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THRSTER: A THRee-STream Ejector Ramjet Analysis and Design ToolAn engineering tool for analyzing ejectors in rocket based combined cycle (RBCC) engines has been developed. A key technology for multi-cycle RBCC propulsion systems is the ejector which functions as the compression stage of the ejector ramjet cycle. The THRee STream Ejector Ramjet analysis tool was developed to analyze the complex aerothermodynamic and combustion processes that occur in this device. The formulated model consists of three quasi-one-dimensional streams, one each for the ejector primary flow, the secondary flow, and the mixed region. The model space marches through the mixer, combustor, and nozzle to evaluate the solution along the engine. In its present form, the model is intended for an analysis mode in which the diffusion rates of the primary and secondary into the mixed stream are stipulated. The model offers the ability to analyze the highly two-dimensional ejector flowfield while still benefits from the simplicity and speed of an engineering tool. To validate the developed code, wall static pressure measurements from the Penn-State and NASA-ART RBCC experiments were used to compare with the results generated by the code. The calculated solutions were generally found to have satisfactory agreement with the pressure measurements along the engines, although further modeling effort may be required when a strong shock train is formed at the rocket exhaust. The range of parameters in which the code would generate valid results are presented and discussed.
Document ID
20010036882
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Chue, R. S.
(General Applied Science Labs., Inc. Ronkonkoma, NY United States)
Sabean, J.
(General Applied Science Labs., Inc. Ronkonkoma, NY United States)
Tyll, J.
(General Applied Science Labs., Inc. Ronkonkoma, NY United States)
Bakos, R. J.
(General Applied Science Labs., Inc. Ronkonkoma, NY United States)
Date Acquired
August 20, 2013
Publication Date
November 1, 2000
Publication Information
Publication: JANNAF 25th Airbreathing Propulsion Subcommittee, 37th Combustion Subcommittee and 1st Modeling and Simultation Subcommittee Joint Meeting
Volume: 1
Subject Category
Spacecraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NASA Order H-29709-D
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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