Accession Number : AD0510734

Title :   Injector/Chamber Scaling Evaluation Rocketdyne Injector Development.

Descriptive Note : Final technical rept. 17 Mar-26 Jun 69,

Corporate Author : AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CALIF

Personal Author(s) : Fleiszar,Mitchell J. , Jr. ; Powell,Michael F. ; Bornhorst,Bernard R. ; Grimes,Donald A. ; Powell,Patrick W.

Report Date : JUN 1970

Pagination or Media Count : 93

Abstract : This report describes the results of Rocketdyne modular injector development tests conducted. This project will study low cost injectors with a performance goal of 90 percent theoretical vacuum Isp (shifting equilibrium), 250K lbs thrust using N2O4/UDMH propellants, and will evaluate their potential for scalability up to the multi-million lb thrust class. A total of 39 tests were conducted. Several design configurations were evaluated which provided design data for demonstration injector tests scheduled to occur later in this project. A total of four injector and two chamber configurations were tested. Maximum performance obtained was approximately 91 percent of the test site theoretical shifting isp. (91.5 percent vacuum Isp). Dynamic combustion characteristics of this concept were evaluated by artificially inducing plenum chamber pressure overpressures of 100 percent or greater. Also a thermal bomb was detonated within a module to evaluate the combustion stability of a single module and to determine interaction effects upon the other six modules. In all perturbed tests, chamber pressure recovered to within 10 percent of the original value within 15 milliseconds. Although combustion stability rating data was not obtained on the highest performing injector, the basic design from which it was derived is dynamically stable. The candidate injector will be dynamically rated in future tests.

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, *FUEL INJECTORS), FUEL INJECTION, COMBUSTION CHAMBERS, THRUST, SPECIFIC IMPULSE, STABILITY, COMBUSTION, CAPTIVE TESTS, INTERIOR BALLISTICS, PERFORMANCE(ENGINEERING), INTERACTIONS, PRESSURE, THERMAL ANALYSIS, HEAT TRANSFER, SCALE (U) LAUNCH VEHICLES, NITROGEN OXIDES, TETROXIDES, DIMETHYL HYDRAZINE (1-1), SEGMENTED ROCKET ENGINES, ABLATION, COMBUSTION CHAMBER LINERS, COST EFFECTIVENESS

Subject Categories : Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE