Turbine Blade Tip Film Cooling Measurements
Abstract
In the design of gas turbine engines, the need to accurately know the heat transfer characteristics of the turbine blade tip is of extreme importance. The pressure differential between the pressure and suction side of the blade induces a strong secondary flow of hot combustion gases through the clearance gap between the turbine blade tip and shroud. This leakage flow is detrimental to the tip of the blade. In order to minimize this leakage flow, designers need to accurately know the heat transfer characteristics of the blade and blade tip so that dimensional changes may be accurately predicted. If dimensional changes are accurately known, the clearance gap and thus the secondary flow may be minimized and the overall thermal efficiency of the gas turbine engine increased. In addition, increased blade life is often achieved by cooling of the blade and blade tip.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1992
- Accession Number
- ADA267686
Entities
People
- Dean A. Ward
Organizations
- Air Force Institute of Technology