DESIGN AND EVALUATION OF A HIGH TEMPERATURE RADIAL TURBINE
Abstract
Radial turbines offer greater stage work capacity than axial turbines. If this advantage can be coupled with a capability of accommodating high turbine inlet temperatures, radial turbines will permit appreciable simplification of small gas turbine engines for use in future Army vehicles. The objective of the contract is to develop a technology for high temperature radial turbines to a level that will permit a potential small-engine manufacturer to make a choice between the radial and axial turbine. A two-year, two-phase program is being conducted involving the design and testing of a cooled, single-stage, radial-inflow turbine with the following design conditions: 2300F turbine inlet temperature, total-to-total aerodynamic efficiency of 87.5%, gas flow of 5 lb/sec, and stage work parameter of 42.5 Btu/lb. The first phase of the program involves a preliminary design of the cooled radial turbine, including development of cold flow data to permit design optimization.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 13, 1967
- Accession Number
- AD0664236
Entities
People
- G. S. Calvert
Organizations
- Pratt & Whitney