Advanced rocket injector development at the Marshall Space Flight Center

Hutt, J.; Cramer, John M.

doi:10.2514/6.1996-4266

Cited by 10 publications

(4 citation statements)

References 9 publications

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“…The facility was originally designed by Schumaker 7,8 based on work conducted at Penn State and NASA Marshall. [9][10][11] It was originally developed to study mixing in reacting and non-reacting coaxial jets under steady operation, and has been described in detail by Schumaker. 8 A schematic diagram of the facility is shown in Figure 1.…”

Section: A Experimental Facilitymentioning

confidence: 99%

Variation of Dominant Instability Mode with Fuel Configuration in an Inverted Coaxial Injector

Dasari

Gamba²

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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We explore the steady and unsteady flame properties of a coaxial jet flame in a moderate pressure combustor with a single shear coaxial injector. Significant flame structure modifications are observed in H2/O2 and CH4/O2 flames at fuel lean conditions over a range of pressure conditions varying from near-atmospheric to about 8 atm. The different stages of flame evolution in H2/O2 flames correspond very well with the different phases of pressure cycles. CH4/O2 flames have a different structure and evolution process as compared to that of H2/O2 flames and also exhibit higher instability limits. The critical equivalence ratio, separating steady and unsteady operation, increases with increase in pressure.

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Section: A Experimental Facilitymentioning

confidence: 99%

Variation of Dominant Instability Mode with Fuel Configuration in an Inverted Coaxial Injector

Dasari

Gamba²

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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“…The Michigan Single Element Injector Experiment, originally designed and sized by Schumaker 1, 13 based on work done at Penn State and NASA Marshall, [14][15][16] is a laboratory scale gas phase rocket engine capable of operations at chamber pressures up to 10 atmospheres. The facility was originally developed to study mixing in reacting and non-reacting coaxial jets, and has been described in detail by Schumaker.…”

Section: A Test Apparatusmentioning

confidence: 99%

Characterization of Unsteady Combustion Phenomena in a University Scale Rocket Combustor

Dasari

Gamba

2015

53rd AIAA Aerospace Sciences Meeting

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We investigate the steady and unsteady flame properties in a moderate pressure, single shear coaxial injector operated with gaseous oxygen/hydrogen and how they relate to the underlying fluid dynamic properties of the flowfield. Under a certain range of conditions, we observe strong modifications of the flame structure as a result of a low-amplitude thermoacoustic instability that develops naturally under fuel-lean conditions. In particular, we observe a periodic evolution of the flame front where ejection events are followed by near-complete extinction and re-ignition. To link the onset of the thermoacoustic instability under fueled (reacting) conditions to the fluid dynamics of the system, we conduct corresponding mixing studies of variable density, non-reacting shear coaxial jets. We particularly investigate the onset and properties of self-excited hydrodynamic instabilities that are observed at high inner-to-outer jet momentum flux ratios. We thus attempt to link them to the unsteady behavior of the corresponding reacting cases. Nomenclature S Density ratio R Velocity ratio Re Reynolds number At Atwood number M Mach number φ Equivalence Ratio J Momentum flux ratio θ Momentum thickness ρ Density v Velocity D Diameter Subscript i Inner stream o Outer stream j Jet exit ∞ Ambient fluid surrounding jets

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“…The design and sizing of the rocket is based on work done at Penn State and NASA Marshall. [18][19][20] The rocket is of a modular design which allows a window section to be moved to any location in the combustion chamber and for the combustion chamber length to be varied by the addition or removal of spacer sections. The 50.8mm x 50.8mm square chamber with rounded corners allows chamber pressures up to 10 atmospheres.…”

Section: Iia Experimental Apparatusmentioning

confidence: 99%

Mixing Lengths of Coaxial Jets in a Rocket Combustor Configuration Using Acetone PLIF

Schumaker¹,

Driscoll²

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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This paper explores the mixing field of non-reacting shear coaxial jets as they apply to rocket fuel injectors; flows characterized by a low-velocity high-density inner jet surrounded by a high-velocity low-density annular jet. Using quantitative acetone PLIF, average and instantaneous mixture fraction fields are obtained while velocity ratio, density ratio and Reynolds number are systematically varied. Using the stoichiometric values of O 2 /H 2 and O2 /CH4, centerline stoichiometric mixing lengths are determined. These lengths are found to scale with the square root of the inner to outer jet momentum ratio. Nomenclature C Scalar concentration d Jet diameter f Mixture fraction based on inner jet fluid L Centerline mixing length M Inner to outer momentum flux ratio = ρ i U 2 i /ρ e U 2 e r u Inner to outer mean velocity ratio S Inner to outer density ratio T P Inner post thickness u Jet exit mean velocity u ee Entrainment velocity u Turbulent intensity ∆t Time interval ρ Density Subscript e Relative to external jet i Relative to inner jet S Relative to stoichiometric value ∞ Relative to ambient fluid surrounding jet

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Advanced rocket injector development at the Marshall Space Flight Center

Cited by 10 publications

References 9 publications

Variation of Dominant Instability Mode with Fuel Configuration in an Inverted Coaxial Injector

Variation of Dominant Instability Mode with Fuel Configuration in an Inverted Coaxial Injector

Characterization of Unsteady Combustion Phenomena in a University Scale Rocket Combustor

Mixing Lengths of Coaxial Jets in a Rocket Combustor Configuration Using Acetone PLIF

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