NDLI: Heat transfer on a film-cooled blade - effect of hole physics

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Heat transfer on a film-cooled blade - effect of hole physics

Content Provider	NASA Technical Reports Server (NTRS)
Author	Rigby, David L. Garg, Vijay K.
Copyright Year	1998
Description	A multi-block, three-dimensional Navier-Stokes code has been used to study the within-hole and near-hole physics in relation to heat transfer on a film-cooled blade. The flow domain consists of the coolant flow through the plenum and hole-pipes for the three staggered rows of shower-head holes on the VK1 rotor, and the main flow over the blade. A multi-block grid is generated that is nearly orthogonal to the various surfaces. It may be noted that for the VK1 rotor the shower-head holes are inclined at 30 deg. to the spanwise direction, and are normal to the streamwise direction on the blade. Wilcox's k-omega turbulence model is used. The present study provides a much better comparison for the heat transfer coefficient at the blade mid-span with the experimental data than an earlier analysis wherein coolant velocity and temperature distributions were specified at the hole exits rather than extending the computational domain into the hole-pipe and plenum. Details of the distributions of coolant velocity, temperature, k and omega at the hole exits are also presented.
File Size	969526
Page Count	14
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19980148005
Archival Resource Key	ark:/13960/t84j5f851
Language	English
Publisher Date	1998-03-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Heat Transfer Surface Cooling Navier-stokes Equation Coolants Sweat Cooling Film Cooling Velocity Distribution Heat Transfer Coefficients Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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