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Thursday, October 15, 2020 | History

1 edition of Full-coverage film cooling heat transfer study found in the catalog.

Full-coverage film cooling heat transfer study

Full-coverage film cooling heat transfer study

summary of data for normal-hole injection and 30 ̊slant-hole injection

  • 261 Want to read
  • 3 Currently reading

Published by U.S. National Aeronautics and Space Administration, for sale by the National Technical Information Service in Washington, Springfield,Va .
Written in English

    Subjects:
  • Heat -- Transmission.,
  • Boundary layer.

  • Edition Notes

    StatementM. E. Crawford ... [et al.] ; prepared by Stanford University for Lewis Research Center.
    SeriesNASA contractor report ; NASA CR-2648, NASA contractor report -- NASA CR-2648.
    ContributionsCrawford, M. E., United States. National Aeronautics and Space Administration., Stanford University., Lewis Research Center.
    The Physical Object
    Pagination[1], 144 p. :
    Number of Pages144
    ID Numbers
    Open LibraryOL15209575M

    Get this from a library! Heat transfer to a full-coverage film-cooled surface with 30 ̊slant-hole injection. [M E Crawford; W M Kays; R J Moffat; United States. National Aeronautics and Space Administration.; Stanford University.; Lewis Research Center.] -- Heat transfer behavior was studied in a turbulent boundary layer with full coverage film cooling through an array of discrete holes and. Cooling Tower Thermal Design Manual Air Density: Lb/ft3 Air Specific Volume: ft3/Lb dry air Air Enthalpy: Btu/Lb dry air Download the example file () This file covers the examples of through Example

    Experimental results showed a heat transfer enhancement of upto 3 times at the highest Reynolds number compared to a smooth channel. Both the heat transfer and pressure drop increased with a decrease in the porosity from L1 to L2. The numerical results revealed formation of prominent vortical structures in the inter-unit cell spaces.   The superposition technique is used in conjunction with 2-D correlations developed in a previous study for single row of holes to obtain the heat transfer augmentation and film-cooling effectiveness for two staggered rows for dustpan shaped holes. The results are compared to data for multiple-row film-cooling.

    The previous phenomenon are largely highlighted and investigated in the literature. Early, Yan et al. (Yan, Lin, & Tsay, ) conducted an experimental study to examine the heat and mass transfer of the evaporative cooling of a falling liquid film. Water and ethanol liquid film were investigated in the study. The present study provides new effusion cooling data for both surfaces of full coverage effusion cooling plate. For the effusion cooled surface, presented are spatially-resolved distributions of surface adiabatic film cooling effectiveness, and surface heat transfer coefficients (measured using transient techniques and infrared thermography).


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Full-coverage film cooling heat transfer study Download PDF EPUB FB2

An Investigation of the Heat Transfer for Full Coverage Film Cooling [20] 18 Film Cooling Effectiveness for Injection from Multirow Holes [21] 18 Turbulence intensity effects on film cooling and heat transfer from compound angle holesAuthor: Justin Hodges. Full-coverage film cooling heat transfer study.

Washington: U.S. National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: M E Crawford.

-m 6d i w full-coverage film cooling heat transfer study - summary of data for normae-hqle injection and 30" slant-hole injection:loan copy: retljer*l a-z3 afwl technical libp 7 a i3-y m. cruwford, h. choe, kirthband afb, n. kdys, and r. j moffat prepared by stanford university. Full-coverage film cooling heat transfer study: Summary of data for normal-hole injection and 30 deg slant-hole injection Article (PDF Available) April with Reads How we measure 'reads'.

Advances in Film Cooling Heat Transfer layer thickness on film cooling effectiveness is evident also in other studies (see, e.g., [13]). For a round hole with compound angle injection, Al-Hamadi. It was hard to consider heat transfer near the film cooling hole using the one-dimensional approximation assumption.

In this study, conjugate heat transfer characteristics for full-coverage film cooling with jet impingement cooling, referred to as impingement/effusion cooling. Pêtre, Brice Dorignac, Eva and Vullierme, Jean Jacques Heat transfer model with two heat transfer coefficients along a multiperforated plate — Application to combustion chamber wall cooling.

