Flat Plate and Turbine Vane Cascade Heat Transfer Investigation Using a Shock Tube.
Abstract
A shock tube was used to initiate boundary layer growth on a splitter plate at zero incidence. The heat transfer rate determined from a thin film semiconductor gage was compared to theoretical values for the flat plate heat transfer problem. Correlation between theoretical laminar and turbulent boundary layer equations and the experimental data for various shock Mach number flows showed excellent agreement. The shock tube was also used to generate high temperature gas flows which were allowed to pass through a turbine vane cascade. Thin film semiconductor and resistance gages provides temperature histories at four locations along the suction side of a turbine vane over a range of shock strengths. Heat transfer rates were determined from these temperature histories using a finite differencing scheme to approximate the energy equation for a semi-infinite solid. The rate of heat transfer along the suction side of the vane was shown to decrease with chordwise position from the stagnation point at the leading edge to the half chord position. At the three quarter chord position heat transfer rates were higher than the preceding chord points. Keywords: Schlieren photography; Boundary layer transition; Sonic flow. (Theses).
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1985
- Accession Number
- ADA163992
Entities
People
- Patrick K. Fillingim
Organizations
- Air Force Institute of Technology