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Performance of a small annular turbojet combustor designed for low cost
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Fear, J. S. |
| Copyright Year | 1972 |
| Description | Performance investigations were conducted on a combustor utilizing several cost-reducing innovations and designed for use in a low-cost 4448-N thrust turbojet engine for commercial light aircraft. Low-cost features included simple, air-atomizing fuel injectors; combustor liners of perforated sheet; and the use of inexpensive type 304 stainless-steel material. Combustion efficiencies at the cruise and sea-level-takeoff design points were approximately 97 and 98 percent, respectively. The combustor isothermal pressure loss was 6.3 percent at the cruise-condition diffuser inlet Mach number of 0.34. The combustor exit temperature pattern factor was less than 0.24 at both the cruise and sea-level-takeoff design points. The combustor exit average radial temperature profiles at all conditions were in very good agreement with the design profile. |
| File Size | 6641813 |
| Page Count | 41 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720009287 |
| Archival Resource Key | ark:/13960/t55f3kj2h |
| Language | English |
| Publisher Date | 1972-02-01 |
| Access Restriction | Open |
| Subject Keyword | Thermodynamics And Combustion Performance Tests Systems Engineering Cost Reduction Fuel Injection Combustion Chambers Atomizing Light Aircraft Turbojet Engines Stainless Steels 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 |
