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Thursday, July 16, 2020 | History

1 edition of Redesign of the low speed three stage axial flow compressor test facility found in the catalog.

Redesign of the low speed three stage axial flow compressor test facility

Michael Hans Vavra

Redesign of the low speed three stage axial flow compressor test facility

by Michael Hans Vavra

  • 182 Want to read
  • 40 Currently reading

Published by Naval Postgraduate School in Monterey, California .
Written in English

    Subjects:
  • Naval Postgraduate School (U.S.). Dept. of Aeronautics,
  • Compressors,
  • Aerodynamics,
  • Naval Postgraduate School (U.S.).,
  • Blades

  • About the Edition

    A flow configuration of an existing low-speed, axial flow compressor test facility at the Turbopropulsion Laboratory, Naval Postgarduate School, Monterey, California, was redesigned in order to improve compressor inlet velocity distribution, improve mass flow measurement, and increase the power input. The design of the new configuration, consisting of an inlet nozzle, ducting, throttling device upstream of the compressor, and a diffusor downstream of it, is reported. The redesign is based on using the existing free-vortex type and solid-body type bladings, and the newly designed symmetrical blading. (Author)

    Edition Notes

    Statementby M.H. Vavra, P.F. Pucci [and] W. Schlachter
    ContributionsPucci, Paul F., Schlachter, Wolfgang, Naval Postgraduate School (U.S.)
    The Physical Object
    Pagination60 p. :
    Number of Pages60
    ID Numbers
    Open LibraryOL25498770M
    OCLC/WorldCa432016336

    T-6 Systems. STUDY. Flashcards. Learn. Write. Spell. Test. PLAY. Match. Gravity. Created by. Andrew_Reese4. Terms in this set () Engine phases. Gas generator section (aft half) Four stage axial-flow compressor Single stage centrifugal flow compressor Combustion chamber Single stage compressor turbine Power turbine section (forward half. ing air flow within the compressor be so con- trolled that damage does not occur from avoid- able stalling during part speed operation, and that stalling is absolutely prevented at full speed. During low speed operation, the inlet guide vanes are closed to limit the amount of air flow-.

    Design Methodology of a Two Stage Axial Compressor Special Issue-2, (February ) Abstract The main objective of the paper is creating a method on how one can model an axial flow compressor. A systematic Three dimensional model of a two stage axial compressor has been generated based on the calculated data. Model. Bibliography Includes bibliographical references (p. []). Contents. The axial fan-- reaction and the vector diagram-- the work and flow coefficient diagram-- blade loading parameters-- blade geometry-- aspect ratio-- relative motion effects-- vortex flow-- Mach number effects-- Reynolds number effects-- compressible flow relationships-- the stage characteristic-- the repeating stage.

    In an axial Discharge compressor, flow moves in an axial direction (from left to right in this diagram), rather than in a circular direction as in centrifugal compressors. Axial Centrifugal p Figure 3. Flow exits an axial rotor (left) in an axial direction, while flow from a centrifugal impeller (right) exits radially. Radial Component Tangential. Fouling is the most important performance degradation factor, so it is necessary to accurately predict the effect of fouling on engine performance. In the previous research, it is very difficult to accurately model the fouled axial flow compressor. This paper develops a new performance calculation method of fouled multistage axial flow compressor based on experiment result and operating by: 6.


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Redesign of the low speed three stage axial flow compressor test facility by Michael Hans Vavra Download PDF EPUB FB2

NAVALPOSTGRADUATESCHOOL Monterey,California^0 n ng Superintendent Provost ABSTRACT: Aflowconfigurationofanexistinglow-speed. Redesign of the low speed three stage axial flow compressor test facility by Vavra, Michael Hans.;Pucci, Paul F.;Schlachter, : Download PDF (3 MB) Abstract A flow configuration of an existing low-speed, axial flow compressor test facility at the Turbopropulsion Laboratory, Naval Postgraduate School, Monterey, California, was redesigned in order to improve compressor inlet velocity distribution, improve mass flow measurement, and increase the power input.

The validation carried out demonstrates the applicability of the proposed formulation to low-speed compressors, with successful simulation of all three operating regimes of the compressor. The developed tool is capable of reproducing the full compressor map of a low-speed compressor in less than 72 hours, a computational cost unrivalled by modern 3D classical CFD by: achieving a good high-speed blade shape.

Choice of Blade Profile for Stage Duty GeneralIt is assumed that a primary design objective is a matched compressor, i.e., that all stages operate at their peak efficiency point simultaneously at some mass flow and Size: 1MB.

In this paper, the evolution of the three-dimensional flow structures inside a cantilevered stator of a stage low-speed highly loaded axial compressor as the stator hub clearance varies, and. Flow within the cavities involved low momentum fluid traveling primarily in the circumferential direction at about 40% of the hub wheel speed.

