An Investigation of Turbine Blade/Disk Attachment Methods for Small, Cooled Gas Turbines
AIRESEARCH MFG CO OF ARIZONA PHOENIX
Pagination or Media Count:
The report describes the analytical, experimental, and developmental efforts that were conducted to design, fabricate, test, and evaluate turbine- rotor blade to rotor disk bladedisk attachment methods for an air-cooled turbine rotor in a small gas turbine engine. This investigation was launched because the combination of factors that are necessary to satisfy the design requirements of a small cooled gas turbine has made it increasingly difficult to utilize conventional blade attachment means. Specifically, the program was directed toward achieving a suitable attachment method for an axial turbine with an inlet temperature of 2400F, an airflow rate of 4.0 lbsec, a tip speed of 1500 ftsec, and matched to a compressor having a 101 pressure ratio. Detailed aerothermodynamic design activities were conducted to determine a turbine design that would provide optimum specific fuel consumption SFC and specific horsepower sp hp. A secondary purpose of the mechanical design and fabrication development activities was to study the feasibility of developing the strut- supported sheet metal blade shellstrut attachment that was revealed by the aerodynamic optimization study to be the most effective blade cooling configuration.
- Manufacturing and Industrial Engineering and Control of Production Systems
- Jet and Gas Turbine Engines