Heat transfer to a full-coverage, film-cooled surface with compound-angle (30ê and 45ê) hole injection

Cover of: Heat transfer to a full-coverage, film-cooled surface with compound-angle (30ê and 45ê) hole injection | H. K Kim

Published by National Aeronautics and Space Administration, Scientific and Technical Information Office, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va .

Written in English

Read online

Subjects:

  • Boundary layer,
  • Film coefficients (Physics)

Edition Notes

Book details

StatementH.K. Kim, R.J. Moffat and W.M. Kays
SeriesNASA contractor report -- 3103
ContributionsMoffat, R. J, Kays, W. M., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Lewis Research Center
The Physical Object
Paginationviii, 150 p. :
Number of Pages150
ID Numbers
Open LibraryOL17978497M

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Heat transfer to a full-coverage, film-cooled surface with compound-angle (30 ̊and 45)̊ hole injection. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Office ; [Springfield, Va.: For sale by the National Technical Information Service], (OCoLC) Material Type.

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This site is like a library, Use search box in the widget to get ebook that you want. Heat transfer to a full-coverage, film-cooled surface with compound-angle (30 ̊and 45)̊ hole injection / H.K. Kim, R.J. Moffat and Heat transfer to a full-coverage. Kays. Heat transfer coefficients have been measured for film cooling injection from a single row of holes laterally directed with a compound angle of 60 deg.

Two hole configurations were tested, round holes and holes with a diffusing expansion at the by: "Experimental Evaluation of Large Spacing Compound Angle Full Coverage Film Cooling Arrays: Heat Transfer Augmentation." values are obtained experimentally with the use of temperature sensitive paint on constant flux heaters attached to full coverage film cooled surfaces as a function of blowing ratio.

The effects of blowing ratio, surface Author: Roberto Claretti, Greg Natsui, Jayanta S. Kapat, Michael E. Crawford, Glenn Brown, Ken Landis. Download heat transfer to a full coverage film cooled surface with thirty degree slant hole injection or read online books in Film-cooled surface with compound-angle book, EPUB, Tuebl, and Mobi Format.

Click Download or Read Online button to get heat transfer to a full coverage film cooled surface with thirty degree slant hole injection book now. This site is like a library, Use. Film cooling performance and heat transfer over an inclined film-cooled surface at different divergent angles with respect to highly turbulent mainstream Full Record Other Related Research.

Heat transfer to a full-coverage film-cooled surface with 30 degree slant-hole injection and a = 30°with and without a compound angle of 45°all with p/D = 5. Heat transfer to a full. Heat transfer to a full-coverage, film-cooled surface with compound-angle (30 ̊and 45)̊ hole injection / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Office.

Kays, W. (William Morrow): Heat transfer to a full-coverage, film-cooled surface with compound-angle (30 ̊and 45)̊ hole injection / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and.

Download Citation | Experimental Investigation on the Effect of Mainstream Turbulence on Full Coverage Film Cooling Effectiveness for a Turbine Guide Vane |.

This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. Convective heat/mass transfer near and within the entrance region of film cooling holes supplied with air from an internal duct (plenum) behind the cooling holes has been measured using a naphthalene sublimation technique.

The experiments are conducted for duct Reynolds number, based on the duct. Full text of "NASA Technical Reports Server (NTRS) Turbulent boundary layer on a full-coverage film-cooled surface: An experimental heat. FundamentalsNeed for Turbine Blade CoolingTurbine-Cooling TechnologyTurbine Heat Transfer and Cooling IssuesStructure of the BookReview Articles and Book Chapters on Turbine Cooling and Heat TransferNew Information from to ReferencesTurbine Heat TransferIntroductionTurbine-Stage Heat TransferCascade Vane Heat-Transfer.

The heat transfer coefficient of counterinclined film holes fed by different intake structures on the turbine vane leading edge (LE) model is experimentally investigated in this p.

Impingement Heat Transfer From Rib Roughened Surface Within Arrays of Circular Jet: The Effect of the Relative Position of the Jet Hole to the Ribs. Effects of Bulk Flow Pulsations on Film Cooling With Compound Angle Holes: Heat Transfer Coefficient Ratio and Heat Flux Ratio.

In Sung Jung, Joon Sik Lee, Film-Cooled Turbine Endwall in a Transonic Flow Field: Part II — Heat Transfer and Film-Cooling Effectiveness Part 1 — Endwall Heat Transfer and Total Pressure Loss. Skip to Main Content. This book, dedicated to Professor Franz Mayinger, contains a large selection of recent work on the application of optical techniques to heat and mass transfer.

The book is arranged in the form of a selection of technical papers sourced from high profile international workers in the field, including Durst, Goldstein and Whitelaw, to name a few. AbstractCharacteristics of full coverage film cooling of an adiabatic flat plate are studied for opposite injection of coolant at different angles.

Two in-line adjacent rows of cooling holes injecting in opposite directions are considered in this study.

The cooling performance is compared with the configurations having forward and reverse injecting holes at similar Author: Mukesh Prakash Mishra, A K Sahani, Sunil Chandel, R K Mishra. Turbine Tip and Shroud Heat Transfer and Loading: Part A — Parameter Effects Including Reynolds Number, Pressure Ratio, and Gas to Metal Temperature Ratio.

Home; Topics; Documents; Film Cooling Enhancement With Surface Restructure; of Share & Embed. AbstractDescribed in this paper is a numerical investigation on the concept for enhancing film cooling performance by placing vortex generator (VG) upstream the film hole.

Six film cooling configurations with different VG locations are investigated, including the distances for VG upstream the film hole (Upstream Distances) of 20 mm, 25 mm, and 30 mm and the VG Author: Daren Zheng, Xinjun Wang, Qi Yuan.

O Scribd é o maior site social de leitura e publicação do mundo. J C Han GT Heat Transfer Review - Free download as PDF File .pdf), Text File .txt) or read online for free. Jet Impingement Heat Trasnfer Review by JC Han.

Full-coverage film cooling. I - Comparison of heat transfer data for three injection angles. NASA Technical Reports Server (NTRS) Crawford, M. E.; Kays, W.

M.; Moffat. Film-Cooling Heat-Transfer Measurements Using Liquid Crystals. NASA Technical Reports Server (NTRS) Hippensteele, Steven A. Mani Project Report - Free download as Word Doc .doc /.docx), PDF File .pdf), Text File .txt) or read online for free.

mani project. The increase in the peak heat flux is then explained by the summation of the contributions of direct vaporization at the heated surface and the convective heat transfer caused by the bubble motion. Van Stralen showed that while the evaporation heat flux decreased with the addition of a solvent to water, the convective heat flux increased by a.

Film injection was found to have a minimal impact on heat transfer coefficients on the pressure surface while on the suction surface, the heat transfer coefficients show a significant increase.

Camci and Arts [47, 48] tested blades with a leading edge film cooling array and suction side film cooling in a short duration wind tunnel facility.

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