Measurements indicated that the flow v/ithin both cavities was much more complex than flrst envisioned. A vortical flow structure in the meridional plane.

multistage turbine redesign. The test multistage axial-flow turbine and the simulation method The 4-stage low-speed axial-flow turbine extensively documented in literature (AGARD E/TU-4 testcase) [14] has been considered as reference test-case to develop the proposed optimization approach.

This test. SummaryThis report describes a compressor which was designed to give a mean stage temperature rise of 30 des C. It has six stages so that the overall pressure ratio at the design point is 1.

Full details of the factors which led to the form adopted and of the design itself are given in the report. The controller is experimentally validated on a 3-stage low-speed axial flow compression system. multi-stage facility featuring a 3 stage axial flow compressor with inlet guide vane (IGV).

This facility has been used to test a set of datum “conventional” blades at engine representative speeds, the results of which will be used to validate a number of industrial and commercial CFD codes and provide a benchmark for an advanced blade design.

This concept is validated and demonstrated through the design and analysis of two unique aspirated compressor stages: a low-speed stage with a design pressure ratio of at a tip speed of ft/s, and a high-speed stage with a design pressure ratio of at a tip speed of ft/ by: Meherwan P.

Boyce, in Gas Turbine Engineering Handbook (Fourth Edition), Axial-Flow Compressors. An axial-flow compressor compresses its working fluid by first accelerating the fluid and then diffusing it to obtain a pressure increase (Chapter 7).The fluid is accelerated by a row of rotating airfoils or blades (the rotor) and diffused by a row of stationary blades (the stator).

The midspan section of a low speed subsonic turbine stage that is built and tested at DFVLR, Cologne, is redesigned using a new inverse blade design method, where the blade walls move with a virtual velocity distribution derived from the difference between the current and target pressure distributions on the blade by: PEMP Introduction RMD In axial flow compressors, flow enters the first blade row and leaves the last blade row in axial direction.

Flow through the machine is parallel to the axis of the shaft. Axial compressors are characterised by lower pressure ratio per stage at higher mass flow rates compared to centrifugal compressors; and hence these machines are preferred for civil and.

This paper tries to investigate the feasibility of using axial compressors at this Re. It starts by presenting the low Retest facility and the single stage compressor designed for Re= 6 The aerodynamics at the design operating point and at stall are presented, focusing on the dif-ferences in the measurements from the design : Konstantinos Pantelidis.

NASA Contractor Report 3 70 1 Axial Compressor Middle Stage Secondary Flow Study Joel H. Wagner, Robert P. Dring, and H. David Joslyn on the average inlet flow speed) of x lo5 to x Boundary layer sults were obtained in an axial flow compressor by Phillips and Head File Size: 5MB.

Hah, Chunill, Hathaway, Michael, and Katz, Joseph. "Investigation of Unsteady Flow Field in a Low-Speed One and a Half Stage Axial Compressor: Effects of Tip Gap Size on the Tip Clearance Flow Structure at Near Stall Operation." Proceedings of the ASME Turbo Expo Turbine Technical Conference and Exposition.

Volume 2D: Turbomachinery Cited by: 7. Air to fuel ratio Fuel flow rate Axial velocity ratio 1 Kg/s Isentropic efficiencies of compressor "η c", turbine, η t, intake, η i, propelling Nozzle "η j" in percentage 80, 93, and 95 respectively.

Velocity Triangles A cross section and a top view of a typical axial-flow compressor and flow though a File Size: KB. This book provides a thorough description of an aerodynamic design and analysis systems for Axial-Flow Compressors.

It describes the basic fluid dynamic and thermodynamic principles, empirical models and numerical methods used for the full range of procedures and analytical tools that an engineer needs for virtually any type of Axial-Flow Compressor, aerodynamic design or analysis by:.

In a dual axial-flow compressor, the first stage turbine drives. In a turbine engine with a dual-spool compressor, the low speed compressor. seeks its own best. Stator blades in the compressor section of an axial-flow turbine engine.

decrease the air velocity and prevent swirling.Two Dimensional Design of Axial Compressor Main Characteristics Page 6 Axial compressor can elaborate a higher flow than the radial, which has a higher pressure ratio per stage, this means that for the same flow rate the firsts will have a smaller diameter, but it will need more stages to reaches the same pressure ratio.LOW SPEED AXIAL COMPRESSOR The NASA LSAC test facility was utilized for this study.

The LSAC facility is described in detail in Refs. 1 through 3, so only the basic characteristics are stated here. The research compressor comprises an inlet guide vane row followed by four geometrically identical axial stages (rotors and stators).

The case radius isCited by: 4.