Journal of Thermal Science, Vol. 12, Issue. 4, p. CrossRef; Google Scholar. heater-foil method for film cooling situations. By using this new method, the film cooling effectiveness and the heat transfer augmentation can be obtained simultaneously.

An analytical theory of this new method is developed. Experimental results on a flat plate with cylindrical film cooling holes are shown for two heater-foil configurations.

Discover the best Heat Transfer in Best Sellers. Find the top most popular items in Amazon Books Best Sellers. Free Convection Film Flows and Heat Transfer De-Yi Shang.

Hardcover. Advanced study institute book S. Kakac. Paperback # Heat Transfer out of 5 stars 2. Unknown Binding.

1 offer from $ #   To calculate the heat transfer coefficient in the film cooling configurations, it is more convenient to use the adiabatic wall temperature as a reference temperature: (3) h r = q r ″ T aw − T w where q r ″ is the local heat flux to the surface, h r is the heat transfer coefficient, and T w is the actual wall temperature with cooling.

This introduction to heat and mass transfer, oriented toward engineering students, may be downloaded without charge. The ebook is fully illustrated, typeset in searchable pdf format, with internal and external links. Download A Heat Transfer Textbook. Version.

Experimental Investigation on the Effect of Mainstream Turbulence on Full Coverage Film Cooling Effectiveness for a Turbine Guide Vane 10 January | Journal of Thermal Science, Vol.

28, No. 1 Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane. Film cooling is used in many applications to reduce convective heat transfer to a surface. Examples are the film cooling of gas turbine combustion chambers, vanes and blades which are subjected to high heat transfer from combustion gases [Metzger et al.

()]. For this study, new squealer tips called partial cavity tips, which combine the advantages of plane and squealer tips, were suggested, and the effects of the cavity shape on the tip heat transfer coefficient and film cooling effectiveness were investigated experimentally in a low-speed linear cascade.

Download multiple PDFs directly from your searches and from tables of contents; Easy remote access to your institution's subscriptions on any device, from any location; Save your searches and schedule alerts to send you new results; Choose new content alerts to be informed about new research of interest to you; Export your search results into file to support your research.

Effects that two different compound-angle film-hole configurations have on film cooling effectiveness are investigated. Effectiveness measurements have been made downstream of a single row of compound-angle cylindrical holes with a diameter of mm, and a single row of compound-angle, diffuser-shaped holes with an inlet diameter of mm.

Experimental study on the full-coverage film cooling of fan-shaped holes with a constant exit width International Journal of Heat and Mass Transfer, Vol.

Turbine platform phantom cooling from airfoil film coolant, with purge flow. An experimental study of heat transfer was conducted on a turbulent boundary layer with full-coverage film cooling through an array of holes inclined at 30 deg to the surface and 45 deg to the flow direction (compound-angle injection).

Heat transfer coefficients were measured over a range of injectant flows (M = 0 to M = ) and Reynolds numbers at velocities between and m/s. (e) Convection heat transfer due to air leakage through exterior walls. (f) Convection heat transfer within the porous insulating structure.

The surface heat transfer coefficients are affected by the nature of the air boundary layer which is strongly influenced by the. Based on the fundamentals of radiative heat transfer a correction method accounting for the specific boundary conditions accompanied by measurements in hot-gas ducts will be described.

Two examples of film cooling investigations, contoured single-hole coolant ejection and full-coverage film cooling, will be presented as typical applications of. Flow and heat transfer over a film cooled blade is not solved directly, instead convective heat transfer coefficients resulting from external convection on a similar blade without film cooling and under the same flow conditions are corrected by use of experimental data to incorporate the effect of film cooling in the heat transfer coefficients.

The.MPE Electronics Cooling 36 3. Basics of Heat Transfer This lecture is intended to refresh the post graduate students memory about the basics of heat transfer regarding the various modes of heat transfer, analogy between heat transfer and electric circuits, combined modes of heat transfer and the overall heat transfer coefficient.vection.

Characterization of the heat transfer coefficient is importa nt for determining the required cooling capa c-ity and corresponding internal properties of the product.

For this reason, a vast amount of work has been devoted to parameterize or model the heat transfer coefficient during spray cooling in different flow regimes [1] [2].