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Effects of radial and circumferential inlet velocity profile distortions on performance of a short-length double-annular ram induction combustor
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Schultz, D. F. Perkins, P. J. |
| Copyright Year | 1972 |
| Description | Inlet air velocity profile tests were conducted on a full-scale short-length 102-centimeter-diameter annual combustor designed for advanced gas turbine engine applications. The inlet profiles studied include radial distortions that were center peaked, and tip peaked, as well as a circumferential distortion which was center peaked for one-third of the circumference and flat for the other two-thirds. An increase in combustor pressure loss was the most significant effect of the radial air velocity distortions. With the circumferential distortion, exit temperature pattern factor doubled when compared to a flat velocity profile. |
| File Size | 1932464 |
| Page Count | 46 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720012191 |
| Archival Resource Key | ark:/13960/t59d1q39v |
| Language | English |
| Publisher Date | 1972-03-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Flow Distortion Inlet Pressure Inlet Flow Temperature Profiles Velocity Distribution Combustion Chambers Combustion Efficiency Jet Engines 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 |
