Accession Number:

AD0253633

Title:

EFFECTS OF INJECTION LOCATION ON COMBUSTION INSTABILITY IN PREMIXED GASEOUS BIPROPELLANT ROCKET MOTORS

Descriptive Note:

Interim rept. no. 4

Corporate Author:

PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER

Personal Author(s):

Report Date:

1961-01-01

Pagination or Media Count:

89.0

Abstract:

Experiments reported were conducted for determining how basic injection variables influence high frequency combustion pressure oscillations in rocket motors. A gaseous bipropellant rocket motor burning ethylene and air as propellants was utilized. The three basic injection schemes included in the investigation were 1 injection at the head end of the motor, 2 injection at the side of the combustion chamber, and 3 injection at the nozzle end of the motor. The experiments indicated that the injection location and pattern have a profound effect on the mode and occurrence of combustion pressure oscillations. It was determined that the mode of oscillation could be predicted by choosing the right injector. Furthermore, combustion oscillations could be completely suppressed by injecting at the proper location. This latter location was different fon the different modes as would be expected.

Subject Categories:

  • Reciprocating and Rotating Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE