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Sunday, July 26, 2020 | History

3 edition of The measurement of boundary layers on a compressor blade in cascade found in the catalog.

The measurement of boundary layers on a compressor blade in cascade

The measurement of boundary layers on a compressor blade in cascade

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  • 10 Currently reading

Published by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Compressors -- Blades.,
  • Boundary layer.,
  • Cascades (Fluid dynamics)

  • Edition Notes

    StatementWillliam C. Zierke and Steven Deutsch.
    SeriesNASA contractor report -- 185118., NASA contractor report -- NASA CR-185118.
    ContributionsDeutsch, Steven., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15281474M

    An Experimental Study of Three-dimensional High- Speed Air Conditions in a Cascade of Axial-flow Compressor Blades K. W. the flow characteristics of two compressor blade cascades. boundary layers were by no means removed by this technique since only some 3 per cent of the mass flow was extracted, but they were reduced from a thickness. Bypass transition induced by free-stream noise in flow past a blade cascade. Open Archives of the 16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC You J, Zaki TA (). Conditional statistics and flow structures in turbulent boundary layers buffeted by free-stream distur- bances.

    @article{osti_, title = {Flow visualization in a linear turbine cascade of high performance turbine blades}, author = {Wang, H P and Olson, S J and Goldstein, R J and Eckert, E R.G.}, abstractNote = {Multiple smoke wires are used to investigate the secondary flow near the endwall of a plane cascade with blade shapes used in high-performance turbine stages.   The performance of NACA series compressor blade sections in cascade has been investigated systematically in a low-speed cascade tunnel. John R. Systematic Two-Dimensional Cascade Tests of NACA Series Compressor Blades at Low Speeds, report, Septem ; Cited by:

    A previous project built a linear compressor cascade for experimentation with highly loaded blades. This project aims to improve the flow model by adding a moving bar wake generator to simulate rotor blade inches upstream of the blade row to aid the removal of the boundary layers that grow on the walls. The Effect of Upstream Duct Boundary Layer Growth and Compressor Blade Lean Angle variation, on an Axial Compressor Performance. I Templalexis1,*, V Pachidis 2, P Pilidis2, and P Kotsiopoulos1 1Hellenic Air Force Academy, Department of Aeronautical Sciences, Section of Thermodynamics, Power and.


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The measurement of boundary layers on a compressor blade in cascade Download PDF EPUB FB2

The Measurement of Boundary Layers on a Compressor Blade in Cascade Volume I--Experimental Technique, Analysis, and Results (NA_A-CR¥oI-1) THE HEASUREMENT OF i_OUNDAR¥ LAYERS ON A CONPRESSOR BLADE IN CASCADE. VOLUME EXe_:L TE:CHNI_UE e ANALYSIS AN r) RESULTS Final Report (Pennsylvania State uniT.) p • CSCL 21E G3/07File Size: 5MB.

boundary layers and wakes about a double-circular-arc compressor blade in cascade. The highly loaded blades operated near a chord Reynolds number ofand at incidence angles ofand degrees.

These conditions are typical of modern compressor blades and should. Get this from a library. The measurement of boundary layers on a compressor blade in cascade at high positive incidence angle.

II, Data report. [Steven Deutsch; William C Zierke; United States. National Aeronautics and Space Administration.]. Get this from a library. The measurement of boundary layers on a compressor blade in cascade at high positive incidence angle.

I, Experiment techniques and results. [Steven Deutsche; William C Zierke; United States. National Aeronautics and Space Administration.]. A continuing recovery from this leading edge separation is apparent in the measured boundary layer profiles at and percent chord.

Recovery appears to be complete by percent chord. The data then illustrate the evolution of the nonequilibrium turbulent boundary layers as they approach a second region of by: The Measurement of Boundary Layers on a Compressor Blade in Cascade: Part 4—Flow Fields for Incidence Angles of − and − Degrees J.

Turbomach (April, ) Laser-Doppler-Velocimetry Measurements in a Cascade of Compressor Blades at StallCited by: 7. The measurement of boundary layers on a compressor blade in cascade Volume II, Data tables [microform] Responsibility Willliam C.

