Investigation of the I-40 Jet-Propulsion Engine in the Cleveland Altitude Wind Tunnel. 3 - Analysis of Turbine Performance and Effect of Tail-Pipe Design on Engine Performance
Abstract
Turbine-performance characteristics of an I-40 turbojet engine, installed in an airplane fuselage, were determined. A comparison of engine performance with three different tail pipes is also presented. The investigation was conducted over a range of simulated altitudes from 10,000 to 40,000 ft and a range of ram pressure ratios from 0.98 to 1.76. Turbine characteristics are presented as functions of turbine pressure ratio, corrected gas flow, and corrected turbine speed. Changes in corrected net thrust, corrected net thrust hp, and specific fuel consumption based on net thrust hp with three different tail pipes are discussed. A maximum turbine efficiency of approximately 0.835 was obtained. Turbine efficiency was unaffected by changes in altitude or tail-pipe designs, but varied with changes in ram pressure ratio. The most satisfactory engine performance was obtained with a constant-diameter tail pipe having a short nozzle at the outlet.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 26, 1948
- Accession Number
- ADA801508
Entities
People
- F. C. Foshag
- Richard P. Krebs
Organizations
- Glenn Research Center