Accession Number : AD0858917
Title : Propulsion System Integration and Test Program (Steady State). Part VI. YTF-33 Turbofan Engine Tests.
Descriptive Note : Technical rept. 9 Sep 68-3 Mar 69 on Phase 2,
Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV
Personal Author(s) : Boyd, Harry E., Jr
Report Date : JUN 1969
Pagination or Media Count : 191
Abstract : A test program to determine the effects of changing the fan-engine airflow split on the operating characteristics of a turbofan engine was conducted. Bypass ratio was varied by changing both the fan and the engine exhaust nozzle discharge areas independently. The effects of fan nozzle area variations on engine performance and engine nozzle area changes on fan performance were determined. The program also included determination of the response of the turbofan compressor components to pressure pulses input at the fan discharge. The effects of frequency and amplitude on the attenuation of the pressure pulse are discussed. The response of inlet airflow to pressure disturbances input at the fan discharge nozzle was investigated. (Author)
Descriptors : *JET FIGHTERS, *TURBOFAN ENGINES, PERFORMANCE(ENGINEERING), NOZZLE GAS FLOW, STALLING, GAS FLOW, EXHAUST NOZZLES, NOZZLE AREA RATIO, PRESSURE.
Subject Categories : Attack and Fighter Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE