Design and Analysis of Gas Ejector in High Altitude Test Facility

Document Type : Research Article

Authors

1 Aerospace Engineering/ Amirkabir University of Technology

2 Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran

Abstract

Usually, ground testing of space engines is performed in a high altitude test facility. The facility is equipped with a supersonic diffuser that expels automatically engine gases to the atmospheric environment and maintains a vacuum pressure around its nozzle and motor. Normally; in the case of lower motor pressure, the supersonic flow in the diffuser could not be established. In this situation, an auxiliary ejector is employed frequently at the end section of the diffuser. In the present study, a new algorithm for designing the supersonic ejector has been proposed. Unlike conventional methods, this algorithm can be used with different primary and secondary fluids. The main design parameters are determined by the algorithm, while the secondary parameters are selected from the experimental test results of the existing references. A safe margin is considered for the safe operation of the ejector, which is predicted through the numerical simulations. Also, numerical simulation is used to verify the present design algorithm. Finally, using the proposed algorithm, an ejector is designed to reduce the minimum starting pressure of a second throat exhaust diffuser. An integrated simulation of the diffuser-ejector is performed and the appropriateness of the designed ejector is confirmed.

Keywords

Main Subjects

References

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Amirkabir Journal of Mechanical Engineering
Volume 52, Issue 11
February 2021
Pages 3015-3032

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