Discussion: “Study of Lubricant Jet Flow Phenomena in Spur Gears—Out of Mesh Condition” (Townsend, D. P., and Akin, L. S., 1978, ASME J. Mech. Des., 100, pp. 61–68)

Lubricant jet flow impingement and penetration depth into a gear tooth space were measured at 4920 and 2560 using a 8.89-cm- (3.5-in.) pitch dia 8 pitch spur gear at oil pressures from 7 × 104 to 41 × 104 N/m2 (10 psi to 60 psi). A high speed motion picture camera was used with xenon and high speed stroboscopic lights to slow down and stop the motion of the oil jet so that the impingement depth could be determined. An analytical model was developed for the vectorial impingement depth and for the impingement depth with tooth space windage effects included. The windage effects on the oil jet were small for oil drop size greater than 0.0076 cm (0.003 in.). The analytical impingement depth compared favorably with experimental results above an oil jet pressure of 7 × 104 N/m2 (10 psi). Some of this oil jet penetrates further into the tooth space after impingement. Much of this post impingement oil is thrown out of the tooth space without further contacting the gear teeth.

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Jet flow phenomena during nucleate boiling

International Journal of Heat and Mass Transfer ◽

10.1016/s0017-9310(01)00246-0 ◽

2002 ◽

Vol 45 (6) ◽

pp. 1359-1363 ◽

Cited By ~ 43

Author(s):

H. Wang ◽

X.F. Peng ◽

B.X. Wang ◽

D.J. Lee

Keyword(s):

Jet Flow ◽

Nucleate Boiling ◽

Flow Phenomena

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Jet Flow Phenomena

Micro Transport Phenomena During Boiling ◽

10.1007/978-3-642-13454-8_4 ◽

2010 ◽

pp. 60-91

Author(s):

Xiaofeng Peng

Keyword(s):

Jet Flow ◽

Flow Phenomena

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Comment on the paper by H. Wang, X.F. Peng, B.X. Wang, and D.J. Lee “Jet flow phenomena during nucleate boiling” IJHMT 45 (6) (2002) 1359–1363

International Journal of Heat and Mass Transfer ◽

10.1016/s0017-9310(03)00019-x ◽

2003 ◽

Vol 46 (14) ◽

pp. 2711-2712 ◽

Cited By ~ 6

Author(s):

I.G Shekriladze

Keyword(s):

Jet Flow ◽

Nucleate Boiling ◽

Flow Phenomena

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Lubricant Jet Flow Phenomena in Spur and Helical Gears With Modified Center Distances and/or Addendums—For Out-of-Mesh Conditions

Journal of Mechanisms Transmissions and Automation in Design ◽

10.1115/1.3258686 ◽

1985 ◽

Vol 107 (1) ◽

pp. 24-30 ◽

Cited By ~ 3

Author(s):

L. S. Akin ◽

D. P. Townsend

Keyword(s):

Computer Program ◽

Computer Analysis ◽

Inclination Angle ◽

High Speed ◽

Jet Flow ◽

Limit Values ◽

Helical Gears ◽

Flow Phenomena ◽

Nozzle Orientation

The work reported is an extension from a previous study which was limited to standard centers and tooth proportions only. This paper includes long and short addendums and modified center distances. The analysis develops the equations for the limit values of variables necessary to remove prior severe limitations or constraints necessary to facilitate computer analysis. A new computer program IMPOUT2 has been developed using these newly established “Limit Formulas” to prevent negative impingement on the pinion. The industrial standard nozzle orientation usually found where the offset S = 0 and inclination angle β = 0 will often cause the pinion to be deprived of primary impingement which can be an important cause of incipient scoring failure in high-speed drives.

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Investigation on Plasma Jet Flow Phenomena During DC Air Arc Motion in Bridge-Type Contacts

Plasma Science and Technology ◽

10.1088/1009-0630/18/5/07 ◽

2016 ◽

Vol 18 (5) ◽

pp. 485-489

Author(s):

Guofu Zhai ◽

Kai Bo ◽

Mo Chen ◽

Xue Zhou ◽

Xinlei Qiao

Keyword(s):

Plasma Jet ◽

Jet Flow ◽

Flow Phenomena ◽

Bridge Type

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Interaction of Wake and Propulsive Jet Flow of a Generic Space Launcher

Notes on Numerical Fluid Mechanics and Multidisciplinary Design - Future Space-Transport-System Components under High Thermal and Mechanical Loads ◽

10.1007/978-3-030-53847-7_8 ◽

2020 ◽

pp. 129-143

Author(s):

Alexander Barklage ◽

Rolf Radespiel

Keyword(s):

Pressure Ratio ◽

Jet Flow ◽

Main Body ◽

Outer Flow ◽

Passive Flow Control ◽

Flow Control Devices ◽

Flow Phenomena ◽

Dual Bell ◽

Propulsive Jet ◽

Space Launcher

Abstract This work investigates the interaction of the afterbody flow with the propulsive jet flow on a generic space launcher equipped with two alternative nozzle concepts and different afterbody geometries. The flow phenomena are characterized by experimental measurements and numerical URANS and LES simulations. Investigations concern a configuration with a conventional truncated ideal contour nozzle and a configuration with an unconventional dual-bell nozzle. In order to attenuate the dynamic loads on the nozzle fairing, passive flow control devices at the base of the launcher main body are investigated on the configuration with TIC nozzle. The nozzle Reynolds number and the afterbody geometry are varied for the configuration with dual-bell nozzle. The results for integrated nozzles show a shift of the nozzle pressure ratio for transition from sea-level to altitude mode to significant lower levels. The afterbody geometry is varied including a reattaching and non-reattaching outer flow on the nozzle fairing. Investigations are performed at supersonic outer flow conditions with a Mach number of $$Ma_\infty =3$$. It turns out, that a reattachment of the outer flow on the nozzle fairing leads to an unstable nozzle operation.

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