skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

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) NETL
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. Tue . "Turbine airfoil with an internal cooling system having vortex forming turbulators". United States. doi:. 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 = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Dec 30 00:00:00 EST 2014},
month = {Tue Dec 30 00:00:00 EST 2014}
}

Patent:

Save / Share: