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Effects of rotation on coolant passage heat transfer. Volume 2: Coolant passages with trips normal and skewed to the flowAn experimental program was conducted to investigate heat transfer and pressure loss characteristics of rotating multipass passages, for configurations and dimensions typical of modem turbine blades. This experimental program is one part of the NASA Hot Section Technology (HOST) Initiative, which has as its overall objective the development and verification of improved analysis methods that will form the basis for a design system that will produce turbine components with improved durability. The objective of this program was the generation of a data base of heat transfer and pressure loss data required to develop heat transfer correlations and to assess computational fluid dynamic techniques for rotating coolant passages. The experimental work was broken down into two phases. Phase 1 consists of experiments conducted in a smooth wall large scale heat transfer model. A detailed discussion of these results was presented in volume 1 of a NASA Report. In Phase 2 the large scale model was modified to investigate the effects of skewed and normal passage turbulators. The results of Phase 2 along with comparison to Phase 1 is the subject of this Volume 2 NASA Report.
Document ID
19940011518
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Johnson, B. V. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Wagner, J. H. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Steuber, G. D. (Pratt and Whitney Aircraft East Hartford, CT, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1993
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.26:4396-VOL-2
NASA-CR-4396-VOL-2
E-6470-1
Accession Number
94N15991
Funding Number(s)
PROJECT: RTOP 505-62-61
CONTRACT_GRANT: NAS3-23691
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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