Accession Number : AD0371812

Title :   TURBINE ENGINE MISSION EFFECTIVITY COMPARISON.

Descriptive Note : Final rept.,

Corporate Author : NORTH AMERICAN AVIATION INC LOS ANGELES CALIF

Personal Author(s) : Barto ,Roger ; Fair,George

Report Date : APR 1966

Pagination or Media Count : 98

Abstract : Performance characteristics of a number of turbine engine cycles are compared on the basis of mission effectivity. 62 fixed cycles, covering a range of turbine inlet temperatures from 2200 to 3200 F, overall pressure ratios from 10 to 25, and bypass ratios from 0 to 4 are evaluated in a dual-mission V/STOL fighter. All cycles are afterburning turbojets or duct-burning turbofans. Best mission performance was achieved with a turbofan cycle with a bypass rationtemperature of 2700 F. This cycle was used as a basepoint for studying the effects of providing variability in the primary nozzle, fan stators, compressor stators, and turbine stators. Results of the study showed that, with cycle variability, takeoff gross weight could be reduced 7% with no loss in range for either the subsonic or supersonic mission. Alternately, if gross weight were held constant, subsonic range could be increased 6% and supersonic range 4.5 percent. Similar studies, but in much less depth, were conducted on preliminary designs for AMSA and SST aircraft. For AMSA, the combination of increased temperature and variability produced a gain of 17% in range for the supersonic mission but no gain for the subsonic mission. For the SST, an 18% increase in range was achieved by going from a 2200 F augmented turbojet to a 3200 F dry turbojet with variability. (Author)

Descriptors :   (*TURBOJET ENGINES, PERFORMANCE(ENGINEERING)), WEIGHT, PAYLOAD, RANGE(DISTANCE), MISSION PROFILES

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE