Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor

Thermal engines based on pressure gain combustion offer new opportunities to generate thrust with enhanced efficiency and relatively simple machinery. The sudden expansion of detonation products from a single-opening tube yields thrust, although this is suboptimal. In this article, we present the co...

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Main Authors: Francesco Ornano, James Braun, Bayindir Huseyin Saracoglu, Guillermo Paniagua
Format: Article
Language:English
Published: SAGE Publishing 2017-02-01
Series:Advances in Mechanical Engineering
Online Access:https://doi.org/10.1177/1687814017690955
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spelling doaj-99fbbcabf1574312865f5f85f213086d2020-11-25T01:27:33ZengSAGE PublishingAdvances in Mechanical Engineering1687-81402017-02-01910.1177/1687814017690955Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustorFrancesco Ornano0James Braun1Bayindir Huseyin Saracoglu2Guillermo Paniagua3Osney Thermo-Fluids Laboratory, Department of Engineering Science, University of Oxford, Oxford, UKZucrow Laboratories, School of Mechanical Engineering, Purdue University, West Lafayette, IN, USAAeronautics and Aerospace Department, The von Karman Institute for Fluids Dynamics, Sint-Genesius-Rode, BelgiumZucrow Laboratories, School of Mechanical Engineering, Purdue University, West Lafayette, IN, USAThermal engines based on pressure gain combustion offer new opportunities to generate thrust with enhanced efficiency and relatively simple machinery. The sudden expansion of detonation products from a single-opening tube yields thrust, although this is suboptimal. In this article, we present the complete design optimization strategy for nozzles exposed to detonation pulses, combining unsteady Reynolds-averaged Navier–Stokes solvers with the accurate modeling of the combustion process. The parameterized shape of the nozzle is optimized using a differential evolution algorithm to maximize the force at the nozzle exhaust. The design of experiments begins with a first optimization considering steady-flow conditions, subsequently followed by a refined optimization for transient supersonic flow pulse. Finally, the optimized nozzle performance is assessed in three dimensions with unsteady Reynolds-averaged Navier–Stokes capturing the deflagration-to-detonation transition of a stoichiometric, premixed hydrogen–air mixture. The optimized nozzle can deliver 80% more thrust than a standard detonation tube and about 2% more than the optimized results assuming steady-flow operation. This study proposes a new multi-fidelity approach to optimize the design of nozzles exposed to transient operation, instead of the traditional methods proposed for steady-flow operation.https://doi.org/10.1177/1687814017690955
collection DOAJ
language English
format Article
sources DOAJ
author Francesco Ornano
James Braun
Bayindir Huseyin Saracoglu
Guillermo Paniagua
spellingShingle Francesco Ornano
James Braun
Bayindir Huseyin Saracoglu
Guillermo Paniagua
Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor
Advances in Mechanical Engineering
author_facet Francesco Ornano
James Braun
Bayindir Huseyin Saracoglu
Guillermo Paniagua
author_sort Francesco Ornano
title Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor
title_short Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor
title_full Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor
title_fullStr Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor
title_full_unstemmed Multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor
title_sort multi-stage nozzle-shape optimization for pulsed hydrogen–air detonation combustor
publisher SAGE Publishing
series Advances in Mechanical Engineering
issn 1687-8140
publishDate 2017-02-01
description Thermal engines based on pressure gain combustion offer new opportunities to generate thrust with enhanced efficiency and relatively simple machinery. The sudden expansion of detonation products from a single-opening tube yields thrust, although this is suboptimal. In this article, we present the complete design optimization strategy for nozzles exposed to detonation pulses, combining unsteady Reynolds-averaged Navier–Stokes solvers with the accurate modeling of the combustion process. The parameterized shape of the nozzle is optimized using a differential evolution algorithm to maximize the force at the nozzle exhaust. The design of experiments begins with a first optimization considering steady-flow conditions, subsequently followed by a refined optimization for transient supersonic flow pulse. Finally, the optimized nozzle performance is assessed in three dimensions with unsteady Reynolds-averaged Navier–Stokes capturing the deflagration-to-detonation transition of a stoichiometric, premixed hydrogen–air mixture. The optimized nozzle can deliver 80% more thrust than a standard detonation tube and about 2% more than the optimized results assuming steady-flow operation. This study proposes a new multi-fidelity approach to optimize the design of nozzles exposed to transient operation, instead of the traditional methods proposed for steady-flow operation.
url https://doi.org/10.1177/1687814017690955
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