Steady and Unsteady Heat Transfer in a Film-Cooled Transonic Turbine Cascade

Abstract

The unsteady interaction of shock waves emerging from the trailing edge of modern turbine nozzle guide vanes and impinging on downstream rotor blades is modeled in a linear cascade. The Reynolds number based on blade chord and exit conditions (5 x 10(exp 6) and the exit Mach number (1.2) are representative of modern engine operating conditions. The relative motion of shocks and blades is simulated by sending a shock wave along of stationary shock waves. The blade geometry is a generic version of modern high turning rotor blade with transonic exit conditions. The blade is equipped with a showerhead film cooling scheme.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 2000
Accession Number
ADA381748

Entities

People

  • Oliver Popp
  • Tom Diller
  • Wing Ng

Organizations

  • Virginia Tech

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Computational Fluid Dynamics
  • Computational Science
  • Data Analysis
  • Energy Transfer
  • Equations
  • Film Cooling
  • Fluid Dynamics
  • Fluid Mechanics
  • Gas Turbines
  • Geometry
  • Guide Vanes
  • Heat Transfer
  • Mach Number
  • Pressure Measurement
  • Reynolds Number
  • Turbines

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.