Preliminary Design Analysis of Regenerative Cooling for N2O/Alcohol Small Scale Liquid Rocket Engine

Author:

Palej Patryk1,Palacz Tomasz1

Affiliation:

1. AGH Space Systems , AGH University of Science and Technology , ul. Mickiewicza 30, 30-059 Kraków , Poland

Abstract

Abstract This paper presents a concept of a small scale liquid-propellant rocket engine designed in AGH Space Systems for sounding rocket. During preliminary design of thermal aspects various ways of cooling were evaluated and described. Possible issues and design approaches for ablative, radiation and regenerative cooling are raised. The authors describe available solutions. Regenerative cooling is especially concerned as it is most popular solution in bi-liquid engines, in which alcohol fuel acts as coolant and is preheated before it reaches combustion chamber. To estimate a possible temperature distribution - and thus an applicability of such a system in the engine - a mathematical model of heat transfer was developed. Unique element of said engine is its oxidizer - nitrous oxide, which have been rarely used to date. Comparison between typical LOX bi-liquids is given and major differences that affect cooling arrangement are discussed. The authors compared different combinations of coolants, fuel/oxidizer ratios etc. to optimize the temperature distribution which is a key factor for the engine performance.

Publisher

Walter de Gruyter GmbH

Reference13 articles.

1. [1] Tokudome S., Yagishita T., Habu H., Shimada T., Daimou Y., 2007, „Experimental Study of an N2O/Ethanol Propulsion System,” 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 8 - 11 July 2007, Cincinnati, OH, Paper No. 546410.2514/6.2007-5464

2. [2] Youngblood, S. H., 2015, “Design and Testing of a Liquid Nitrous Oxide and Ethanol Fueled Rocket Engine,” MSc thesis, https://infohost.nmt.edu/~mjh/Pubs/Youngblood2015.pdf

3. [3] Palacz, T., 2017, “Nitrous Oxide Application for Low-Cost, Low-Thrust Liquid Rocket Engines”, 7th European Conference for Aeronautics and Space Sciences (EUCASS), 3 – 7 July, Milan, Paper No. 474

4. [4] Sutton, G. P., Biblarz, O., 2001. “Rocket Propulsion Elements.” John Wiley & Sons, New York

5. [5] Bartz, D. R., 1957. “A Simple Equation for Rapid Estimation of Rocket Nozzle Convective Heat Transfer Coefficients” Jet Propulsion

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