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)
Abstract
Seven firings of the J-2S rocket engine (S/N 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1970
- Accession Number
- AD0870534
Entities
People
- C. H. Kunz
- H. J. Counts Jr.
Organizations
- Arnold Engineering Development Complex