LOX-Kerosene Oxidizer-Rich Gas-Generator and Main Combustion Chamber Subscale Testing

Haeseler, D.; Mäding, Chris; Preclik, D.; Rubinskiy, Vitaly; Kosmacheva, V.P.; Federation, Russian

doi:10.2514/6.2006-5197

Cited by 7 publications

(5 citation statements)

References 3 publications

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“…The reduction of injector element numbers results in more simplicity, lower cost or even higher reliability for the engine design. Thus, reducing the number of elements in future high-performance engines has become a goal of injector researcher [9][10][11][12][13]. Tamura introduced the swirl coaxial injector in the H 2 /O 2 engine main chamber to enhance the mixing and increase the flowrate per injector element.…”

Section: Introductionmentioning

confidence: 99%

“…However, this type of injector results in high local heat fluxes on the injector faceplate and the chamber wall near the faceplate [10]. To obtain a high-flowrate injector element, Immich and Haeseler used different numbers of shear coaxial elements in a chamber under the same conditions [11,12]. To reduce the costs of the gas-generator, tri-coaxial elements were applied in gas-generators [13] to decrease the number of injector elements, but this type of element has a complicated configuration and may add additional complexity in the form of an of extra oxidizer dome or in the design and manufacturing difficulty of the element itself, so its application in main combustion chambers is very limited.…”

Section: Introductionmentioning

confidence: 99%

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High flowrate injector with gaseous hydrogen and gaseous oxygen

Wang

Cai

Gao

et al. 2011

Sci. China Technol. Sci.

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In order to get a high flowrate gas-gas injector and its design methodology, the combustion flow field of a typical shear-coaxial injector was analyzed firstly. The dimensional analysis was applied in the phenomenon of gas-gas combustion, and design parameter optimization and a structure improvement were also carried out. A high flowrate single-element injector with high H 2 /O 2 momentum ratio and tapered O 2 post tip was obtained and validated by both numerical and experimental studies. This high flowrate injector has simple construction and it can effectively enhance the mixing, decrease the combustion completion length and also has a benign heat environment. Furthermore, based on the study of the single-element injector, numerical optimization and validation experiments were conducted successively on a multi-element injector equipped with high flowrate injection elements. The multi-element injector with the high flowrate elements started up and shut down smoothly, and operated steadily without any stability aids. In the combustor designed with nominal parameters, this injection element can obtain high combustion efficiency with a flowrate of 3.7 times that of SSME main injector element and shows a benign chamber wall heat compatibility. This injector design and the design methodology can become a reference for the design of other types of injectors for liquid rocket engines. liquid rocket engine, gas-gas injector, shear-coaxial injector,, Large Eddy Simulation, subscale combustor, experiment Citation: Wang X W, Cai G B, Gao Y S, et al. High flowrate injector with gaseous hydrogen and gaseous oxygen.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

High flowrate injector with gaseous hydrogen and gaseous oxygen

Wang

Cai

Gao

et al. 2011

Sci. China Technol. Sci.

View full text Add to dashboard Cite

show abstract

“…9 Frequently, the injectors are placed in sub-scale experiments to verify the desired performance before implementing into full-scale engines. 10–19 These experiments can also provide test data to validate CFD tools for use in the design process.…”

Section: Introductionmentioning

confidence: 99%

Flame dynamics of an injection element operated with LOX/H₂, LOX/CNG and LOX/LNG in a sub- and supercritical rocket combustor with large optical access

Martin

Armbruster

Stützer

et al. 2023

International Journal of Spray and Combustion Dynamics

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Hot fire tests were performed using a single-injector research combustor featuring a large optical access window ([Formula: see text] mm) for flame visualisation. Three test campaigns were conducted with the propellant combination of liquid oxygen and hydrogen, liquid oxygen and compressed-natural-gas, as well as liquid oxygen and liquefied-natural-gas at conditions relevant for main- and upper-stage rocket engines. The large optical access enabled synchronised flame imaging using ultraviolet and blue radiation wavelengths covering a large portion of the combustion chamber for various sets of sub- and supercritical operating conditions. Combined with temperature, pressure and unsteady pressure measurements, this data provides a high-quality basis for the validation of numerical modelling. Flame width, length and opening angle as features describing the flame topology were extracted from the imaging. The suitability of flame imaging using ultraviolet and blue radiation wavelengths as qualitative markers of heat release was evaluated. Two-dimensional distributions of the Rayleigh Index were calculated for intervals with and without high-amplitude, self-excited oscillations of the longitudinal acoustic resonance modes. The calculated Rayleigh Index values properly reflect the thermoacoustic state of the chamber, indicating that both types of imaging may be used for qualitative study of thermoacoustic coupling of high-pressure cryogenic flames.

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“…al. 3 studied on a characteristic of injectors used for preburners by numerical method. Haeseler et.…”

Section: Introductionmentioning

confidence: 99%

Development of Ultra Lean Burn Preburners for Small Liquid Rockets

Moon

Lee

Moon

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Korea Aerospace Research Institute (KARI) is developing gas generator cycle kerosene engines and also researching technologies of staged combustion cycle LREs for the next generation engine development. As a first step to study the staged combustion cycle, an oxygen rich combustion preburner was developed. The preburner is characterized with ultra-lean burn and high combustion pressure of O/F 60 and 200 bar, respectively. The exhaust gas of the preburner is so similar to high temperature pure oxygen gas that it may burn any metal contacted if the temperature is not strictly controlled. Hot fire tests showed that the combustion pressure was stable and the exhaust temperature satisfied the requirements of the average value and the spatial dispersion. This article will introduce the preburner and show the results of the hot fire tests Nomenclature O/F = oxygen to fuel mass flow rate LOx = liquid oxygen TEAL = triethylaluminum TEAB = triethylaluminum/boron

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LOX-Kerosene Oxidizer-Rich Gas-Generator and Main Combustion Chamber Subscale Testing

Cited by 7 publications

References 3 publications

High flowrate injector with gaseous hydrogen and gaseous oxygen

High flowrate injector with gaseous hydrogen and gaseous oxygen

Flame dynamics of an injection element operated with LOX/H₂, LOX/CNG and LOX/LNG in a sub- and supercritical rocket combustor with large optical access

Development of Ultra Lean Burn Preburners for Small Liquid Rockets

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LOX-Kerosene Oxidizer-Rich Gas-Generator and Main Combustion Chamber Subscale Testing

Cited by 7 publications

References 3 publications

High flowrate injector with gaseous hydrogen and gaseous oxygen

High flowrate injector with gaseous hydrogen and gaseous oxygen

Flame dynamics of an injection element operated with LOX/H2, LOX/CNG and LOX/LNG in a sub- and supercritical rocket combustor with large optical access

Development of Ultra Lean Burn Preburners for Small Liquid Rockets

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Product

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Flame dynamics of an injection element operated with LOX/H₂, LOX/CNG and LOX/LNG in a sub- and supercritical rocket combustor with large optical access