Computational investigation of cooling effectiveness for film cooled dual-bell exhaust nozzle for LO2/LH2 liquid rocket engines-Reference-Cited by-同舟云学术

Computational investigation of cooling effectiveness for film cooled dual-bell exhaust nozzle for LO2/LH2 liquid rocket engines

Published:2021-09-04 Issue: Volume: Page:1-17
ISSN:1556-7036
Container-title:Energy Sources, Part A: Recovery, Utilization, and Environmental Effects
language:en
Short-container-title:Energy Sources, Part A: Recovery, Utilization, and Environmental Effects

Author:

Raju Martin¹,Suryan Abhilash¹,Šimurda David²

Affiliation:

1. Department of Mechanical Engineering, College of Engineering Trivandrum, Trivandrum, Kerala, India

2. Institute of Thermomechanics, Czech Academy of Sciences, Prague, Czech Republic

Publisher

Informa UK Limited

Subject

Energy Engineering and Power Technology,Fuel Technology,Nuclear Energy and Engineering,Renewable Energy, Sustainability and the Environment

Link

https://www.tandfonline.com/doi/pdf/10.1080/15567036.2021.1963885

Reference62 articles.

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2. Film Cooling of Accelerated Flow in a Subscale Combustion Chamber

3. Experimental and Numerical Study of Supersonic Film Cooling

4. Batha, D. R., J. G. Campbell, M. D. Carey, and C. D. Coulbert (1963). Thrust chamber cooling techniques for spacecraft engines. Volume I-evaluation procedure and analyses. NASA Technical Reports: NASA-CR-50958

5. Campbell, J. G., D. R. Batha, M. D. Carey, A. R. Nagy, and R. C. Stechman (1963). Thrust chamber cooling techniques for spacecraft engines. Volume II – Final report. NASA Technical Reports: NASA-CR-50959.

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