History of Liquid-Propellant Rocket Engines in Russia, Formerly the Soviet Union

Sutton, George P.

doi:10.2514/2.6943

Cited by 74 publications

(19 citation statements)

References 1 publication

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“…1. As shown in the figure, gaseous oxygen (GO 2 ) flows through the inner passage of the injector and then, it is mixed with liquid hydrocarbon fuel injected through several peripheral holes and finally, both GO 2 and liquid fuel are injected into the chamber [5].…”

Section: Introductionmentioning

confidence: 99%

A Numerical Study on Combustion Characteristics of Coaxial-Jet Injectors Using Scaling Techniques in a Subscale Chamber

Kim

Sohn

Lee

2013

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

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Numerical analyses are conducted with scaling techniques to predict combustion instability in actual fullscale combustion chamber of rocket engines. From the simulation with a subscale chamber, flame patterns are investigated as a function of the recess length and spreading angle of fuel jet is focused on. For stability rating, damping factors have been obtained as a function of hydraulic parameter and the data give us information on relatively stable and unstable zones. From the numerical results, the stable zone can be identified in a quantitative manner.

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Section: Introductionmentioning

confidence: 99%

A Numerical Study on Combustion Characteristics of Coaxial-Jet Injectors Using Scaling Techniques in a Subscale Chamber

Kim

Sohn

Lee

2013

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

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“…1. As shown in this figure, gaseous oxidizer (GO 2 ) flows through the inner passage of the injector and then is mixed with liquid hydrocarbon fuel injected through several peripheral holes and, finally, both GO 2 and liquid fuel are injected into the chamber [9]. At this point, with the inside volume of the injector occupied by gas, it is noteworthy that the gas-liquid scheme injector can play a significant role in acoustic damping like acoustic resonators or damper in addition to its original function of propellant injection.…”

Section: Introductionmentioning

confidence: 99%

Effects of inlet blockage of gas-liquid scheme injector on acoustic tuning for acoustic damping in a combustion chamber

Sohn

Park

2008

J Mech Sci Technol

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In a rocket combustor, purely acoustic tuning of gas-liquid scheme injector is studied numerically for acoustic absorption by adopting linear acoustic analysis. Acoustic behavior in the combustor with a single injector is investigated to assure the optimum injector length. Acoustic-absorption effect of the injector is evaluated for cold condition by the quantitative parameter of damping factor as a function of injector length in the chamber for several boundary absorption coefficients. Irrespective of boundary absorption at the chamber wall, it is assured that the optimum tuning-length of the injector corresponds to half of a full wavelength of the first longitudinal overtone mode traveling in the injector with the acoustic frequency intended for damping in the chamber. Although boundary absorption affects little the tuning length of the injector, it appreciably affects damping capacity. Acoustic absorption at the wall increases with boundary absorption coefficient, but purely acoustic-damping effect induced by the tuned injector decreases with the coefficient. As another design parameter, effects of blockage at the injector inlet on acoustic tuning are investigated. It is found that the optimum injector length is shifted depending on the blockage ratio. Suitable combination of injector length and blockage should be made for maximum damping.

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“…When the injector is scaled up to reduce the number of injector elements, the mixing performance of the shear coaxial injector degrades, and the propulsion system needs a more powerful mixing device. Most Russian oxidizer-rich staged combustion engines, which use storable hydrocarbon fuel, are equipped with a gas-centered swirl coaxial injector at the main combustor where the kerosene fuel and the oxidizer-rich pre-burned gas are burned 5,6 . The swirl coaxial injector discharges liquid propellant in a conical film shape, and this enhances the disintegration of the liquid propellant.…”

Section: Introductionmentioning

confidence: 99%

Effects of Wall-injection Length on Spray Core and Combustion Performance in a Coaxial Porous Injector

Kim¹,

Koo

2014

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

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The mixing performance of an injector determines the combustion performance of a bipropellant rocket engine. A novel coaxial porous injector concept was developed to improve the mixing performance of a shear coaxial injector. It showed higher characteristic velocity efficiency than that of a shear coaxial injector. The combustion flow fields of both injectors were visualized using a high speed shadowgraph technique to observe the geometry factor effect on the spray core length and the combustion performance, as well as the difference of reactive spray behavior between the coaxial porous injector and the shear coaxial injector. Changes in wall-injection length had a non-monotonic effect on both the spray core length and the characteristic velocity efficiency. As opposed to the expected result, the coaxial porous injector with the highest combustion efficiency showed the longest spray core length. The phase change pattern width, caused by the evaporation of liquid fuel, was proportional to the efficiency. Nomenclature c * = characteristic velocity c * CEA = theoretical characteristic velocity D cc = diameter of combustion chamber D G = diameter of gas injector in shear coaxial injector D L = diameter of liquid injector in coaxial porous/shear coaxial injectors D P = diameter of center post in shear coaxial injector D PR = inner diameter of porous cylinder D VIS.= diameter of visualized region J tip = momentum flux ratio calculated at injector tip L cc = length of combustion chamber L ing.= axil distance from injector face to igniter center L PR = axial length of wall-injection area of porous cylinder O/F = oxidizer to fuel P cc = combustion chamber pressure P inj.O = oxidizer pressure upstream of injector P inj.F = fuel pressure upstream of injector R = length of recess in shear coaxial injector R A = ratio of gas to liquid injection area at injector tip t AG = thickness of annular gap in shear coaxial injector t f = thickness of coaxial porous injector face plate T inj.O = oxidizer temperature at injector t PR = thickness of porous cylinder

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History of Liquid-Propellant Rocket Engines in Russia, Formerly the Soviet Union

Cited by 74 publications

References 1 publication

A Numerical Study on Combustion Characteristics of Coaxial-Jet Injectors Using Scaling Techniques in a Subscale Chamber

A Numerical Study on Combustion Characteristics of Coaxial-Jet Injectors Using Scaling Techniques in a Subscale Chamber

Effects of inlet blockage of gas-liquid scheme injector on acoustic tuning for acoustic damping in a combustion chamber

Effects of Wall-injection Length on Spray Core and Combustion Performance in a Coaxial Porous Injector

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