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1Effect of coolant temperature and mass flow on film cooling of turbine blades

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“Effect of coolant temperature and mass flow on film cooling of turbine blades” Metadata:

  • Title: ➤  Effect of coolant temperature and mass flow on film cooling of turbine blades
  • Author:
  • Language: English
  • Publisher: ➤  National Technical Information Service, distributor - National Aeronautics and Space Administration
  • Publish Date:
  • Publish Location: ➤  [Washington, D.C - Springfield, Va

“Effect of coolant temperature and mass flow on film cooling of turbine blades” Subjects and Themes:

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Access and General Info:

  • First Year Published: 1997
  • Is Full Text Available: No
  • Is The Book Public: No
  • Access Status: No_ebook

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    Stagnation temperature

    thermodynamics and fluid mechanics, stagnation temperature is the temperature at a stagnation point in a fluid flow. At a stagnation point, the speed of the fluid

    Temperature

    of temperature – Method to measure temperature quantitatively Sea surface temperature – Water temperature close to the ocean's surface Stagnation temperature –

    Stagnation pressure

    flow, the stagnation enthalpy or stagnation temperature plays a role similar to the stagnation pressure in incompressible flow. Stagnation pressure is

    Solar thermal collector

    the melting point of polypropylene is 160 °C (320 °F), while the stagnation temperature of insulated thermal collectors can exceed 180 °C (356 °F) if control

    Kiel probe

    A Kiel probe is a device for measuring stagnation pressure or stagnation temperature in fluid dynamics. It is a variation of a Pitot probe where the inlet

    Afterburner

    entry) temperature, resulting in a significant increase in engine thrust. In addition to the increase in afterburner exit stagnation temperature, there

    Rayleigh flow

    temperature, velocity and stagnation pressure are shown below, respectively. They are represented graphically along with the stagnation temperature ratio

    Total air temperature

    In aviation, stagnation temperature is known as total air temperature and is measured by a temperature probe mounted on the surface of the aircraft. The

    Compressible flow

    steady, and adiabatic flow of a perfect gas is assumed. Stagnation temperature and stagnation enthalpy are the same upstream and downstream of the shock

    Hypersonic speed

    total enthalpy (MJ/kg), total pressure (kPa-MPa), stagnation pressure (kPa-MPa), stagnation temperature (K), or flow velocity (km/s).[citation needed] Wallace