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Title: Airfoil for a gas turbine

Abstract

An airfoil is provided for a gas turbine comprising an outer structure comprising a first wall, an inner structure comprising a second wall spaced relative to the first wall such that a cooling gap is defined between at least portions of the first and second walls, and seal structure provided within the cooling gap between the first and second walls for separating the cooling gap into first and second cooling fluid impingement gaps. An inner surface of the second wall may define an inner cavity. The inner structure may further comprise a separating member for separating the inner cavity of the inner structure into a cooling fluid supply cavity and a cooling fluid collector cavity. The second wall may comprise at least one first impingement passage, at least one second impingement passage, and at least one bleed passage.

Inventors:
 [1]
  1. Palm City, FL
Issue Date:
Research Org.:
Siemens Energy, Inc. (Orlando, FL)
Sponsoring Org.:
USDOE
OSTI Identifier:
1013057
Patent Number(s):
7871246
Application Number:
11/707,192
Assignee:
Siemens Energy, Inc. (Orlando, FL)
Patent Classifications (CPCs):
F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Liang, George. Airfoil for a gas turbine. United States: N. p., 2011. Web.
Liang, George. Airfoil for a gas turbine. United States.
Liang, George. Tue . "Airfoil for a gas turbine". United States. https://www.osti.gov/servlets/purl/1013057.
@article{osti_1013057,
title = {Airfoil for a gas turbine},
author = {Liang, George},
abstractNote = {An airfoil is provided for a gas turbine comprising an outer structure comprising a first wall, an inner structure comprising a second wall spaced relative to the first wall such that a cooling gap is defined between at least portions of the first and second walls, and seal structure provided within the cooling gap between the first and second walls for separating the cooling gap into first and second cooling fluid impingement gaps. An inner surface of the second wall may define an inner cavity. The inner structure may further comprise a separating member for separating the inner cavity of the inner structure into a cooling fluid supply cavity and a cooling fluid collector cavity. The second wall may comprise at least one first impingement passage, at least one second impingement passage, and at least one bleed passage.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2011},
month = {1}
}

Patent:

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