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Wednesday, July 29, 2020 | History

2 edition of Experimental and computational results from a large low-speed centrifugal impeller found in the catalog.

Experimental and computational results from a large low-speed centrifugal impeller

Experimental and computational results from a large low-speed centrifugal impeller

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  • 11 Currently reading

Published by National Aeronautics and Space Administration, U.S. Army Research Laboratory, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Compressors.

  • Edition Notes

    StatementM.D. Hathaway ... [et al.].
    SeriesNASA technical memorandum -- 106421., Army research labratory technical report -- ARL-TR-331., NASA technical memorandum -- 106421., Army research labratory technical report -- ARL-TR-331.
    ContributionsHathaway, M. D., United States. National Aeronautics and Space Administration., U.S. Army Research Laboratory.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14703250M

    Centrifugal compressors are similar to axial compressors in that they are rotating airfoil based compressors as shown in Figure [5] [6] It should not be surprising that the first part of the centrifugal impeller looks very similar to an axial first part of the centrifugal impeller is also termed an fugal compressors differ from axials as they use a . Impeller diameter 2 /mm Impeller outlet width 2 /mm a new volute and built a closed-loop system to successfully carry out self-coupling startup simulation by means of given experimental result of rotational speed [ ]. Except for the pure water medium, on the condition that the transmission medium is solid-liquid two-phase ow, the rst author of.

    Centrifugal compressors, sometimes termed radial compressors, are a sub-class of dynamic axisymmetric work-absorbing turbomachinery.. The idealized compressive dynamic turbo-machine achieves a pressure rise by adding kinetic energy/velocity to a continuous flow of fluid through the rotor or kinetic energy is then converted to an increase in potential .   Wisler () reported that for a low speed four stage compressor the effect of increasing rotor tip clearance from % to % was to reduce the efficiency by % and the peak pressure rise by.

    Centrifugal compressor From Wikipedia, the free encyclopedia Jump to navigation Jump to search. The final objective of the present study is achieved through the comparative study of the predictions obtained against the results of Eckardt's experimental investigation of the viscous compressible flow in a high speed radial impeller operating at design condition and in a backswept impeller at design and off-design : A. Tourlidakis.


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Experimental and computational results from a large low-speed centrifugal impeller Download PDF EPUB FB2

Get this from a library. Experimental and computational results from a large low-speed centrifugal impeller. [M D Hathaway; United States. National Aeronautics and Space Administration.; U.S. Army Research Laboratory.;]. @article{osti_, title = {Off-design flow measurements in a centrifugal compressor vaneless diffuser}, author = {Pinarbasi, A.

and Johnson, M.W.}, abstractNote = {Detailed measurements have been taken of the three-dimensional velocity field within the vaneless diffuser of a backswept low speed centrifugal compressor using hot-wire anemometry. Application of a multi-block CFD code to investigate the impact of geometry modeling on centrifugal compressor flow field predictions Full Record Other Related Research.

The turbulent flow inside a low-speed centrifugal compressor at design condition is investigated using large-eddy simulation (LES) comprising of up to 26 × 10 6 computational volume cells. Unlike in the past, the current study’s special emphasis is placed on the turbulence field evolution inside the by: 6.

Meridional view of the predicted velocity field in the NASA low speed centrifugal compressor with a large impeller tip clearance gap showing front-wall separation in the diffuser.

The computational results indicated that the separation shown in Figure 10 was due to a large region of low-momentum fluid near the impeller : A.J. Strazisar. Experimental and Computational Results From the NASA Lewis Low-Speed Centrifugal Impeller at Design and Part-Flow Conditions J.

Turbomach (January, ) The Performance Evaluation With Diffuser Geometry Variations of the Centrifugal Compressor in a Marine Engine (70 MW) Cited by: 9. Zhu [6] performed experiments on transient performance of a low specific speed centrifugal pump (= 45) during starting and stopping periods with open impeller and.

Experimental and computation investigation of the rotating instability in a centrifugal pump impeller Conference Paper (PDF Available) March with 75 Reads How we measure 'reads'. Theory of operation.

In the case where flow passes through a straight pipe to enter a centrifugal compressor the flow is straight, uniform and has no vorticity, ie swirling motion, so the swirl angle α 1 = 0° as illustrated. As the flow passes through the centrifugal impeller, the impeller forces the flow to spin faster as it gets further from the rotational axis.

Experimental and computational results from a large low-speed centrifugal impeller [microform] [] [Washington, DC]: National Aeronautics and Space Administration: U.S.

Army Research Laboratory ; [Springfield, Va.: National Technical Information Service, distributor, ]. In order to study the near-wall region flow characteristics in a low-specific-speed centrifugal impeller, based on ANSYS-CFX software, Reynolds averaged Navier-Stokes (RANS) methods and renormalization group (RNG) k-ɛ turbulence model were used to simulate the whole flow field of a low specific speed centrifugal pump with five blades under different flow rates.

Author: Weidong Cao, Zhixiang Jia, Qiqi Zhang. The investigation of the clocking effect mainly concentrates on turbines and compressors, but seldom in centrifugal pumps. In this paper, using numerical simulation and experiment, the influence of the clocking effect on the hydraulic performance of centrifugal pump with guide vane is studied.

Numerical simulations with SST k-w turbulence model were applied to obtain the Author: Jiang Wei, Chen Diyi, Yuchuan Wang, Li Ting. impellers of different outlet diameter. The results indicate that the unsteady phenomena at the blade passage frequency clearly depend on the value of the impeller-tongue gap.

Saad [9] investigated the feasibility of controlling the stall in radial diffuser of a low speed centrifugal. In this article, the test pump is a single-stage low-specific speed centrifugal pump.

The main parameters of the pump are as follows: Q = 15 m 3 /h, H = 60 m, n = r/min. The impeller inlet diameter D 1 = 45 mm, impeller outlet diameter D 2 = mm, impeller outlet width b 2 = 5 mm, blade outlet angle β 2 = 31°, blade number Z = 4; volute base diameter D 3 = Cited by: 1.

For the present study, centrifugal pump with rated head, discharge and speed of 20 m, m 3 /s and rpm respectively was selected for the experimental setup. At rated parameters, the maximum efficiency of the pump in pump mode was obtained as %.Six numbers of backward curved vanes having inlet and outlet blade angles as 24° and 19° were provided in the pump Cited by: The present experimental investigation deals with performance improvement of a low-speed centrifugal compressor by inexpensive passive means such as turbulence generator placed at different positions and partial shroud near the rotor blade tip.

The experiments are carried out at three values of tip clearance, namely %, %, and % of rotor blade height at the by: 3. The effects of blade thickness on impeller performance is seldom considered when design the low specific speed centrifugal pump and only considered crowding coefficient when use the speed coefficient method calculate the head of the impeller was designed.

It was didn't consider the fundamental relationship how leaf thickness and low specific speed centrifugal impeller Cited by: 3.

The wind energy pump system is a new green energy technology. The wide high efficiency region of pump is of great significance for energy conservation of wind power pumping system.

In this study, factorial experiment design (FED) and computational fluid dynamics (CFD) are employed to optimize the hydraulic design of wind energy centrifugal pump (WECP). The blade outlet width Cited by: 1. Introduction. Low specific speed centrifugal pumps (30 ≤ n s ≤ 80) have comprehensive applications on the field of aviation, aerospace, petrochemical industry, agricultural irrigation and light industry due to its characteristics of low flow rate and high head [1, 2].

On the basis of the traditional design method, the passages of impeller are long and narrow, which give rise to lots Cited by: 1. The key component that makes a compressor centrifugal is the centrifugal impeller, Figurewhich contains a rotating set of vanes (or blades) that gradually raises the energy of the working gas.

This is identical to an axial compressor with the exception that the gases can reach higher velocities and energy levels through the impeller's. ^ Xu, C. and R.S.

Amano, The Development of a Centrifugal Compressor Impeller, International Journal for Computational Methods in Engineering Science and Mechanics, Volume 10 Issue 4Pages – ^ Xu, C., Design experience and considerations for centrifugal compressor development., J. of Aerospace Eng. igns, this is a simple matter of altering impeller geometry and rotational speed to achieve the desired pressure rise and flow rate.

However, this particular pump was limited by housing geometry and the magnetic bearings that support the impeller. Without much freedom in the overall impeller size, the only parameters open to the designers were the blade profiles and .The computational study of centrifugal compressor is carried out without and with a partial shroud on the tip of the blade with finite volume method upwind scheme using ANSYS CFX software.

Centrifugal compressor impeller with three values of tip clearances i.e., τ = %, % and % of blade height at trailing.