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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 | HathiTrust Digital Library |
|---|---|
| Author | Schultz, Donald F Perkins, Porter J |
| Editor | Donald F. Schultz Porter J. Perkins |
| Organization | United States. National Aeronautics and Space Administration. |
| 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 |
| Volume Number | D-6706 |
| Language | English |
| Publisher | National Aeronautics and Space Administration |
| Publisher Date | 1972-01-01 |
| Publisher Place | Washington D.C. |
| Access Restriction | Open |
| Rights License | Items in this record are available as Public Domain, Google-digitized. View the access and use profile at http://www.hathitrust.org/access_use#pd-google. Please see individual items for rights and use statements |
| Subject Keyword | Jet engines Combustion gases Aircraft gas-turbines |
| Content Type | Text |
| Resource Type | Book |
