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Wednesday, July 29, 2020 | History

3 edition of Effects of stator indexing on performance in a low speed multistage axial compressor found in the catalog.

Effects of stator indexing on performance in a low speed multistage axial compressor

Effects of stator indexing on performance in a low speed multistage axial compressor

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  • 37 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C, Springfield, Va .
Written in English

    Subjects:
  • Stators.,
  • Turbocompressors.,
  • Low speed.,
  • Losses.,
  • Stator blades.

  • Edition Notes

    StatementWendy S. Barankiewicz and Michael D. Hathaway.
    SeriesNASA technical memorandum -- 113113., Army Research Laboratory memorandum report -- ARL-MR-370.
    ContributionsHathaway, Michael D., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15498502M

    The SMURF rig is a low-speed multi-stage compressor, representative of a modern high pressure compressor. Each stage has identical geometry, with shrouded stator hub endwalls. For use in this paper, experimental data has been collected from a 1% span shroud clearance build of the rig and a 3% span clearance build. Longley et al. 7 studied the low-speed axial compressor and found the stall happens earlier. Gunn et al. 8 conducted a detailed full-annulus measurements in a low-speed fan stage under 60° inlet total pressure distortion and reported the reduction of % in the efficiency.

    The effects of circumferentially nonuniform tip clearance on axial compressor performance and stability have been investigated experimentally and analytically. A theoretical model for compressor behavior with nonaxisymmetric tip clearance has been developed and used to design a series of first-of-a-kind experiments on a four-stage, low-speed. Low-Speed Axial Compressor (LSAC), which comprises an IGV followed by four geometrically identical stages designed for an accurate low-speed simulation of a high-speed multistage core compressor (Wasserbauer []). In addition, commensurate with the NASA LSAC compressor, the JHU compressor has a long entrance length to develop.

    A comparative study of low-speed axial-flux and low-speed radial-flux permanent-magnet machines is presented. The comparative study concentrates on 55 kW machines with rotation speeds min-1, min-1 and min-1 and is based on calculated designs. A novel comparison method is introduced. Moore RD and Reid L. Performance of single-stage axial-flow transonic compressor rotor and stator aspect ratios of and , respectively, and with design pressure ratio of NASA Report, TP, Google Scholar.


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Effects of stator indexing on performance in a low speed multistage axial compressor Download PDF EPUB FB2

Effects of Stator Indexing on Performance in a Low Speed Multistage Axial Compressor Article (PDF Available) September with 69 Reads How we measure 'reads'.

Barankiewicz, Wendy S., and Hathaway, Michael D. "Effects of Stator Indexing on Performance in a Low Speed Multistage Axial Compressor." Proceedings of the ASME International Gas Turbine and Aeroengine Congress and by: Get this from a library. Effects of stator indexing on performance in a low speed multistage axial compressor.

[Wendy S Barankiewicz; Michael D Hathaway; United States. National Aeronautics and Space Administration.]. Barankiewicz and M. Hathaway, “Effects of stator indexing on performance in a low speed multistage axial compressor,” ASME Paper GT, View at: Google Scholar G. Walker, J. Hughes, I.

Köhler, and W. Solomon, “The influence of wake-wake interactions on loss fluctuations of a downstream axial compressor blade Cited by: 3. [12] Barankiewicz W. and Hathaway M. D., “ Effects of Stator Indexing on Performance in a Low Speed Multistage Axial Compressor,” American Soc.

of Mechanical Engineers Paper GT, Fairfield, NJ, Crossref Google Scholar [13] Walker G. J., Hughes J. D., Köhler I. and Solomon W. by: 8. [13] Barankiewicz W. and Hathaway M. D., “ Effects of Stator Indexing on Performance in a Low Speed Multistage Axial Compressor,” American Society of Mechanical Engineers Paper GT, Crossref Google Scholar [14] Key N.

L., Lawless P. and Fleeter S. London: ASME Gas Turbine Conference, [3] Barankiewicz W S, Hathaway M D. Effects of stator indexing on performance in a low speed multistage ax- ial compressor. NASA TM, [4] Xing X L, Ren M L, Gu Y, et al. Experimental investi- gation of parameter measurements in an axial-flow multistage compressor.

