Small Axial Turbine Stage Cooling Investigation
Abstract
The report describes an investigation of advanced cooling concepts for the gas producer axial flow turbine of a small gas turbine engine. These concepts were directed toward minimizing the engine performance penalties, especially at part power, associated with conventional air cooling of the turbine. The initial phase consisted of a conceptual analysis of five stator and five rotor cooling concepts. The coolants for closed systems included liquid metal, high pressure gas, two phase H2O, heat pipe (two-phase liquid metal), and superheated steam. Modulated compressor air for transpiration cooling was also studied. To return the heat to the cycle, heat exchangers used in conjunction with the closed coolant systems utilized compressor exit air of fuels. Heat transfer analyses and preliminary designs were conducted on two selected turbine cooling concepts. The concepts selected as the most feasible included the closed systems using liquid metal or high pressure air for the stator and liquid metal or superheated steam for the rotor. Compressor discharge air was used as the heat sink for these systems. The effects of these systems on engine performance were also evaluated.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1971
- Accession Number
- AD0727741
Entities
People
- A. Sievers
- A. Stappenbeck
- H. Watts
- S. Moskowitz
- T. Dalton