Characterisation of Main Chamber Injectors for GOX/Kerosene in a Single Element Rocket Combustor

Soller, Sebastian; Wagner, Róbert; Martin, Philip; Maeding, C.

doi:10.2514/6.2005-3750

Cited by 17 publications

(10 citation statements)

References 12 publications

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“…Jong Gyu Kim et al 6 had found that the spray characteristics and mixing efficiency of the GCSC injector are decided by the recess ratio and momentum flux ratio. S. Soller et al 7 had tested two different type GO 2 /kerosene injectors in a single element combustor with a wide variety of design parameters. Gregor Schlieben et al 8 had minutely studied the Dynamic Characterization of Double Swirl Injectors.…”

Section: A Injectormentioning

confidence: 99%

“…The GH 2 /GO 2 ejector rocket chamber is widely used in the RBCC propulsion system [1][2][3][4] , while the GO 2 /kerosene ejector rocket chamber is not usually found in the RBCC propulsion system. But the GO 2 /kerosene injector itself had been deeply researched all around the world.…”

Section: Introductionmentioning

confidence: 99%

“…5-5.5), scramjet-mode (Ma=5. [5][6][7][8][9][10][11][12], when the flight altitude is too high for the engine to catch enough air to produce thrust the engine come to pure-rocket mode. In order to research how do the different inject ratio under those diverse modes work on the engine performance in the direct-connection ground-tests, the ejector rocket chamber was required to work steadily in a wide total mass flow rate range of 500g/s to 1200 g/s, chamber pressure of 2 MPa, and mixture ratio of O/F=1.…”

Section: Introductionmentioning

confidence: 99%

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Experimental Investigations of a GO2/Kerosene Ejector Rocket Chamber for the RBCC Propulsion System

Zhu

Tian²,

Li³

et al. 2014

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

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A GO 2 /kerosene ejector rocket chamber was designed and tested to meet the requirements of the direct-connection tests of the RBCC engine model, and its performance was experimentally and numerically evaluated. Such an ejector rocket chamber is required to operate in a very wide range of total mass flow (̇= .~. / ). To realize such a wide work range by one set of ejector rocket chamber, double-recessed-coax-swirl (DRSC) spray nozzles were firstly designed and installed in a low mass flow rate range (̇=~/ ) ejector rocket chamber. The rocket was tested both separately and jointly with the RBCC engine. The * of the rockets were ranged from 88% to 98%, and it was positively influenced by the momentum flux ratio and the pressure drop ratio of the injector. The improved spray nozzles were used and tested perfectly in the high mass flow rate range ejector rocket chamber. No thermal damage occurred under all operating conditions, and steadily operation was achieved as well. NomenclatureC * = characteristic velocity ℎ * = theory characteristic velocity * = experimental characteristic velocity p c = rocket chamber pressure ̇ = total mass flow rate ̇O = oxygen mass flow rate ̇k ero = kerosene mass flow rate ̇N = force coefficient in the y direction A t = Area of the throat O/F = mixture ratio =m o /m f O2 = flow coefficient of oxygen kero = flow coefficient of kerosene O2 = pressure upstream of the oxygen sonic nozzle kero = pressure upstream of the kerosene venturi tube * = characteristic velocity efficiency g = outlet pressure of the gas hole g = jet velocity of the gas l = outlet pressure of the kerosene channels la = axis jet velocity of the kerosene = momentum flux ratio Δ = pressure drop Δ = pressure drop ratio1 PHD student, school of astronautics, zhushaohua@sa.buaa.edu.cn 2 PHD student, school of astronautics, tianliangg@sina.com 3 Graduate student, school of astronautics, onecangzhitao@hotmail.com 4 Professor, school of astronautics,

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Section: A Injectormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Experimental Investigations of a GO2/Kerosene Ejector Rocket Chamber for the RBCC Propulsion System

Zhu

Tian²,

Li³

et al. 2014

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

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“…In [21], it was found that the discharge coefficient of a coaxial swirl injector that injects oxygen gas increased from 0.44 to 0.63 when the mass flow rate varied from 95 to 115 g/s. For the swirl injector designed for this paper, the flows ranged between 6 and 14 g/s for C d from 0.52 to 0.49, respectively.…”

Section: Calculation Of C Dmentioning

confidence: 99%

Performance analysis of injectors for a hybrid propulsion system

Pedreira

Dutra

Oliveira

et al. 2019

J Braz. Soc. Mech. Sci. Eng.

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This paper presents a study about injectors, where the radial injector was evaluated. This type of injector was chosen because only a small amount of information on it was found. Thus, the radial injector will be compared with other two types of injectors, the orifice plate and the swirl, in terms of parameters, such as discharge coefficient (C d), regression rate r, and specific impulse (I sp). In respect of the regression rate, the values appeared increasingly with the test pressure and, consequently, with the injection pressure. Thus, each injector model responded in the same way as for the regression rate behavior; however, the same behavior was not observed in relation to the specific impulse.

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“…For film cooling and CMC material investigation tests, a water cooled combustion chamber setup with an inner diameter of 37 mm (see Figure 1) was designed, manufactured and commissioned 1 .The design is based on experiences gained during past campaigns on a hardware with an inner chamber diameter of 20 mm 2,3 . The main geometric features of this combustion chamber are summarized in Table 1.…”

Section: A Combustion Chamber Characteristicsmentioning

confidence: 99%

Dynamic Characterization of Double Swirl Injectors for GOX/Kerosene

Schlieben¹,

Kirchberger²,

Hupfer³

et al. 2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The Institute for Flight Propulsion (LFA) of the Technische Universität München (TUM) operates a high pressure combustion facility, which serves as a testbed for injector element characterization, film and transpiration cooling as well as material compatibility tests both in national and international research programs. Especially tests to characterise film and transpiration cooling require efficient and stable combustion with minimum pressure oscillations in the chamber. During some test campaigns, the baseline injector showed increased HF pressure oscillations, which had not been observed during the commissioning of the injector in the past. A detailed analysis was performed identifying possible causes for the HF oscillations. Consequently, the possible mechanisms were investigated in a dedicated test campaign, leading to an optimized design of the injector.

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Characterisation of Main Chamber Injectors for GOX/Kerosene in a Single Element Rocket Combustor

Cited by 17 publications

References 12 publications

Experimental Investigations of a GO2/Kerosene Ejector Rocket Chamber for the RBCC Propulsion System

Experimental Investigations of a GO2/Kerosene Ejector Rocket Chamber for the RBCC Propulsion System

Performance analysis of injectors for a hybrid propulsion system

Dynamic Characterization of Double Swirl Injectors for GOX/Kerosene

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