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Tuesday, August 4, 2020 | History

1 edition of The effects of an embedded vortex on a film cooled turbulent boundary layer found in the catalog.

The effects of an embedded vortex on a film cooled turbulent boundary layer

Stephen L. Joseph

The effects of an embedded vortex on a film cooled turbulent boundary layer

by Stephen L. Joseph

  • 344 Want to read
  • 32 Currently reading

Published .
Written in English

    Subjects:
  • Mechanical engineering

  • The Physical Object
    Pagination221 p.
    Number of Pages221
    ID Numbers
    Open LibraryOL25529148M

    Turbulence measurements for a longitudinal vortex interacting with athree-dimensional turbulent boundary layer. Effects of mean flow three dimensionality on turbulent boundary-layer structure. An experimental study of the development of longitudinal vortex pairs embedded in a turbulent boundary layer.   The influence of the wake vortex arising behind a perforated tab on the mixing process in heat exchangers and chemical reactors is analyzed. The preliminary step of this study, i.e., investigation of the turbulent field generated by a single perforated tab, is presented here.

    The area where friction slows down the airflow is called the boundary layer. The boundary layer isn't very deep, maybe to an inch thick, but it's important. It's the source of skin friction drag, and can actually decrease pressure drag. Air flowing in the boundary layer travels in one of two states: laminar flow and turbulent flow. Results are presented that illustrate the effects of single embedded longitudinal vortices on heat transfer and injectant downstream of a row of film-cooling holes in a turbulent boundary layer. Attention is focused on the changes resulting as circulation magnitudes of the vortices are varied from to m{sup 2}/s.

    Effect of Vortex Circulation on Injectant from a Single Film-Cooling Hole and a Row of Film-Cooling Holes in a Turbulent Boundary Layer, Part 2: Injection beneath the vortex upwash by Pisut Kaisuwan Lieutenant Commander, Royal Thai Navy B.S., Royal Thai Navy Academy, THAILAND, Submitted in partial fulfillment.   Although many works have been conducted on curvature induced APG boundary layers, only a few tried to isolate APG effects on supersonic turbulent boundary layer without the impact of wall curvatures. External compression waves induced APG (β max = ) are exerted on a flat-plate supersonic turbulent boundary layer by Fernando and Smits 22


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The effects of an embedded vortex on a film cooled turbulent boundary layer by Stephen L. Joseph Download PDF EPUB FB2

Experimental heat transfer results were obtained with a turbulent boundary layer only, with boundary layer and injection of film cooling, with boundary layer and embedded vortex, and finally with boundary layer, film cooling, and embedded vortex.

The effects of the vortex on heat transfer in the film cooled boundary layer are significant and important: (1) On the downwash side of the vortex, heat transfer is augmented, effects Cited by: 1. Near the downwash side of the vortex, heat transfer is augmented, vortex effects dominate flow behavior, and the protection from film cooling is minimized.

Near the upwash side of the vortex, coolant is pushed to the side of the vortex, locally increasing the protection provided by film by: The effects of the vortex on heat transfer in the film cooled boundary layer are significant and important: (]) On the downwash side of the vortex, heat transfer is augmented, effects of the film cooling are negated and local "hot-spots" will exist in : Stephen Leo Joseph.

Effects of embedded longitudinal vortices on heat transfer in a turbulent boundary layer film cooled from a single injections hole are discussed. Film coolant was injected at blowing ratios to at a freestream velocity of 10 m/s. A single longitudinal vortex was induced upstream of the film cooling by: 2.

Heat transfer effects of longitudinal vortices embedded within film cooled turbulent boundary layers on a flat plate were examined for freestream velocities of 10 m/s and 15 m/s.

A single row of film cooling holes was employed with blowing ratios ranging from to Moderate strength vortices were used having circulation to free stream velocity ratios of Cited by: 1.

Effects of embedded longitudinal vortices on heat transfer in turbulent boundary layers with injection from a single film cooling hole are described. These results were obtained at a freestream velocity of 10 m/s, with a film cooling hole inclined 30 degrees to horizontal and a blowing ratio of about   Basically, vortex generator jets enhance the mixing process embedded in a turbulent boundary layer, see Lachmann ().

Furthermore, a free jet flow increases the turbulent kinetic energy due to its entrainment effect between the shear layers, see Abramovich (). Of particular significance are boundary layer and vortex structural changes which occur at high blowing ratios.

Heat transfer effects of longitudinal vortices embedded within film-cooled turbulent boundary layers on a flat plate were examined for freestream velocities of 10 m/s and 15 m/s, and for blowing ratios ranging from to Ligrani, Phillip M., and Mitchell, Stephen W.

"Effects of Embedded Vortices on Injectant From Film Cooling Holes With Large Spanwise Spacing and Compound Angle Orientations in a Turbulent Boundary Layer." Proceedings of the ASME International Gas Turbine and Aeroengine Congress and Exposition.

Volume 3A: General. Ligrani et al. described the effects of embedded longitudinal vortices on film cooling from a single row of holes in a turbulent boundary layer.

In their study, each hole has 30° inclination angle with respect to the test surface, and spaced 3 hole diameters from neighboring holes. Heat transfer and fluid mechanics data were obtained for a turbulent boundary layer with arrays of embedded streamwise vortices containing both counterrotating and corotating vortex pairs.

The data show that these arrays can cause both large local variations in the heat transfer rate and significant net heat transfer augmentation over large areas. Experiments on vortex shedding from a blunt trailing edge symmetric hydrofoil operating at zero angle of attack in a uniform high speed flow, Re-h = 10(3) - 10(3), where the reference length h is the trailing edge thickness, are reported.

The effects of a tripped turbulent boundary layer on the wake characteristics are analyzed and compared with the condition of. The turbulent boundary-layer stripes underneath the disturbed free stream travel downstream and grow together so that the embedded laminar regions disappear and the boundary layer becomes fully.

Heat transfer effects of longitudinal vortices embedded within film cooled turbulent boundary layers on a flat plate were examined for freestream velocities of 10 m/s and 15 m/s.

Approved for public release; distribution is s of embedded longitudinal vortices on heat transfer in a turbulent boundary layer film cooled from a single injection hole are discussed. Film coolant was injected at blowing ratios to. Experimental results are presented which describe the effects of bulk flow pulsations on film cooled boundary layer structure.

The film is produced by a single row of simple angle film cooling holes and the pulsations are in the form of sinusoidal variations of static pressure and streamwise velocity. Approved for public release; distribution is unlimitedThe effects of longitudinal vortices on film-cooling injectant from a single injection hole and from a row of injection holes in a turbulent boundary layer are investigated.

Attention is focused on the effects of vortex circulation when the injection hole is located beneath the vortex downwash. Effects of Embedded Vortices on Injectant From Film Cooling Holes With Large Spanwise Spacing and Compound Angle Orientations in a Turbulent Boundary Layer (P.

Ligrani and S. Mitchell), ASME Transactions-Journal of Turbomachinery, Vol. Abstract. Approved for public release; distribution is unlimitedResults are presented which illustrated the effects of single embedded longitudinal vortices on heat transfer and injectant downstream of a row of film-cooling holes and downstream of a single hole in a turbulent boundary layer.

As in the preceding study, one objective of the close-up (FOV2) data is the analysis of the incoming boundary layer properties. For that reason, the. The process of film cooling is known to severely disturb the boundary layer around a turbine airfoil.

Since most film-cooled airfoils have more than one injection station, the flow field. P.M. Ligrani, W. WilliamsEffects of an Embedded Vortex Injectant From a Single Film-Cooling Hole in a Turbulent Boundary Layer ASME Journal of Turbomachinery, Vol.

(), pp. Google Scholar.The effect of upstream injection by means of continuous air jet vortex generators (AJVGs) on a shock wave turbulent boundary layer interaction is experimentally investigated.