  • Improved high-temperature turbine nozzle with light decreasement by light reflection and manufactuirng process
  • Improved high-temperature turbine nozzle with light decreasement by light reflection and manufactuirng process

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Embodiment Construction

[0043] According to the invention, a thin layer of specular optically reflective material with high temperature resistance is coated on components of the high heat portion of the gas turbine engine, which components form the boundaries of or are located in the gas flow path. These materials are applied with a smooth surface finish that reflects heat back into the fluid path and away from other high heat parts.

[0044] exist figure 1 A high bypass ratio aircraft gas turbine engine 10 is schematically shown in FIG. During operation, air passes through the fan 12 . A portion of the air bypasses the core of the engine and is used to create the thrust that propels the engine. A portion of the air is compressed to up to 10-25 times atmospheric pressure in the booster 14 and compressor 16 sections of the engine and is adiabatically heated to 800-1250°F in the process. This heated and pressurized gas is introduced into the combustion chamber portion 18 of the engine where it mixes...

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Abstract

A component for a high temperature gas turbine in a gas flow path (120) that is also a specular optical reflector. A thin layer of high temperature reflector (116) is applied to the gas flow path of the component, ie the surface of the component forming the hot gas boundary. The component typically includes a thermal barrier coating (114) laminated over the high temperature metal component, which allows the component to operate at elevated temperatures. The thermal barrier coating (114) must be polished to provide a surface that properly reflects radiation into the gas flow path. A thin layer of the high temperature reflector (116) is then applied to the polished thermal barrier coating (114) by a process capable of adequately bonding the reflector to the polished surface without increasing the surface roughness. )superior. This high temperature reflector (116) can be applied on any surface at the rear of the compressor, such as the turbine nozzle. The surface reflects radiation back into the flow path of the hot gas (120). The reflected radiation does not collect on any other components.

Description

technical field [0001] The present invention is related to the application No.10 / 335657 entitled "Improved high temperature splashback and its manufacturing process for reducing temperature by light reflection" filed at the same time as this application on December 31, 2002 (attorney file number is No. .13DV-13956), which application has been assigned to the assignee of the present invention and is incorporated herein by reference, and the present invention is also related to the application entitled "Reducing Improvement of temperature high temperature center body and its manufacturing process" Application No. 10 / 335647 (Attorney Docket No. 13DV-13957), assigned to the assignee of the present invention and incorporated herein by reference, The present invention also relates to Application No. 10 / 335442 entitled "Improved High-Temperature Combustion Chamber Wall and Manufacturing Process for Lowering Temperature by Light Reflection" filed simultaneously with this application o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/00F02C7/12F01D9/02F01D5/28F02K3/10F23M5/00F23R3/00F23R3/18F23R3/42
CPCF23M5/00F23M2900/05004F23R3/002Y02T50/60
Inventor J·F·阿克尔曼P·V·阿斯兹曼B·A·纳加拉N·B·朱斯蒂斯
Owner GENERAL ELECTRIC CO
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