Laser ignition of a multi-injector LOX/methane combustor

Börner, Michael; Manfletti, Chiara; Hardi, Justin; Suslov, Dmitry; Kroupa, Gerhard; Oschwald, Michael

doi:10.1007/s12567-018-0196-6

Cited by 19 publications

(8 citation statements)

References 22 publications

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“…Major drawback is a reduction of the specific impuls. Nevertheless multiple LOX/CH 4 or LOX/LNG engines are currently under development. 2,4,8) One of the major concerns regarding methane as a fuel are the cooling capabilities in regenerative cooling channels.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigation of Heat Transfer Processes in Rocket Engine Cooling Channels Operated with Cryogenic Hydrogen and Methane at Supercritical Conditions

Haemisch

Suslov

Oschwald

2021

AEROSPACE TECHNOLOGY JAPAN

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Hydrogen and Methane are two fluids that are either used or in discussion as propellants for upper and lower stage rocket engines. The conception of a regenerative cooling system is a crucial part in the design of a rocket engine and so is the detailed knowledge of the coolants behavior and the heat transfer capabilities. Hydrogen is a very efficient and well known cooling fluid whereas the properties of methane as a cooling fluid are intensively investigated nowadays. Experiments were performed with a subscale combustion chamber that is divided into four sectors around the circumference each containing rectangular cooling channels with different aspect ratios. Cryogenic hydrogen and liquid methane were used as cooling fluids. These experiments provide a broad data basis that is used for the validation of CFD simulations. The simulations are capable of predicting wall temperatures for high pressure conditions. Thermal stratification effects that are known to limit cooling properties in high aspect ratio cooling channels arise for both fluids, but the effects are much stronger for hydrogen compared to methane. However in the vicinity to the critical point, when it comes to heat transfer deterioration, the simulations show large deviations to the experimental values.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigation of Heat Transfer Processes in Rocket Engine Cooling Channels Operated with Cryogenic Hydrogen and Methane at Supercritical Conditions

Haemisch

Suslov

Oschwald

2021

AEROSPACE TECHNOLOGY JAPAN

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“…Развитие работ по исследованию возможности применения лазерного зажигания для двигателей различного назначения активно ведется во всем мире [1][2][3][4][5]. Применительно к камерам сгорания ракетных двигателей это обусловлено в первую очередь возможностью многократных включений при массогабаритных характеристиках системы зажигания не превышающих параметры электроискровых и электроплазменных систем.…”

Section: Introductionunclassified

Laser Ignition of Oxygen-Hydrocarbon Fuels in Rocket Engines

Rebrov¹,

Голубев²,

Golikov³

2018

PoHEI.MB

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АннотацияРассмотрены этапы разработки лазерного зажигания топлива кислород-керосин применительно к ракетной технике. Приведены варианты конструкций и параметры систем лазерного зажигания для запальных устройств (ЗУ), ракетных двигателей малой тяги (РДМТ), модельных установок и камер сгорания (КС) ракетных двигателей (РД), а также особенности их использования, включая характеристики лазеров и параметры топливных смесей, обеспечивающие надежное зажигание топлива различного состава. Целью проведенных работ была разработка единых рекомендаций по внедрению лазерного зажигания на крупноразмерные камеры сгорания многокамерных двигательных установок и отработка данных рекомендаций в ходе проведения испытаний системы зажигания штатных КС ракетных двигателей РД107/РД108 первой и второй ступеней ракеты-носителя «Союз».

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“…Sub-scale research combustor model 'A' ("BKA") during operation at the European Research and Technology Test Bench P8 at the DLR Institute of Space Propulsion to guarantee ignition during the transient injection phase. Further details on the combustor and the laser ignition system can be found in Ref [15]…”

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confidence: 99%

Injector-coupled thermoacoustic instabilities in an experimental LOX-methane rocket combustor during start-up

et al. 2020

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This paper reports the investigation of acoustic combustion instability experienced during repetitive ignition testing of a sub-scale LOX-methane rocket thrust chamber. The occurrence of resonant coupling between the LOX injectors and the combustion chamber acoustic modes was assessed from the experimental data recorded during the highly transient phase of operation from ignition up to around 2 s. A method was developed to model the evolution of acoustic properties in both the combustion chamber and the injectors during the transient period. For the LOX injectors, the Woods equation was used to estimate the speed of sound in the two-phase flow. The models were used to identify the corresponding mode frequencies in the unsteady pressure measurements, and show that the high-amplitude instability occurred when they intersected. Very close coupling of less than 3% frequency difference is required for high amplitudes to be observed. However, the condition was necessary but not sufficient for high amplitudes to be reached. Keywords High-frequency instability • Combustion stability • LOX/CH 4 • Methane List of symbols X Void fraction density A Cross-section area c Speed of sound f Frequency P Static pressure p ′ Dynamic pressure T Temperature t b Begin of phase transition t e End of phase transition ⋅ F Fuel ⋅ g Gaseous phase ⋅ l Liquid phase ⋅ O Oxygen ⋅ CC Combustion chamber ⋅ FM Flow meter ⋅ mlf Two phase ⋅ t Throttle

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Laser ignition of a multi-injector LOX/methane combustor

Cited by 19 publications

References 22 publications

Experimental and Numerical Investigation of Heat Transfer Processes in Rocket Engine Cooling Channels Operated with Cryogenic Hydrogen and Methane at Supercritical Conditions

Experimental and Numerical Investigation of Heat Transfer Processes in Rocket Engine Cooling Channels Operated with Cryogenic Hydrogen and Methane at Supercritical Conditions

Laser Ignition of Oxygen-Hydrocarbon Fuels in Rocket Engines

Injector-coupled thermoacoustic instabilities in an experimental LOX-methane rocket combustor during start-up

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