국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	THE EFFECTS OF COMPRESSOR SEVENTH-STAGE BLEED AIR EXTRACTION ON PERFORMANCE OF THE F100-PW-220 AFTERBURNING TURBOFAN ENGINE.
저자	Alison B. Evans
Keyword	Engine bleed; Engine performance; F100 engine; Thrust loss
URL	http://www.dfrc.nasa.gov/DTRS/1991/PDF/H-1677.pdf
보고서번호	NASA-CR-179447
발행년도	1991
출처	NASA Dryden Flight Research Center
ABSTRACT	A study has been conducted to determine the effects of seventh-stage compressor bleed on the performance of the F100 afterburning turbofan engine. The effects of bleed on thrust, specific fuel consumption, fan turbine inlet temperature, bleed total pressure, and bleed total temperature were obtained from the engine manufacturerchr(39)s status deck computer simulation for power settings of intermediate, partial afterburning, and maximum afterburning for Mach numbers between 0.6 and 2.2 and for altitudes of 30,000, 40,000, and 50,000 ft. It was found that thrust loss and specific fuel consumption increase were approximately linear functions of bleed flow and, based on a percent-thrust change basis, were approximately independent of power setting.