Accession Number:

AD0860397

Title:

Altitude Developmental Testing of the J-2S Rocket Engine in Propulsion Engine Test Cell (J-4) (Tests J4-1902-05 through J4-1902-07)

Descriptive Note:

Final rept.

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1969-10-01

Pagination or Media Count:

105.0

Abstract:

Seven idle-mode firings of the J-2S rocket engine SN J-112-1 were conducted. The objectives of these firings were to determine the effect of restricting fuel bypass and thrust chamber film coolant flows on fuel density at the injector and idle-mode performance. Reduction of fuel bypass flow from 2 lbmsec to zero resulted in a 20-percent reduction in calculated fuel density at the injector reduction of film coolant flow from 1 lbmsec to zero apparently had no effect on calculated density at the injector. Essentially no performance differences were noted in engine steady-state, idle-mode performance because of reduction of these flows. No significant engine damage was sustained on any of the firings. Total accumulated engine idle-mode firing duration was 656.5 sec.

Subject Categories:

  • Liquid Propellant Rocket Engines
  • Ground Support Systems and Facilities for Space Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE