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3 edition of An investigation of the flow characteristics in the blade endwall corner region found in the catalog.

An investigation of the flow characteristics in the blade endwall corner region

An investigation of the flow characteristics in the blade endwall corner region

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  • 23 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Office in [Washington, DC] .
Written in English

    Subjects:
  • Aerofoils.,
  • Aerodynamics.

  • Edition Notes

    StatementBirinchi K. Hazarika and Rishi S. Raj.
    SeriesNASA contractor report -- 4076., NASA contractor report -- NASA CR-4076.
    ContributionsRaj, Rishi., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18030268M

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An investigation of the flow characteristics in the blade endwall corner region Download PDF EPUB FB2

Get this from a library. An investigation of the flow characteristics in the blade endwall corner region. [Birinchi K Hazarika; Rishi Raj; United States. National Aeronautics and Space Administration.

Scientific and Technical Information Office.]. Three-dimensional (3D) An investigation of the flow characteristics in the blade endwall corner region book separation in a linear highly loaded compressor cascade is studied by using delayed detached-eddy simulation (DDES) method.

This paper studies the flow mechanism of corner separation, including vortical structures and turbulence by: The region around the blade-endwall junction point in inlet guide vane blades of modern gas turbines constitutes one of the hardest “hot spots”, requiring special attention for its cooling.

Three-dimensional separations are an inherent flow feature in the axial compressor corner, formed by the suction surface and the endwall. Its effect will limit the loading and reduce compressor efficiency [1,2,3].With the change of compressor operating conditions, corner separation may develop into corner stall, causing severe passage blockage and sharp.

Number of investigations [9][10][11][12][13][14][15] [16] [17][18] employs fillets on the junction of linear blade/vane stagnation region and endwall An investigation of the flow characteristics in the blade endwall corner region book study the effects on the flow field and.

The endwall heat transfer in the junction region might be increased as much as %. R.S. RajAn Investigation of the Flow Characteristics in the Blade Endwall Corner Region () NASA Contractor Report No.

New York D.P. GeorgiouFilm cooling effectiveness in the region of the blade-endwall corner junction with the injection Cited by: 1. The secondary flow region near the suction surface-casing corner indicated the presence of the passage vortex detached from the vane surface.

The boundary layer code accurately predicts the three-dimensional boundary layers on both vane surfaces and endwall in the regions where the influence of the secondary flow is by: 2. Hazarika, BK, Raj RS () An investigation of the flow characteristics in the Blade Endwall Corner Region.

NASA Contractor Report Google Scholar Hoerner SF () Fluid-Dynamic Drag Google ScholarCited by: 2. A detailed numerical analysis of secondary flows in a transonic turbine is presented in this paper.

The turbine stage is optimized by mitigating secondary flow through the method of non-axisymmetric endwall design. An automated optimization platform of NUMECA/Design3D was coupled with Euranus as a flow solver for the numerical by: 1. A large vortex breaks into many small vortices in the corner separation region, thereby resulting in strong turbulence fluctuation.

The passage vortex transports the low-energetic flow near the endwall to the blade suction surface and enlarges corner separation in the cascade. Hence, total pressure loss increases in the by:   AbstractA combined An investigation of the flow characteristics in the blade endwall corner region book control method based on positively bowed blade and endwall vortex generator jet (VGJ) was performed to a compressor cascade under three kinds of inlet conditions.

The results show that the endwall VGJ can further decrease the total losses in positively bowed cascades. At 0° incidence with zero inlet boundary layer, the separation type Author: Longting Li, Yanping Song, Fu Chen.

For the same reason as in the upright cylinder case, the flow near the lower endwall shows negative pitch angles. Away from the lower endwall, the flow has a positive pitch angle, heading toward the lower endwall at ≤ z/D ≤ When the mainstream flow separates from the cylinder surface, it is turned, resulting in a positive pitch angle.

Abstract. This paper describes the modeling of axial compressor blade rows in an axisymmetric viscous throughflow method. The basic method, which has been reported previously, includes the effects of spanwise mixing, using a turbulent diffusion model, and endwall shear within the throughflow calculation.

Characteristics of End-Wall Flow at Spike and Modal Stall Inceptions in a Variable-Pitch Axial-Flow Fan Reduction of Tip Clearance Losses in an Axial Turbine by Shaped Design of the Blade Tip Region.

Kusterer, N. Moritz, D Performance Evaluation and Endwall Flow Structure Investigation of an S-Shaped Intermediate Turbine Duct.

Lars. Abstract: This article deals with experimental and numerical investigation of flow in an axial turbine stage with prismatic blades which are not equipped with the attention is paid to explain the influence of the radial clearance under the stator blade on the flow around the rotor experiment was performed on the test rig equipped with the water brake.

@article{osti_, title = {An experimental investigation of the rib surface-averaged heat transfer coefficient in a rib-roughened square passage}, author = {Taslim, M E and Wadsworth, C M}, abstractNote = {Turbine blade cooling is accomplished, among other methods, by passing the cooling air through an often serpentine passage in the core of the blade.

Secondary flows have been long recognised as a significant form of loss mechanism in turbomachinery. They have a major influence over the performance of the blade rows since they cause unsteadiness in the mainstream flow. This consequently affects not only the mechanical integrity of the blades but also causes extra loss.

This research is aimed to reduce secondary. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Flow Resistance in Sinuous or Irregular Channels: Usgs Professional Paper D [Leopold, L.

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of GT ASME Turbo ExpoMontreal, Canada, 14–17 May Cited by: 1. Start studying Of Mice and Men Chapters Learn vocabulary, terms, and more with flashcards, games, and other study tools.

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An Experimental Study of Stall Suppression and Associated Changes to the Flow Structures in the Tip Region of an Axial Low Speed Fan Rotor by Axial Casing Grooves Control of the Corner Separation in a Linear Cascade by Trailing Gaps.

Wenfeng Investigation of 3D Blade Design on Flow Field and Performance of a Low Pressure Turbine Stage. Book Summary About Catch; Character List Summary and Analysis Chapters Chapters Chapters Chapters Chapters Chapters Chapters Chapters Within the context of these four sentences, which is the resolution.

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Select two of these contradictions and discuss them in literary terms. Excess blade depth allows the blade to flare outward during the entire cut resulting in a long curve from one corner to another. This is caused by too much blade extending out the bottom of the cutting head.

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This highly unsteady process is measured in great detail at the exit plane pdf the first rotor. The unsteady pdf field is classified into three time periods for one blade passing event.

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