Experimental and computational studies of film cooling with compound angle injection Page: 3 of 31
This article is part of the collection entitled: Office of Scientific & Technical Information Technical Reports and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
Introduction and Objectives
The thermal efficiency of gas turbine
systems depends largely on the turbine inlet
temperature. Recent decades have seen a
steady rise in the inlet temperature and a
resulting reduction in fuel consumption. At
the same time, it has been necessary to employ
intensive cooling of the hot components.
Among various cooling methods, film cooling
has become a standard method for cooling of
the turbine airfoils and combustion chamber
walls. The University of Minnesota program
is a combined experimental and computational
study of various film-cooling configurations.
Whereas a large number of parameters
influence film cooling processes, this research
focuses on compound angle injection through a
single row and through two rows of holes.
Later work will investigate the values of con-
toured hole designs. An appreciation of the
advantages of compound angle injection has
risen recently with the demand for more
Research sponsored by the U.S. Department of
Energy's Morgantown Energy Technology Center, under
Contract 94-01-SR021 with University of Minnesota,
Mechanical Engineering Department, 111 Church St.,
SE., Minneapolis, MN 55455; fax: 612-624-1398
effective cooling and with improved under-
standing of the flow; this project should con-
tinue to further this understanding.
Approaches being applied include:
(1) a new measurement system that extends
the mass/heat transfer analogy to obtain both
local film cooling and local mass (heat) trans-
fer results in a single system, (2) direct mea-
surement of three-dimensional turbulent
transport in a highly-disturbed flow, (3) the
use of compound angle and shaped holes to
optimize film cooling performance, and (4) an
exploration of anisotropy corrections to turbu-
lence modeling of film cooling jets.
The outcome of this research will be
threefold. First, it will provide fundamental
scientific information in the form of detailed
measurements, computational results, and tur-
bulence model validation. Second, the results
of the experiments and computations will be
presented in a generalized form so that they
will be directly usable by design engineers in
industry. And finally, the experimental and
computational activities will be used to famil-
iarize graduate and undergraduate students
with the gas turbine industry. In the previous
year, research on the turbulence generation has
been conducted, test facilities for the experi-
ments have been designed and constructed,
Experimental and Computational Studies of Film
Cooling With Compound Angle Injection
R.J. Goldstein (firstname.lastname@example.org; 612-625-5552)
E.R.G. Eckert (612-625-8010)
S.V. Patankar (patan001 @maroon.tc.umn.edu; 612-625-6302)
T.W. Simon (email@example.com; 612-625-5831)
Heat Transfer Laboratory, Department of Mechanical Engineering
University of Minnesota
111 Church Street SE
Minneapolis, MN 55455
Here’s what’s next.
This article can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Article.
Goldstein, R.J.; Eckert, E.R.G.; Patankar, S.V. & Simon, T.W. Experimental and computational studies of film cooling with compound angle injection, article, December 31, 1995; United States. (digital.library.unt.edu/ark:/67531/metadc664212/m1/3/: accessed January 21, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.