Publication Date:
2019-07-13
Description:
A ground test was performed to determine the effects of compressor bleed flow extraction on the performance of F404-GE-400 afterburning turbofan engines. The two engines were installed in the F/A-18 High Alpha Research Vehicle at the NASA Dryden Flight Research Facility. A specialized bleed ducting system was installed onto the aircraft to control and measure engine bleed airflow while the aircraft was tied down to a thrust measuring stand. The test was conducted on each engine and at various power settings. The bleed air extraction levels analyzed included flow rates above the manufacturer's maximum specification limit. The measured relationship between thrust and bleed flow extraction was shown to be essentially linear at all power settings with an increase in bleed flow causing a corresponding decrease in thrust. A comparison with the F404-GE-400 steady-state engine simulation showed the estimation to be within +/- 1 percent of measured thrust losses for large increases in bleed flow rate.
Keywords:
AIRCRAFT PROPULSION AND POWER
Type:
NASA-TM-104247
,
H-1806
,
NAS 1.15:104247
,
AIAA PAPER 92-3092
,
AIAA Joint Propulsion Conference; Jul 06, 1992 - Jul 08, 1992; Nashville, TN; United States
Format:
application/pdf
Permalink
