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Title: Integrated circuit cooled turbine blade

Abstract

A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.

Inventors:
; ; ; ;
Publication Date:
Research Org.:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1377874
Patent Number(s):
9,745,853
Application Number:
14/840,572
Assignee:
SIEMENS ENERGY, INC. NETL
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2015 Aug 15
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Lee, Ching-Pang, Jiang, Nan, Um, Jae Y., Holloman, Harry, and Koester, Steven. Integrated circuit cooled turbine blade. United States: N. p., 2017. Web.
Lee, Ching-Pang, Jiang, Nan, Um, Jae Y., Holloman, Harry, & Koester, Steven. Integrated circuit cooled turbine blade. United States.
Lee, Ching-Pang, Jiang, Nan, Um, Jae Y., Holloman, Harry, and Koester, Steven. Tue . "Integrated circuit cooled turbine blade". United States. doi:. https://www.osti.gov/servlets/purl/1377874.
@article{osti_1377874,
title = {Integrated circuit cooled turbine blade},
author = {Lee, Ching-Pang and Jiang, Nan and Um, Jae Y. and Holloman, Harry and Koester, Steven},
abstractNote = {A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Aug 29 00:00:00 EDT 2017},
month = {Tue Aug 29 00:00:00 EDT 2017}
}

Patent:

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Works referenced in this record:

Gas Turbine Engines with Improved Leading Edge Airfoil Cooling
patent-application, April 2016


Turbine Airfoil Turbulator Arrangment
patent-application, November 2016