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Effects of Multiple Nozzles on Asymmetric Ejector PerformanceThis paper presents a comparison of a single nozzle and a dual nozzle strut based ejector. The results are focused on the fluid properties in the ejector duct. The research focused on choking mechanisms, mass flow entrainment, and mixing duct pressure distributions. The two ejectors were tests at equivalent primary mass flow rates. This corresponds to chamber pressures ranging from 100 psi to 900 psi in the single nozzle strut and 50 psi to 450 psi in the dual nozzle strut. Secondary flow was drawn from the lab at atmospheric pressure, and was not controlled. The secondary flow was found to choke at a value of 2.3 lb/s for a primary mass flow rate at approximately 2.1 lb/s for both ejectors. This choke was believed to be a mass addition choke rather than a traditional aerodynamic choke. The mixing duct pressure distribution exhibited two distinct trends at "low pressure" trend and at "high pressure" trend. For the low pressure trend, the mixing length for the ejectors remained fixed around 20 inches, regardless of the chamber pressure. For the higher pressure trend, the mixing length was considerably longer and increased with increasing chamber pressure. At high chamber pressures (high mass flow rates), a supersonic core flow was present at the exit of the duct. For these cases, the two streams did not have time to mix by the end of the duct.
Document ID
20050204030
Acquisition Source
Marshall Space Flight Center
Document Type
Preprint (Draft being sent to journal)
Authors
Lineberry, D.
(Alabama Univ. Huntsville, AL, United States)
Landrum, B.
(Alabama Univ. Huntsville, AL, United States)
Date Acquired
September 7, 2013
Publication Date
June 14, 2005
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2005-4283
Report Number: AIAA Paper 2005-4283
Meeting Information
Meeting: AIAA 41st Joint Propulsion Conference and Exhibit
Location: Tucson, AZ
Country: United States
Start Date: July 10, 2005
End Date: July 14, 2005
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NCC8-200
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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