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Analysis of limitations imposed on one-spool turboprop-engine designs by compressors and turbines at flight mach numbers of 0, 0.6, and 0.8
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1956 |
| Description | Turbine centrifugal stress is a limiting factor for all flight conditions studied. This stress is more severe for sea-level operations than for subsonic flight at the tropopause. Turbines designed for a stress of 30,000 psi are capable of driving a light, compact, high-spedd compressor but only at high values of specific fuel consumption. An increase in turbine-inlet temperature is accompanied by an increase in turbine centrifugal stress. If stresses in excess of 50,000 psi can be tolerated, compressor aerodynamics may become a primary limitation. |
| File Size | 30271643 |
| Page Count | 68 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930089485 |
| Archival Resource Key | ark:/13960/t0rr6k860 |
| Language | English |
| Publisher Date | 1956-12-06 |
| Access Restriction | Open |
| Subject Keyword | Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
