Accession Number:

ADP007687

Title:

Computation of 3D Viscous Flow and Heat Transfer for the Application to Film Cooled Gas Turbine Blades,

Descriptive Note:

Corporate Author:

DEUTSCHE GESELLSCHAFT FUER LUFT- UND RAUMFAHRT E V COLOGNE (GERMANY F R)

Personal Author(s):

• Vogel, Thorsten

Report Date:

1992-02-01

Pagination or Media Count:

12.0

Abstract:

The mechanism of film cooling and heat transfer on gas turbine blades and endwalls is theoretically investigated by simultaniously solving the 3D Navier-Stokes equations for the flow field and the 3D heat conduction equation for the cooled blade. The coupling of flow calculation and heat conduction calculation in the turbine blades supplies the wall temperatures and heat fluxes at the blade surfaces. These have to be taken from measurements if a traditional boundary layer approach is used for calculating the corresponding heat transfer coefficients. Heat transfer coefficients and film cooling efficiencies resulting from the 3D solution are presented. Additionally a comparison between measured and calculated data is shown.

Descriptors:

• *HEAT TRANSFER COEFFICIENTS
• *TURBINE BLADES
• *COMPUTATIONS
• *VISCOUS FLOW
• *THREE DIMENSIONAL FLOW
• APPROACH
• BLADES
• BOUNDARIES
• BOUNDARY LAYER
• COEFFICIENTS
• COMPARISON
• COOLING
• COUPLINGS
• EFFICIENCY
• EQUATIONS
• FILM COOLING
• FILMS
• FLOW
• FLOW FIELDS
• GAS TURBINE BLADES
• GAS TURBINES
• HEAT
• HEAT TRANSFER
• LAYERS
• MEASUREMENT
• NAVIER STOKES EQUATIONS
• SUPPLIES
• SURFACES
• TEMPERATURE
• TRANSFER
• TURBINES
• WALLS

Subject Categories:

• Fluid Mechanics
• Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE