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Performance and component frontal areas of a hypothetical two-spool turbojet engine for three modes of operation
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1955 |
| Description | Engine performance is better for constant outer-spool mechanical-speed operation than for constant inner-spool mechanical-speed operation over most of the flight range considered. Combustor and afterburner frontal areas are about the same for the two modes. Engine performance for a mode characterized by a constant outer-spool equivalent speed over part of the flight range and a constant outer-spool mechanical speed over the rest of the flight range is better that that for constant outer-spool mechanical speed operation. The former mode requires larger outer-spool centrifugal stresses and larger component frontal areas. |
| File Size | 1715566 |
| Page Count | 49 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930088846 |
| Archival Resource Key | ark:/13960/t18m21n0f |
| Language | English |
| Publisher Date | 1955-12-19 |
| 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 |
