NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Computations of the three-dimensional flow and heat transfer within a coolant passage of a radial turbine bladeA numerical code is developed for computing three-dimensional, turbulent, compressible flow within coolant passages of turbine blades. The code is based on a formulation of the compressible Navier-Stokes equations in a rotating frame of reference in which the velocity dependent variable is specified with respect to the rotating frame instead of the inertial frame. The algorithm employed to obtain solutions to the governing equation is a finite-volume LU algorithm that allows convection, source, as well as diffusion terms to be treated implicitly. In this study, all convection terms are upwind differenced by using flux-vector splitting, and all diffusion terms are centrally differenced. This paper describes the formulation and algorithm employed in the code. Some computed solutions for the flow within a coolant passage of a radial turbine are also presented.
Document ID
19910061174
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shih, T. I.-P.
(Carnegie Mellon University Pittsburgh, PA, United States)
Roelke, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Steinthorsson, E.
(Carnegie-Mellon Univ. Pittsburgh, PA, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1991
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 91-2238
Accession Number
91A45797
Funding Number(s)
CONTRACT_GRANT: NAG3-929
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available