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Development of a thermal and structural analysis procedure for cooled radial turbinesA procedure for computing the rotor temperature and stress distributions in a cooled radial turbine is considered. Existing codes for modeling the external mainstream flow and the internal cooling flow are used to compute boundary conditions for the heat transfer and stress analyses. An inviscid, quasi three-dimensional code computes the external free stream velocity. The external velocity is then used in a boundary layer analysis to compute the external heat transfer coefficients. Coolant temperatures are computed by a viscous one-dimensional internal flow code for the momentum and energy equation. These boundary conditions are input to a three-dimensional heat conduction code for calculation of rotor temperatures. The rotor stress distribution may be determined for the given thermal, pressure and centrifugal loading. The procedure is applied to a cooled radial turbine which will be tested at the NASA Lewis Research Center. Representative results from this case are included.
Document ID
19880066937
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kumar, Ganesh N.
(Sverdrup Technology, Inc. Cleveland, OH, United States)
Deanna, Russell G.
(NASA Lewis Research Center; U.S. Army, Propulsion Directorate, Cleveland OH, United States)
Date Acquired
August 13, 2013
Publication Date
June 1, 1988
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 88-GT-18
Accession Number
88A54164
Distribution Limits
Public
Copyright
Other

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