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Title: Turbine airfoil with an internal cooling system having vortex forming turbulators

Abstract

A turbine airfoil usable in a turbine engine and having at least one cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The configuration of turbulators may create a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance.

Inventors:
Publication Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1166773
Patent Number(s):
8,920,122
Application Number:
13/417,714
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Mar 12
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING

Citation Formats

Lee, Ching-Pang. Turbine airfoil with an internal cooling system having vortex forming turbulators. United States: N. p., 2014. Web.
Lee, Ching-Pang. Turbine airfoil with an internal cooling system having vortex forming turbulators. United States.
Lee, Ching-Pang. 2014. "Turbine airfoil with an internal cooling system having vortex forming turbulators". United States. https://www.osti.gov/servlets/purl/1166773.
@article{osti_1166773,
title = {Turbine airfoil with an internal cooling system having vortex forming turbulators},
author = {Lee, Ching-Pang},
abstractNote = {A turbine airfoil usable in a turbine engine and having at least one cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The configuration of turbulators may create a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance.},
doi = {},
url = {https://www.osti.gov/biblio/1166773}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Dec 30 00:00:00 EST 2014},
month = {Tue Dec 30 00:00:00 EST 2014}
}

Works referenced in this record:

Member having internal cooling passage
patent, March 1995


Turbine blade having offset turbulators
patent, October 1997


Gas turbine blade
patent, May 2001


Hot gas path component with mesh and turbulated cooling
patent, January 2006


Turbine blade frequency tuned pin bank
patent, March 2006


Offset Coriolis turbulator blade
patent, August 2006


Advanced turbulator arrangements for microcircuits
patent-application, September 2007


Angled tripped airfoil peanut cavity
patent-application, February 2009


Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method
patent-application, April 2009


Advanced Turbulator Arrangements for Microcircuits
patent-application, April 2009


Turbine Blades and Methods of Manufacturing
patent-application, June 2009


Crossflow Turbine Airfoil
patent-application, December 2009


Turbine Blade
patent-application, March 2010


System and Method for Generating Modulated Pulsed Flow
patent-application, March 2010


Turbine Blade with Micro Channel Cooling System
patent-application, July 2010