Zierke and Steven Deutsch. Imprint [Washington, DC]: National Aeronautics and Space Administration ; [Springfield, Va.: For.

growth of boundary layers on compressor end walls and blade surfaces has been investigated by various researchers both in cascades [] and in rotating machines []. In an attempt to optimize the suction slot location, Chen et al. [1] examined the performance. Experimental and Computational Investigation of the Endwall Flow in a Cascade of Compressor Blades [James R.

Carlson] on *FREE* shipping on qualifying offers. This is a NAVAL POSTGRADUATE SCHOOL MONTEREY CA report procured by the Pentagon and made available for public release. It has been reproduced in the best form available to the Pentagon. The boundary layer transition process on compressor blades in a multi-row environment is mainly influenced by incoming periodic wakes generated by the upstream blade row.

To simulate such conditions experimentally, a moving bar wake generator device was used which is arranged in front of a compressor cascade in a high speed wind by: 2. The compressor cascade under examination consists of nine (9) bl a de s i n a li ne a r c on f ig ur a ti on a s s ho wn i n F ig.

The 3 - dimensional blade ge om e t ry is d es cr i b ed in. Boundary layer control plays a decisive role in controlling the performance of axial compressor. Vortex generators are well known as passive control devices of the boundary layer.

Determine the mass flow rate per unit frontal area. Assuming the flow is isentropic, calculate the exit Mach number and the static pressure ratio across the cascade.

A compressor blade design tested in a cascade is found to choke with an inlet Mach number of when the inlet flow angle is 52°.of Geometric Variability on Axial Compressor Performance.

ASME,/Vol. [12] h, Measurement of Boundary Layers on a Compressor Blade in Cascade:Part 2-Suction Surface Boundary Layers. s of different chord cascades at the same relative arc length position aren’t : Chen Fen-fen, Gui Xing-min, Jin Dong-hai, Qiu Dao-bin. IntroductionIn axial-flow compressor blade passages separation of the boundary layer from the blade surfaces increases the losses and reduces the pressure rise.

Separation of either the laminar or turbulent boundary layers can occur, depending on the Reynolds number at which tile passage is Size: 2MB. performance of the boundary layer in the meridional line, measured on different planes of the suction and pressure surface of the blade.

Besides the tip leakage of the blade, with tip clearances of 0% and 1% of the blade span were measured. The experiment was carried out in a File Size: KB.

DCA cascade blade flow, results and discussion Blade boundary layer data The blade boundary layers have been investigated on six measurement sections, respectively: %, % and % of blade chord on suction side (SS); %, % and % of blade chord on pressure side (PS).

Design of turbine cascades with transitional profile boundary layers Gabriel Acacio Alarcon Iowa State University Follow this and additional works at: Part of theMechanical Engineering Commons, and theOil, Gas, and Energy Commons. ize cascade performance and enrich the scarce database.

To satisfy such needs, an experimental study of roughness ef-fects on the performance of a modern compressor blade has been namic measurements have been carried out in a linear cascade. The specific research questions are as follows: sor cascade.

Separated flow can be effectively controlled through the management of blade boundary layer development. Numerical simulations on a highly-loaded, low-solidity compressor cascade indicate that combined blowing and suction flow control technique can significantly improve cascade performance, especially in increasing the cascade loading and static pressure ratio as well as decreasing the loss Cited by: 6.

@article{osti_, title = {Comparison of measurement data at the impeller exit of a centrifugal compressor measured with both pneumatic and fast-response probes}, author = {Roduner, C and Koeppel, P and Kupferschmied, P and Gyarmathy, G}, abstractNote = {The main goal of these investigations was the refined measurement of unsteady high speed flow in a centrifugal compressor .performance of a compressor cascade with a large camber angle.

The flow field of the cascade is measured and the ink-trace flow visualization is also presented. The experimental results show that the boundary layer suction reduces losses near the area of midspan in the cascade most effectively for all suction cases under Size: KB.COMPRESSOR BLADE MEASUREMENT USING 3D LINE SCAN PROFILOMETRY Prepared by Duanjie Li, PhD 6 Morgan, Ste, Irvine CA P: F: