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Air cooled turbine blade and corresponding method of cooling turbine blade

An air-cooled, turbine blade technology that addresses inefficiency issues such as blade support elements, air transport, and climate sustainability

Active Publication Date: 2015-06-03
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, limited by manufacturing constraints, these circuits are inefficient because the circuits carry cooling fluid through the center of the cavity where removing heat from the walls of the airfoil is inefficient

Method used

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  • Air cooled turbine blade and corresponding method of cooling turbine blade
  • Air cooled turbine blade and corresponding method of cooling turbine blade
  • Air cooled turbine blade and corresponding method of cooling turbine blade

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Embodiment Construction

[0017] Reference will now be made in detail to the provided embodiments, one or more examples of which are illustrated in the drawings. Each example is provided by way of illustration, not limitation, of the disclosed embodiments. In fact, it will be apparent to those skilled in the art that various modifications and changes can be made to the present embodiments without departing from the scope or spirit of the present disclosure. For example, features illustrated or described as part of one embodiment can be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and changes as come within the scope of the appended claims and their equivalents.

[0018] now refer to Figure 1-5 , depicting various embodiments of methods and apparatus for cooling gas turbine rotor blades. Exemplary turbine blades include a plurality of chambers defining a circuit for delivering high pressure compressor exhaus...

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Abstract

Apparatuses and methods are taught for cooling a turbine blade wherein at least one circuit is isolated along a cool suction side of the blade and the circuit turns aft toward a trailing edge.

Description

technical field [0001] The present embodiments relate generally to gas turbine engines, and more particularly, but without limitation, to methods and apparatus for cooling gas turbine engine rotor assemblies. Background technique [0002] In a gas turbine engine, air is pressurized in a compressor and mixed with fuel in a combustor to produce hot combustion gases that flow downstream through the turbine stages. These turbine stages extract energy from the combustion gases. A high pressure turbine includes a first stage nozzle and a rotor assembly having a disk and a plurality of turbine blades. The high pressure turbine first receives the hot combustion gases from the combustor and includes first stage stator nozzles which direct the combustion gases downstream through a row of high pressure turbine rotor blades from the first rotor The disk extends radially outward. In a two-stage turbine, the second-stage stator nozzles are positioned downstream of the first-stage blade...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/186F01D5/187F05D2250/185Y02T50/60F01D5/147F01D5/18F01D5/188F05D2260/20F05D2260/202F05D2260/203F05D2260/2212
Inventor S.M.莫尔特S.R.布拉斯菲尔德M.E.斯特格米勒S.M.皮尔森
Owner GENERAL ELECTRIC CO