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contributor authorR. S. Bunker
contributor authorD. E. Metzger
contributor authorS. Wittig
date accessioned2017-05-08T23:40:01Z
date available2017-05-08T23:40:01Z
date copyrightJanuary, 1992
date issued1992
identifier issn0889-504X
identifier otherJOTUEI-28617#211_1.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/111141
description abstractResults are presented from an experimental study designed to obtain detailed radial heat transfer coefficient distributions applicable to the cooling of disk-cavity regions of gas turbines. An experimental apparatus has been designed to obtain local heat transfer data on both the rotating and stationary surfaces of a parallel geometry disk-cavity system. The method employed utilizes thin thermochromic liquid crystal coatings together with video system data acquisition and computer-assisted image analysis to extract heat transfer information. The color display of the liquid crystal coatings is detected through the analysis of standard video chromanance signals. The experimental technique used is an aerodynamically steady but thermally transient one, which provides consistent disk-cavity thermal boundary conditions yet is inexpensive and highly versatile. A single circular jet is used to introduce fluid from the stator into the disk cavity by impingement normal to the rotor surface. The present study investigates hub injection of coolant over a wide range of parameters including disk rotational Reynolds numbers of 2 to 5 × 105 , rotor/stator spacing-to-disk radius ratios of 0.025 to 0.15, and jet mass flow rates between 0.10 and 0.40 times the turbulent pumped flow rate of a free disk. The results are presented as radial distributions of local Nusselt numbers. Rotor heat transfer exhibits regions of impingement and rotational domination with a transition region between, while stator heat transfer shows flow reattachment and convection regions with evidence of an inner recirculation zone. The local effects of rotation, spacing, and mass flow rate are all displayed. The significant magnitude of stator heat transfer in many cases indicates the importance of proper stator modeling to rotor and disk-cavity heat transfer results.
publisherThe American Society of Mechanical Engineers (ASME)
titleLocal Heat Transfer in Turbine Disk Cavities: Part I—Rotor and Stator Cooling With Hub Injection of Coolant
typeJournal Paper
journal volume114
journal issue1
journal titleJournal of Turbomachinery
identifier doi10.1115/1.2927988
journal fristpage211
journal lastpage220
identifier eissn1528-8900
keywordsHeat transfer
keywordsCooling
keywordsCoolants
keywordsRotors
keywordsTurbines
keywordsDisks
keywordsCavities
keywordsStators
keywordsFlow (Dynamics)
keywordsCoatings
keywordsLiquid crystals
keywordsFluids
keywordsTurbulence
keywordsReynolds number
keywordsRotation
keywordsBoundary-value problems
keywordsComputers
keywordsConvection
keywordsGas turbines
keywordsModeling
keywordsHeat transfer coefficients
keywordsData acquisition
keywordsGeometry AND Signals
treeJournal of Turbomachinery:;1992:;volume( 114 ):;issue: 001
contenttypeFulltext


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