Porous Injectors in Cryogenic Liquid Propellant Rocket Engines at Sub- and Supercritical Pressures

Lux, Johannes; Suslov, Dmitry; Haidn, Oskar

doi:10.2514/6.2008-947

Cited by 4 publications

(2 citation statements)

References 10 publications

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“…Part of the gaseous fuel was injected through the face plates, which improved the surface cooling. 5 The basic shape of the coaxial-porous injector is similar to that of a shear coaxial injector. However, it differs in that it has a cylindrical sintered metal porous cylinder that surrounds the center post and recessed region.…”

Section: Introductionmentioning

confidence: 99%

Combustion Characteristics on a Coaxial-Porous Injector

Kim

Lee

et al. 2013

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

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A coaxial-porous injector concept for gas-liquid combustion is proposed as a means of improving the mixing performace of a conventional shear-coaxial injector. The coaxialporous injector discharges a gas jet in the normal direction of the center liquid core, and it is expected that the momentum transfer from the radial gas jet to the axial liquid jet occurs more efficiently than it does with a traditional shear-coaxial injector. To validate the effectiveness of this idea, the combustion performances between the coaxial-porous injector and the shear-coaxial injector were compared by conducting a hot-firing test using nitrous oxide-ethanol combinations as propellant. The momentum flux ratio at the injector tip was selected as a spraying condition index, and the characteristic velocity efficiency was considered as a combustion performance parameter. The coaxial-porous injector demonstrated higher combustion efficiency than the conventional shear-coaxial injector, especially at the lower momentum flux ratio condition. In addition, the comparison of spray images between the shear-coaxial and coaxial porous injector supported the results of the hot-firing experiment quite well. Nomenclature AR= ratio of gas to liquid injection area at the tip A cc = combustion chamber area A G = gas injection area at the injector tip A L = liquid injection area at the injector tip A t = nozzle throat area C * = characteristic velocity J tip = momentum flux ratio at the tip of injector J tip,combustion = momentum flux ratio at the tip of injector in conditions of combustion L cc = combustion chamber length L * = characteristic length G m = mass flow rate of gas L m = mass flow rate of liqud OFR = O/F ratio P cc = chamber pressure tot m= total mass flow rates R G = gas constant of oxidizer ρ G = gas density ρ L = liquid density ρ tip = gas density at the tip of injector T G = gas temperature

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Section: Introductionmentioning

confidence: 99%

Combustion Characteristics on a Coaxial-Porous Injector

Kim

Lee

et al. 2013

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

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“…여 연구 중에 있다[2,3]. 폐쇄 사이클 방식 액체 로켓의 주연소기용 2상 유체 분사기는 대부분 동축형으로 설계되며, 기체-액체제트 사이의 분 사속도 차이에 의한 전단력 발생을 통하여 추진 제의 혼합과정이 일어난다.…”

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Combustion Performance of a Coaxial Porous Injector using Ethanol/N₂O Propellant

Kim¹,

Lee

Koo

2013

Journal of the Korean Society of Propulsion Engineers

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The gas jet from a coaxial porous injector for two-phase flows is discharged radially from the porous surface, which encloses the center liquid jet. Several hot-firing test using ethanol/nitrous oxide propellants was conducted to analyze the effect of oxidizer/fuel ratio on the combustion performance, and the uncertainty analysis was performed for the results. The characteristic velocity was affected by oxidizer/fuel ratio similarly with the results of CEA calculation except that the maximum characteristic velocity was appeared in the stoichiometric ratio. The characteristic velocity efficiency was increased as the oxidizer/fuel ratio increases.

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Combustion Characteristics of a Coaxial Porous Injector

Kim

Lee

Koo

2014

Journal of Propulsion and Power

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Porous Injectors in Cryogenic Liquid Propellant Rocket Engines at Sub- and Supercritical Pressures

Cited by 4 publications

References 10 publications

Combustion Characteristics on a Coaxial-Porous Injector

Combustion Characteristics on a Coaxial-Porous Injector

Combustion Performance of a Coaxial Porous Injector using Ethanol/N₂O Propellant

Combustion Characteristics of a Coaxial Porous Injector

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Porous Injectors in Cryogenic Liquid Propellant Rocket Engines at Sub- and Supercritical Pressures

Cited by 4 publications

References 10 publications

Combustion Characteristics on a Coaxial-Porous Injector

Combustion Characteristics on a Coaxial-Porous Injector

Combustion Performance of a Coaxial Porous Injector using Ethanol/N2O Propellant

Combustion Characteristics of a Coaxial Porous Injector

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Combustion Performance of a Coaxial Porous Injector using Ethanol/N₂O Propellant