Multistage compressor is the most important constituent of gas turbines used in land, naval and aeronautical applications. Overall performance of such machinery depends mainly on the axial compressor performance. Due to the relative motion between rotor and stator blades, the flow field in this machinery is highly unsteady.

Abstract. The unsteady flowfield in an axial compressor stage (with an inlet guide vane) has been examined experimentally and computationally. In particular, the effects produced by mutually shifting (clocking) the airfoils in the stationary blade rows has been investigated.

Barankiewicz W. S., Hathaway M. Effects of stator indexing on performance in a low speed multistage axial compressor.

ASME International Gas Turbine and Aeroengine Congress and Exhibition, Orlando, Florida, Dorney D. J., Sharma O. P., Gundy Burlet K.-L. Physics of airfoil clocking in a high-speed axial compressor. International Journal. In this paper, the effect of the rotor–stator axial spacing is investigated in an axial pump with the working fluid of water.

The pressure-rise performance was tested at a range of flow rates. Experiments were performed on a low-speed multistage axial-flow compressor to assess the effects of shrouded stator cavity flows on aerodynamic performance. Five configurations, which involved changes in seal-tooth leakage rates and/or elimination of the shrouded stator cavities, were tested.

Based on the appropriate flow loss,the deviation angle models and the blade row-by-blade row cascade model,an engineering method for calculating multistage axial compressor performances has been rmore,the effects of variable stator vane on the flow loss and performance of multistage axial compressor system are result shows that enlarging installation angle.

A multi-stage axial compressor has inherently unsteady flow fields because of the following main reasons: (1) relative positions between rotor and stator airfoil; (2) the buildup of converted wakes lead to complex wake/wake and wake/airfoil interactions. The distributions of the potential flows and wakes in the flow passage are depended on the relative positions of blade rows in axial and.

The strong interaction effects of the bowed stator with the viscous endwall flowfield are shown to be predictable using a three-dimensional multistage Navier–Stokes analysis.

This permits matching of the rotors to the altered stator exit profiles, in order to avoid potential stability limiting interactions. User Tools. Cart. Sign In. Experiments were performed on a low-speed multistage axial-flow compressor to assess the effects of shrouded stator cavity flows on aerodynamic performance.

Five configurations, which involved changes in seal-tooth leakage rates and/or elimination of the shrouded stator cavities, were tested. Data collected enabled differences in overall, individual stage and the third stage blade element. A uniform increase in aspect ratio in a multistage compressor leads to a greater reduction of secondary loss than the same change in aspect ratio of a single blade row.

In literature only the first approach is usually used to estimate the effect of an aspect ratio change on compressor performance. The authors have conducted in their previous studies a series of unsteady RANS (URANS) simulations of a stage high-speed highly-loaded axial-flow compressor, and explored many unsteady effects as well as effects of real geometries such as Variable Stator Vane (VSV) clearance and inter-stage seal leakage flow on the compressor performance.

@article{osti_, title = {The influence of shrouded stator cavity flows on multistage compressor performance}, author = {Wellborn, S R and Okiishi, T H}, abstractNote = {Experiments were performed on a low-speed multistage axial-flow compressor to assess the effects of shrouded stator cavity flows on aerodynamic performance.

Five configurations, which involved systematic changes in seal. compressor boundary layer development are limited to low-speed.-s tage, and/or repeating stage machines. Walker et al. [] investigated suction side stator boundary layer transition in a single stage compressor consisting of an IGV-rotor-stator.

ey clocked the upstream IGV so that the IGV wake provided additional unsteadiness to the downstream.The Potential of Rotor and Stator Clocking in a Stage Low-Speed Axial Compressor GT An Experimental Investigation of Stator Clocking Effects in a Two-Stage Low-Speed Axial Compressor.Additionally, a compressor design was chosen that allows an extension up to three stages with regard to the investigation of multistage axial compressor flow behavior.

Test results of the steady measurements are discussed for IGV, rotor, and stator flow at design conditions as well as the overall stage performance.