Investigation of Two Dimensional Thermal Loads in the Region Near the Injector Head of a High Pressure Subscale Combustion Chamber

Suslov, Dmitry; Arnold, Richard T.; Haidn, Oskar

doi:10.2514/6.2009-450

Cited by 24 publications

(13 citation statements)

References 4 publications

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“…Similar results have been found in previous studies using H 2 /LOx propellant combination [16]. The drop in wall pressure at the face plate (x = 0) is linked to the presence of a recirculation zone triggered by the heat release and connected expansion directly after the injection point.…”

Section: Pressure Distribution and Discharge Coe©cient Of The Injectosupporting

confidence: 89%

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Celano

Silvestri

Schlieben

et al. 2016

Progress in Propulsion Physics

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The results from an experimental investigation on an oxygenmethane single-injector combustion chamber are presented. They provide detailed information about the thermal loads at the hot inner walls of the combustion chamber at representative rocket engine conditions and pressures up to 20 bar. The present study aims to contribute to the understanding of the thermal transfer processes and to validate the in-house design tool Thermtest and a base for an attempt to simulate the §ame behavior with large-eddy simulation (LES). Due to the complex §ow phenomena linked to the use of cryogenic propellants, like extreme variation of §ow properties and steep temperature gradients, in combination with intensive chemical reactions, the problem has been partially simpli¦ed by injecting gaseous oxygen (GOx) and gaseous methane (GCH 4 ). external combustion chamber width, m c speci¦c heat capacity, J/(kg·K)' E in total energy entering the control volume, W ' E out total energy leaving the control volume, W

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Section: Pressure Distribution and Discharge Coe©cient Of The Injectosupporting

confidence: 89%

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Celano

Silvestri

Schlieben

et al. 2016

Progress in Propulsion Physics

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“…A well documented experimental test case 12,16,27 is reproduced to investigate wall heat flux in high pressure film cooled thrust chambers. This test case consists in a film cooled high pressure subscale combustion chamber operated with liquid oxygen and gaseous hydrogen.…”

Section: A Experimental Test Casementioning

confidence: 99%

Numerical Study of Heat Transfer in Film Cooled Thrust Chambers

Betti¹,

Martelli²,

Nasuti³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Film cooling as a thermal protection for the walls of liquid rocket engines is studied numerically for hydrogen and methane thrust chamber tests. The aim is to verify the capability of the Reynolds Average Navier-Stokes model to capture the basic characteristics of film-cooled thrust chambers, considering a simplified approach, named pseudo-injector approach, which does not model propellant injection and combustion. This assumption allows a great saving in computational time, in particular when considering 3D simulations. The present study takes its origin from the European Community In-Space Propulsion 1 (ISP-1) program where, among various projects, an experimental campaign has been designed to study the film cooling technique in an oxygen/methane thrust chamber and to provide a database for computational fluid dynamics validation. The results show that the present approach gives good results in terms of heat flux characterization, in particular when dealing with test cases of high chamber pressure.

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“…However, injector vicinity caused chamber wall temperature variations in circumferential direction of the chamber wall such as e.g. described in [1] may cause localization effects of the deformation of the inner liner of chamber wall structures. Exemplary, an injector vicinity caused 20 K wall temperature variation is taken into account by a three-channel model.…”

Section: Introductionmentioning

confidence: 98%

Inner liner temperature variation caused deformation localisation effects in a multichannel model of a generic LRE wall structure

Riccius¹,

Zametaev²,

Bouajila³

et al. 2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The inner liner of a regeneratively cooled wall of a main stage rocket combustion chamber is extremely loaded by the high temperature of the hot gas and the pressure difference between the coolant and the hot gas. A cyclic operation of such a chamber usually causes a LFC failure of the wall structure after a very low number of cycles. The development and flight qualification of such components includes on top of many other actions thermal, structural and fatigue life analyses of chamber wall structures. Often, these analyses are based on half cooling channel + half fin Finite Element models of a tiny chamber wall section with symmetry conditions at the centerline of the cooling channel and the centerline of the fin. However, injector vicinity caused chamber wall temperature variations in circumferential direction of the chamber wall may cause localization effects of the deformation of the inner liner of chamber wall structures. Exemplary, an injector vicinity caused 20 K wall temperature variation is taken into account by a three-channel model. The influence of this variation to the distribution of the circumferential strain distribution as well as to the post processing determined fatigue life is shown.

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Investigation of Two Dimensional Thermal Loads in the Region Near the Injector Head of a High Pressure Subscale Combustion Chamber

Cited by 24 publications

References 4 publications

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Numerical Study of Heat Transfer in Film Cooled Thrust Chambers

Inner liner temperature variation caused deformation localisation effects in a multichannel model of a generic LRE wall structure

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