Study on the Design Criteria of the Coaxial Injector for a LOX/Hydrogen Rocket Engine —Evaluation of Design for Injectors of the LE-5 Engine and Its Derivatives

Study on the Design Criteria of the Coaxial Injector for a LOX/Hydrogen Rocket Engine —Evaluation of Design for Injectors of the LE-5 Engine and Its Derivatives—

Published:2007 Issue:169 Volume:50 Page:201-208
ISSN:0549-3811
Container-title:TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
language:en
Short-container-title:Trans. Japan Soc. Aero. S Sci.

Author:

YATSUYANAGI Nobuyuki

Publisher

Japan Society for Aeronautical and Space Sciences

Subject

Space and Planetary Science,Aerospace Engineering

Link

https://www.jstage.jst.go.jp/article/tjsass/50/169/50_169_201/_pdf

Reference9 articles.

1. 1) Yatsuyanagi, N.: An Empirical and Analytical Study of Spray Flow Fields Formed by Liquid-Gas Coaxial Injector Element. Part 3, Application for the Combustion Performance Prediction Model of LOX/Hydrogen Rocket Combustor, Technical Report of the National Aerospace Laboratory, NAL TR-769, 1983 (in Japanese).

2. 2) Priem, R.J. and Heidmann, M.F.: Propellant Vaporization as a Design Criterion for Rocket Engine Combustion Chambers, NASA TR-67, 1960.

3. 3) Combs, L.P. and Schuman, M.D.: Steady State Rocket Combustion of Gaseous Hydrogen and Liquid Oxygen, Research Report RR64-29, Rocket-dyne, 1965.

4. Study on Breakup Length of Liquid Jet by Liquid-Gas Coaxial Injector —Evaluation of Atomization Characteristics of Rocket Engine Injectors—

5. 5) Yatsuyanagi, N., Sakamoto, H. and Sato, K.: Experimental Study on Vaporization Rate of LOX-Spray with Methane and Hydrogen in Rocket Combustor, Proceedings of the 19th International Symposium on Space and Science, ISTS 94-a-21, 1994.

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3. Establishment of Design Method for Liquid Hydrogen Regenerative Cooling Combustor of LOX/Hydrogen Rocket Engine;TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2009

4. Comprehensive Design Method for LOX/Liquid-Methane Regenerative Cooling Combustor with Coaxial Injector;TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES;2009