Accession Number:

AD0870534

Title:

Altitude Developmental Testing of the J-2S Rocket Engine in Rocket Development Test Cell (J-4) (Tests J-4-1902-13 through J4-1902-15)

Descriptive Note:

Final rept.

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1970-06-01

Pagination or Media Count:

110.0

Abstract:

Seven firings of the J-2S rocket engine SN J-112-1C were conducted. The major objectives of these test periods were 1 to determine a method of increasing fuel turbine inlet temperature in order to prevent turbine icing and attain stable high thrust idle-mode operation, and 2 to demonstrate post-main-stage transition to low thrust idle model. Changes in injector mixture ratio during high thrust idle-mode operation from 1.55 to 2.02 increased inlet temperature, in general, from 85 to 190 deg F for the fuel turbine, and from 45 to 95 deg F for the oxidizer turbine. Stable high thrust idle-mode operation was attained on five firings which had fuel turbine inlet temperatures above 160 deg F. Satisfactory transition to post-main-stage low thrust idle mode was accomplished.

Subject Categories:

  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE