Loading...
Please wait, while we are loading the content...
Similar Documents
Performance of a vortex-controlled diffuser in an annular swirl-can combustor at inlet mach numbers up to 0.53
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Smith, J. M. |
| Copyright Year | 1979 |
| Description | A short, annular dump diffuser with suction stabilized vortices in the region of abrupt area change was tested with a full scale, annular swirl can combustor. The prediffuser area ratio was 1.4. Performance data were obtained for both isothermal and burning conditions at inlet temperatures of 589 to 895 K and pressures of 0.5 to 1.0 MPa for a range of diffuser inlet Mach numbers from 0.25 to 0.53. Suction rates were 0 to 20 percent of the total diffuser mass flow rate. Diffuser effectiveness increased from 47 percent without suction to approximately 80 percent for a total suction rate of 14 percent. Combustor total pressure loss for the same total suction rate was reduced from 6.8 percent without suction to 4.0 percent at an inlet Mach number of 0.40. |
| File Size | 663709 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790013928 |
| Archival Resource Key | ark:/13960/t7kq2t473 |
| Language | English |
| Publisher Date | 1979-04-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Flow Stability Suction Vortices Annular Nozzles Pressure Distribution Diffusers Combustion Chambers Performance Mach Number 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 |
