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Effect of cooling-hole geometry on aerodynamic performance of a film-cooled turbine van tested with cold air in a two-dimensional cascade

a CPRE briefing.

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Published by Administrator in National Aeronautics and Space Administration, Scientific and Technical Information Office

    Places:
  • United States
    • Subjects:
    • National Aeronautics and Space Administration, Scientific and Technical Information Office


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      • Issued Mar. 1978.Includes bibliographical references.

        StatementNational Aeronautics and Space Administration, Scientific and Technical Information Office
        PublishersNational Aeronautics and Space Administration, Scientific and Technical Information Office
        Classifications
        LC Classifications1978
        The Physical Object
        Paginationxvi, 64 p. :
        Number of Pages83
        ID Numbers
        ISBN 10nodata
        Series
        1
        2NASA technical paper -- 1136.
        3NASA technical paper ; 1136

        nodata File Size: 9MB.


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Effect of cooling-hole geometry on aerodynamic performance of a film-cooled turbine van tested with cold air in a two-dimensional cascade by National Aeronautics and Space Administration, Scientific and Technical Information Office Download PDF EPUB FB2


[] performed a numerical simulation of a turbine blade with two rows of holes straddling the stagnation line. Flow conditions and aerodynamic losses were determined by vane-exit surveys of total pressure, static pressure, and flow angle. Improved performance can be achieved by operating the engine at higher pressure and temperature levels than previous designs. Thin film deposition processes were evaluated.

High efficiency film cooling, in the form of shaped film cooling and full coverage film cooling, is one of the most important cooling technologies.it is clear that the difference in incidence angle changes the adiabatic effectiveness predominantly in the showerhead region. In addition, a reduction of the thermal stress concentration can be obtained by increasing the height of the bulge configuration.

Infrared thermal images indicated the surface temperatures, and the OH - emission of the flame was used to visualize the limits of combustion.

supersonic film cooling: Topics by clubmap.com.hk

NUMBER OF PAGES 70 14. LES results are used to assess the applicability of basic assumptions of conventional eddy viscosity turbulence models used with Reynolds-averaged RANS approach, namely the isotropy of an eddy viscosity and thermal diffusivity. The wall is heated at a temperature value between the one of the jets and the one of the main flow. The study brings out the existance of an optimum gaseous film coolant injector configuration for which the effectiveness is maximum.

Inventor 1983-01-01 Thermal barrier coating systems were applied to hardware having passageways in the walls connecting apertures in the surface to a gas supply for film cooling. In accordance with the invention, a cooling fluid is injected into a hot flowing gas through a passageway in a wall which contains and is subject to the hot gas.

A series of measurements are performed using hot air as the core gas and gaseous nitrogen and water as the film coolants in a cylindrical test section simulating a thrust chamber. 1993-10-26 An apparatus for fabricating thin film materials utilizing high speed gas dynamics relies on supersonic free jets of carrier gas to transport depositing vapor species generated in a microwave discharge to the surface of a prepared substrate where the vapor deposits to form a thin film.

Oliver, Todd; Moser, Robert 2015-11-01 The combustor exit temperatures in modern gas turbine engines are generally higher than the melting temperature of the turbine blade material. The model of turbulence in the near wall region is the wall function method, and in the fully turbulent region is the k-epsilon model. Nusselt numbers increase only slic,htly but film cooling, effectiveness increases significantly with increasing, blowing ratio.

Results are also compared with the experimental data for all the blades. Two injectant mass flow rates with matched and unmatched pressure conditions using the database of Holden et al.

2016-01-01 While the effects of thermal barrier coating TBC thermal protection and air film cooling effectiveness for jet engine components are usually studied separately, their contributions to combined cooling effectiveness are interdependent and are not simply additive. EST; PBS stations check local listings The? Film cooling effectiveness of double rows of holes and each single row was used to study the accuracy of superposition predictions.

[], it has slowly been expanded upon in studies by Nathan et al.