An Investigation of Turbine Blade/Disk Attachment Methods for Small, Cooled Gas Turbines
Abstract
The report describes the analytical, experimental, and developmental efforts that were conducted to design, fabricate, test, and evaluate turbine- rotor blade to rotor disk (blade/disk) 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 lb/sec, a tip speed of 1500 ft/sec, and matched to a compressor having a 10:1 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 (shell/strut attachment) that was revealed by the aerodynamic optimization study to be the most effective blade cooling configuration.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1970
- Accession Number
- AD0867179
Entities
People
- F. Weber
- J. L. Helmbrecht
- R. F. Kirby