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Title: Cooling arrangement for a tapered turbine blade

Abstract

A cooling arrangement (11) for a highly tapered gas turbine blade (10). The cooling arrangement (11) includes a pair of parallel triple-pass serpentine cooling circuits (80,82) formed in an inner radial portion (50) of the blade, and a respective pair of single radial channel cooling circuits (84,86) formed in an outer radial portion (52) of the blade (10), with each single radial channel receiving the cooling fluid discharged from a respective one of the triple-pass serpentine cooling circuit. The cooling arrangement advantageously provides a higher degree of cooling to the most highly stressed radially inner portion of the blade, while providing a lower degree of cooling to the less highly stressed radially outer portion of the blade. The cooling arrangement can be implemented with known casting techniques, thereby facilitating its use on highly tapered, highly twisted Row 4 industrial gas turbine blades that could not be cooled with prior art cooling arrangements.

Inventors:
 [1]
  1. (Palm City, FL)
Issue Date:
Research Org.:
Siemens Energy, Inc. (Orlando, FL)
Sponsoring Org.:
USDOE
OSTI Identifier:
1012763
Patent Number(s):
7,762,774
Application Number:
11/639,961
Assignee:
Siemens Energy, Inc. (Orlando, FL) NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Country of Publication:
United States
Language:
English

Citation Formats

Liang, George. Cooling arrangement for a tapered turbine blade. United States: N. p., 2010. Web.
Liang, George. Cooling arrangement for a tapered turbine blade. United States.
Liang, George. Tue . "Cooling arrangement for a tapered turbine blade". United States. https://www.osti.gov/servlets/purl/1012763.
@article{osti_1012763,
title = {Cooling arrangement for a tapered turbine blade},
author = {Liang, George},
abstractNote = {A cooling arrangement (11) for a highly tapered gas turbine blade (10). The cooling arrangement (11) includes a pair of parallel triple-pass serpentine cooling circuits (80,82) formed in an inner radial portion (50) of the blade, and a respective pair of single radial channel cooling circuits (84,86) formed in an outer radial portion (52) of the blade (10), with each single radial channel receiving the cooling fluid discharged from a respective one of the triple-pass serpentine cooling circuit. The cooling arrangement advantageously provides a higher degree of cooling to the most highly stressed radially inner portion of the blade, while providing a lower degree of cooling to the less highly stressed radially outer portion of the blade. The cooling arrangement can be implemented with known casting techniques, thereby facilitating its use on highly tapered, highly twisted Row 4 industrial gas turbine blades that could not be cooled with prior art cooling arrangements.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2010},
month = {7}
}

Patent:

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