Performance characteristics of LOX-H2, tangential-entry, swirl-coaxial, rocket injectorsDevelopment of a high performing swirl-coaxial injector requires an understanding of fundamental performance characteristics. This paper addresses the findings of studies on cold flow atomic characterizations which provided information on the influence of fluid properties and element operating conditions on the produced droplet sprays. These findings are applied to actual rocket conditions. The performance characteristics of swirl-coaxial injection elements under multi-element hot-fire conditions were obtained by analysis of combustion performance data from three separate test series. The injection elements are described and test results are analyzed using multi-variable linear regression. A direct comparison of test results indicated that reduced fuel injection velocity improved injection element performance through improved propellant mixing.
Document ID
19930038645
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Howell, Doug (NASA Marshall Space Flight Center Huntsville, AL, United States)
Petersen, Eric (NASA Marshall Space Flight Center Huntsville, AL, United States)
Clark, Jim (Pratt & Whitney Group West Palm Beach, FL, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-0228Report Number: AIAA PAPER 93-0228
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit