Cryogenic Flow and Atomization from a Coaxial Injector

Gautam, Vivek; Gupta, Ashwani K.

doi:10.2514/1.28921

Cited by 12 publications

(4 citation statements)

References 22 publications

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“…Although there has been no work done on cryogenic jets in crossflow, there have been many studies on cryogenic jets in ambient and co-flow [39,40,41,42]. Such studies have been mostly focused on rocket propulsion; because of this most studies looked at the transcritical -supercritical regime.…”

Section: Cryogenic Jetsmentioning

confidence: 99%

“…(a) Potential core of a cryogenic jet in a co-flow compared to a jet in thermo-equilibrium in coflow adapted from [42] (b) Breakup regimes of cryogenic droplets versus droplets in thermodynamic equilibrium [44] Figure 2.9: Cryogenic vs non-cryogenic breakup [41] used back-lit photography to study supercooled liquid nitrogen. The nitrogen was injected into a pressurized environment about 10 K below its boiling point.…”

Section: Cryogenic Jetsmentioning

confidence: 99%

“…This is the liquid region that is unaffected by the surrounding fluid, and generally can be observed as a continuous dark region in backlit photography. Gautam et al [42] compared the potential core of cryogenic jets to jets in thermodynamic equilibrium. Their results can be seen in Figure 2.9a.…”

Section: Cryogenic Jetsmentioning

confidence: 99%

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Trajectory and Breakup of Cryogenic Jets in Crossflow

Richards

2018

Journal of Propulsion and Power

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This study investigated the breakup processes of subcritical cryogenic jets injected in to subsonic crossflows of heated air. The crossflow speed, temperature, and jet velocity were varied to demonstrate the effect of thermal differences on a jet in crossflow. High speed back-lit photography and Mie scattering were used to examine the primary breakup regimes, trajectory, and breakup points. The breakup regimes show little change from

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Section: Cryogenic Jetsmentioning

confidence: 99%

Section: Cryogenic Jetsmentioning

confidence: 99%

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Trajectory and Breakup of Cryogenic Jets in Crossflow

Richards

2018

Journal of Propulsion and Power

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“…The spray core length is also called the 'liquid intact core length' 10 and 'potential core length'. 11 Before detecting the spray core length, the shadowgraph images of the combustion flow field were converted to the density gradient magnitude images, which represent the root mean square of the x and y direction gradients from 0 (black) to 255 (white). Since a spray core consists of unburned high density propellant, the density gradient image shows the spray core more clearly.…”

Section: E Image Processing Technique: Spray Core Length Detection Amentioning

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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Experimental study of Cryogenic jet injection using centrifugal nozzles at supercritical pressure

Fang,

Qiao,

et al. 2024

Acta Astronautica

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Cryogenic Flow and Atomization from a Coaxial Injector

Cited by 12 publications

References 22 publications

Trajectory and Breakup of Cryogenic Jets in Crossflow

Trajectory and Breakup of Cryogenic Jets in Crossflow

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

Experimental study of Cryogenic jet injection using centrifugal nozzles at supercritical pressure

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