Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines
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ORIGINAL ARTICLE
Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines P. Concio1 · M. T. Migliorino1 · F. Nasuti1 Received: 1 June 2020 / Revised: 27 August 2020 / Accepted: 19 September 2020 © The Author(s) 2020
Abstract The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challenge, because of the little experimental information. Such a problem is of obvious importance in general, and becomes even more important when considering reusable engines. Unfortunately, only few indirect experimental data are available for the validation of throat heat flux prediction. On the numerical side, a detailed solution would require a huge resolution and codes able to solve at the same time combustion, boundary layer with possible finite-rate reactions, expansion up to at least sonic speed, and in some cases radiative heat flux. Therefore, it is important to validate, with the few experimental data available in the literature, simplified CFD approaches whose aim is to predict heat flux in the nozzle in affordable times. Results obtained by different numerical models based on a RANS approach show the correctness and quality of the approximations made, indicating the main phenomena to be included in modeling for the correct prediction of throat heat flux. Keywords Liquid rocket engines · Heat transfer · CFD
1 Introduction Heat flux prediction at throat of liquid rocket engines still constitutes a challenge, also because of the limited experimental information. On the other hand, being capable of predicting numerically the heat flux at the throat of a rocket thrust chamber is of paramount importance. In fact, throat region is the most critical one in terms of heat loading and requires a suitable cooling system design, which is a tradeoff between overall engine efficiency and safe structural life. This is even more important if one considers reusable engines. Many experimental studies have been focused on the measure of wall temperature and heat flux in the combustion region, that is the thrust chamber part from the injector faceplate up to the beginning of the converging section. Less experimental data are available concerning throat heat flux. Based on paper presented at the XXV Congresso Nazionale AIDAA, Settembre 2019, Roma, Italia. © AIDAA, Associazione Italiana di Aeronautica e Astronautica. * P. Concio [email protected] 1
Dipartimento di Ingegneria Meccanica ed Aerospaziale, “La Sapienza”-Università di Roma, Rome, Italy
In fact, it can be easily imagined that inserting thermocouples in an experimental apparatus in the vicinity of the converging-diverging nozzle throat is much more challenging. The numerical estimation of heat load in both combustion chamber and nozzle presents its uncertainties. Since the boundary-layer based empirical relations, as the famous Bartz equation [1], significant progresses have been made thanks to CFD developments. However, a detailed solution requires a huge resolution and codes able to solve at the same
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