HIGH TEMPERATURE TURBINE COMPONENT DEVELOPMENT FOR USAAML SMALL GAS TURBINE ENGINE PROGRAM.
Abstract
The objective of the program is to advance and demonstrate high turbine temperature technology for small gas turbine engines. A transpiration cooled single stage axial flow turbine stage will be designed and tested to demonstrate feasibility of operation at 2500 F average turbine inlet temperature with a turbine work of 140 Btu/lb and a turbine airflow of 4 lb/sec. Separate discussions are presented for each heading in the statement of work. In those cases where either work on a given item has been previously completed or there is no activity during the reporting period, the work statement heading is omitted.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 15, 1965
- Accession Number
- AD0481017