A trade-off analysis is performed on a test case representative of the cooling system of 1 MN thrust class oxygen/hydrogen liquid rocket engine. The aim of the analysis is to find the channel aspect ratio that maximizes the heat extracted from the hot-gas, for a given coolant pressure drop and hot-gas side wall temperature. The analysis requires many cooling channel flow calculations which are performed by means of a simplified model, referred to as quasi-2D, and an accurate conjugate heat transfer model based on numerical integration of the Navier-Stokes and Fourier's Equations. Both models are able to describe the whole cooling device composed by the coolant and the solid domain, which is exposed the hot-gas, with different computational time and level of details. The fast quasi-2D approach is used to select channel geometries showing the same pressure loss. Discussion is made on results obtained with the more accurate CHT model. Results identify, for the selected test case, an ideal aspect ratio which optimizes cooling performance at large values of channel aspect ratio © 2012 by M. Pizzarelli, F. Nasuti, M. Onofri.

Analysis on the effect of channel aspect ratio on rocket thermal behavior / Pizzarelli, Marco; Nasuti, Francesco; Onofri, Marcello. - STAMPA. - 4:(2012), pp. 2885-2896. ((Intervento presentato al convegno 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 tenutosi a Atlanta, GA nel 30 July 2012 through 1 August 2012 [10.2514/6.2012-3991].

Analysis on the effect of channel aspect ratio on rocket thermal behavior

PIZZARELLI, MARCO;NASUTI, Francesco;ONOFRI, Marcello
2012

Abstract

A trade-off analysis is performed on a test case representative of the cooling system of 1 MN thrust class oxygen/hydrogen liquid rocket engine. The aim of the analysis is to find the channel aspect ratio that maximizes the heat extracted from the hot-gas, for a given coolant pressure drop and hot-gas side wall temperature. The analysis requires many cooling channel flow calculations which are performed by means of a simplified model, referred to as quasi-2D, and an accurate conjugate heat transfer model based on numerical integration of the Navier-Stokes and Fourier's Equations. Both models are able to describe the whole cooling device composed by the coolant and the solid domain, which is exposed the hot-gas, with different computational time and level of details. The fast quasi-2D approach is used to select channel geometries showing the same pressure loss. Discussion is made on results obtained with the more accurate CHT model. Results identify, for the selected test case, an ideal aspect ratio which optimizes cooling performance at large values of channel aspect ratio © 2012 by M. Pizzarelli, F. Nasuti, M. Onofri.
48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Analysis on the effect of channel aspect ratio on rocket thermal behavior / Pizzarelli, Marco; Nasuti, Francesco; Onofri, Marcello. - STAMPA. - 4:(2012), pp. 2885-2896. ((Intervento presentato al convegno 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 tenutosi a Atlanta, GA nel 30 July 2012 through 1 August 2012 [10.2514/6.2012-3991].
File allegati a questo prodotto
Non ci sono file associati a questo prodotto.

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/507317
 Attenzione

Attenzione! I dati visualizzati non sono stati sottoposti a validazione da parte dell'ateneo

Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 6
  • ???jsp.display-item.citation.isi??? ND
social impact