TRANSONIC WIND TUNNEL FACILITY FOR TURBINE DURABILITY STUDIES
Abstract
The DURIP funding will be used to complete the construction of a high speed wind tunnel facility designed to test advanced turbine cooling concepts. Air Force and Navy aircraft operate under extreme conditions requiring that their gas turbine engines be extremely reliable and efficient. A critical aspect of the turbine engine operation is cooling the “hot section” of the engine. This cooling is achieved using air that bypasses the engine combustor and is fed into internal ducts in the blades and vanes of the turbine section of the engine. Ultimately this coolant air is exhausted through film cooling holes along the surface of the turbine airfoils providing a layer of cooler air protecting metal components from the hot gases exhausting from the combustor. Film cooling technology has been developed over many years, but continues to be a very active area of development.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Aug 12, 2021
- Source ID
- FA95502010109
Entities
People
- David Bogard
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Texas at Austin