Operating Characteristics of Turbojet Engines with Afterburners,
Abstract
With high-altitude, low-speed flight, pressures in certain types of afterburner chambers may be so low as to prevent ignition and stable fuel combustion; the larger the exhaust-nozzle exit cross-section area of the afterburner, the lower the pressure in the afterburner chamber, and the more difficult fuel ignition. Therefore, during afterburner startup, engine-control instruments, especially the gas-temperature indicator behind the turbine must be watched carefully, and the afterburner startup must be stopped when it exceeds the permitted maximum value. Emergency shotoff switches serve this purpose. In some aircraft types, the afterburner exhaust-nozzle exit area is not reduced automatically. If the exhaust-nozzle fails to close, aircraft flight and tactical characteristics deteriorate considerably. Since nominal and maximum rpm's are equal in modern engines, their thrust is increased by increasing gas temperature before the turbine and by changing the exhaust-nozzle exit cross-section area; it is recommended that such engines be run for 10 to 15 sec at maximum rate before starting the afterburner; thus the afterburner chamber is heated up and starting conditions are improved. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 27, 1969
- Accession Number
- AD0859552
Entities
People
- Henryk Rzewski
- Ryszard Bekiesinski
Organizations
- National Air and Space Intelligence Center