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Airfoils for a turbine engine and corresponding method of cooling

A turbine engine, airfoil technique applied at an angle close to the centerline of the tip surface. Fields that can solve problems such as shortened service life maintenance

Active Publication Date: 2019-06-14
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The airflow path may include one or more airflow elements for enhanced cooling, however, this element can lead to excessive accumulation of dust or particulate matter, reducing service life or requiring additional maintenance

Method used

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  • Airfoils for a turbine engine and corresponding method of cooling
  • Airfoils for a turbine engine and corresponding method of cooling
  • Airfoils for a turbine engine and corresponding method of cooling

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Embodiment Construction

[0013] The described embodiments of the invention are directed to holes, eg membrane holes, extending in passages through the tip of the airfoil. For purposes of illustration, the invention will be described in relation to a turbine for an aircraft gas turbine engine. However, it should be understood that the invention is not so limited and may have general application within engines (including compressors) as well as in non-aircraft applications such as other mobile applications and non-mobile industrial, commercial and residential applications. applicability.

[0014] As used herein, the terms "forward" or "upstream" refer to moving in a direction toward the engine inlet, or a component being relatively closer to the engine inlet than another component. The terms "rearward" or "downstream" used in conjunction with "forward" or "upstream" refer to a direction toward the rear or outlet of the engine, or relatively closer to the outlet of the engine than to another component. ...

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Abstract

An airfoil (90) for a turbine engine (10) comprises a wall bounding an interior (100) and defining a pressure sidewall and a suction sidewall, extending chord-wise from a leading edge to a trailing edge and span-wise from a root to a tip (92) defining a tip surface (140); an air flow channel (130) located within the interior (100) and having a portion (128) located adjacent the tip (92); and at least one hole (142, 144) extending through the tip (92) and having an inlet (146) fluidly coupled to the air flow channel (130), a diffusing outlet (148) located in the tip surface (140) including at least one tip rail (154, 156) extending radially from a tip floor (134), and a curvilinear passage (150) fluidly coupling the inlet (146) to the outlet (148), and the passage (150) adjacent the outlet(148) has a centerline (152) approaching the tip surface (140) at an angle ([theta]) less than 60 degrees. A corresponding method of cooling a tip is also disclosed therein.

Description

Background technique [0001] A turbine engine, and particularly a gas or combustion turbine engine, is a rotary engine that extracts energy from the flow of combustion gases passing through the engine onto a plurality of rotating turbine blades. [0002] Gas turbine engines for aircraft are designed to operate at high temperatures to maximize engine efficiency, so cooling of certain engine components such as the high and low pressure turbines can be beneficial. Cooling is typically achieved by piping cooler air from high and / or low pressure compressors to engine components requiring cooling. The temperature in the high pressure turbine is around 1000°C to 2000°C and the cooling air from the compressor is around 500°C to 700°C. Although the compressor air is hot, it is cooler relative to the turbine air and can be used to cool the turbine. [0003] Contemporary turbine blades generally include one or more internal air flow passages for directing cooling air through the blade t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/20F01D5/18
CPCF01D5/186F01D5/20F05D2250/71F05D2260/202F05D2260/607Y02T50/60F01D5/187F01D9/041F01D25/12F02K3/06F04D29/324F04D29/542F04D29/582F05D2220/323F05D2240/125F05D2240/307F05D2260/221F05D2260/232
Inventor 詹姆斯·迈克尔·霍夫曼
Owner GENERAL ELECTRIC CO
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