NDLI: Influence of a Broken-Away TBC on the Flow Structure and Wall Temperature of an Effusion Cooled Multi-Layer Plate Using the Conjugate Calculation Method

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Bohn, Dieter Krewinkel, Robert
Copyright Year	2008
Abstract	Within Collaborative Research Center 561 “Thermally Highly Loaded, Porous and Cooled Multi-Layer Systems for Combined Cycle Power Plants” at RWTH Aachen University an effusion-cooled multi-layer plate configuration is investigated numerically by application of a 3-D in-house fluid flow and heat transfer solver, CHTflow. Previous conjugate calculations have shown a considerably decreased surface temperature for a hole geometry with a broken-away TBC, but could not attribute this effect conclusively to the decreased surface or the changed fluid flow conditions resulting from the changed outlet geometry. For this work, both conjugate calculations and calculations with adiabatic wall temperatures are conducted to analyse the flow in and around a hole with a fan-shaped outlet. The adiabatic calculations will exclude the effect of the solid body, making a quantification of its effects possible. The geometrical setup and the fluid flow conditions derive from modern gas turbine combustion chambers and bladings and are the same for both types of calculations. The numerical grid contains the coolant supply (plenum), the solid body for the conjugate calculations and the main flow area on the plate. The effusion-cooling is realized by finest drilled holes with a diameter of 0.2 mm that are shaped in the region of the thermal barrier coating. The flow field and the resulting temperature distributions on the hot gas surface will be discussed in detail for the two approaches, two blowing ratios and two different fan-shapes. Finally, the results will be discussed from the point-of-view of optimising the cooling effectivenss for effusion cooling geometries. The results will show that only for the smallest blowing ratio and the largest cooling hole exit area the decreased surface area of the TBC is the dominant factor.
Sponsorship	International Gas Turbine Institute
Starting Page	351
Ending Page	362
Page Count	12
File Format	PDF
ISBN	9780791843147
DOI	10.1115/GT2008-50378
e-ISBN	0791838242
Volume Number	Volume 4: Heat Transfer, Parts A and B
Conference Proceedings	ASME Turbo Expo 2008: Power for Land, Sea, and Air
Language	English
Publisher Date	2008-06-09
Publisher Place	Berlin, Germany
Access Restriction	Subscribed
Subject Keyword	Temperature distribution Computational methods Temperature Cooling Fluid dynamics Flow (dynamics) Wall temperature Geometry Gas turbines Thermal barrier coatings Coolants Shapes Combustion chambers Combined cycle power stations Heat transfer
Content Type	Text
Resource Type	Article

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