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Thursday, May 14, 2020 | History

3 edition of Design of a low aspect ratio transonic compressor stage using CFD techniques found in the catalog.

Design of a low aspect ratio transonic compressor stage using CFD techniques

Design of a low aspect ratio transonic compressor stage using CFD techniques

  • 238 Want to read
  • 31 Currently reading

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

    Subjects:
  • Compressor rotors.,
  • Computational fluid dynamics.,
  • Design analysis.,
  • Low aspect ratio.,
  • Stators.,
  • Transonic compressors.,
  • Turbomachinery.

  • Edition Notes

    StatementNelson L. Sanger.
    SeriesNASA technical memorandum -- 106636.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17000312M

    Coordinates for a high performance pressure ratio centrifugal compressor [microform] / Ted F. McKain and Greg J. Holbrook National Aeronautics and Space Administration ; National Technical Information Service, distributor [Washington, DC: Springfield, Va Australian/Harvard Citation. McKain, Ted F. & Holbrook, Greg J. & United States. In various applications the use of sorption chillers and heat pumps is limited by the available temperature level of the driving heat source or the heat sink for export of reject heat. These constraints can be overcome by integrating an efficient high-speed transonic turbo-compressor into the internal cycle of a thermally driven water/lithium bromide absorption heat : Thomas Eckert, Leo Dostal, Martin Helm, Christian Schweigler.

    Design of a Low Aspect Ratio Transonic Compressor Stage Using CFD Techniques 1 July | Journal of Turbomachinery, Vol. , No. 3 Dynamic stability derivatives evaluation in a low Cited by: 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.

    are computationally expensive in nature, and their use in design optimisation becomes infeasible for large design problems given a limited computational budget. This paper addresses the aerodynamic shape optimisation of a transonic compressor rotor on a limited computational budget. Although centrifugal compressors are widely used in construction, they consume a large amount of energy; in existing multistage centrifugal compressors, there is a serious pressure loss of ~% when gas flows through the diffuser, bend, and return channel. In this study, we analyze the loss mechanisms of these stages in detail, using computational fluid by: 2.


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Design of a low aspect ratio transonic compressor stage using CFD techniques Download PDF EPUB FB2

A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory. The design relied heavily on CFD techniques while minimizing conventional empirical design methods.

The low aspect ratio () rotor has been designed for a specific head ratio of and a tip relative inlet Mach number of Overall stage pressure ratio is A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory. The design relied heavily on CFD techniques while minimizing conventional empirical design methods.

The low aspect ratio () rotor has been designed for a specific head ratio of and a tip relative inlet Mach number of Cited by: 1. A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory.

The design relied heavily on CFD techniques while minimizing conventional empirical design methods. The low aspect ratio () rotor has been designed for a specific head ratio of and a tip relative inlet Mach number of Cited by: A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory.

The design relied heavily on CFD techniques while minimizing conventional empirical design methods. The low aspect ratio () rotor has been designed for a specific head ratio of and a tip relative inlet Mach number of Author: Nelson L.

Sanger. The design relied heavily on CFD techniques while minimizing conventional empirical design methods. The low aspect ratio () rotor has been designed for a specific head ratio of and a tip.

Sanger N () Design of a low aspect ratio transonic compressor stage using cfd techniques. J Turbomach (3) Shepard D () A two-dimensional interpolation function for irregularly-spaced by: The studied rotor, NASA rotor67, is a low aspect ratio design rotor and is the flrst stage rotor of a two-stage fan.

The rotor has a design pressure ratio of at a mass °ow rate of kg/sec. The design rotational speed is 16, rpm, which yields a tip speed of Cited by: A numerical analysis was carried out on the effects of low-aspect ratio and aerodynamic sweep on axial transonic compressor design based on RANS Equations by S.

Puterbaugh, C Hah and Wadia A R[11]. From analysis it was found that, the upswept rotor. With its low aspect ratio and large tip clearance, the compressor stage features pronounced three-dimensional flows in the endwall regions.

The general design parameters are listed in Table 1. More information about this compressor Figure 1: DLR Transonic Compressor Stage Test Rig [5]. This paper has employed a non-uniform stator loss reduction design strategy to make a redistribution of stator incidence at the compressor off-design working point so as to reduce the potential separation loss and enhance the stage aerodynamic performance.

the high-performance low-aspect ratio transonic fan stage NASA St which is a Author: Hanan Lu, Zhe Yang, Tianyu Pan, Qiushi Li.

based on low-discrepancy Halton and Sobol sequences are used. NASA Rotor 37 was chosen as a test case as it is freely available and experimental data for CFD validation exists. It is a low-aspect ratio transonic axial compressor rotor with 36 blades originally designed as an inlet stage for an eight-stage core compressor with a pressure ratio.

The transonic compressor stage chosen for study has a competence of generating stage total pressure ratio, absorbing air mass flow rate of 23 kg/s at corrected rated design speed of RPM. Transonic fan and compressor design Show all authors.

H., Wadia, A. Low aspect ratio transonic rotors: Part 1—Baseline design and performance. Trans. ASME, J. Effect of a mismatch between the buttons of variable stator vanes and the flowpath in a highly loaded transonic compressor stage.

ASME paper GT, Cited by: Get this from a library. Design of a low aspect ratio transonic compressor stage using CFD techniques. [Nelson L Sanger; United States. National Aeronautics and Space Administration.].

Design And Development Of Transonic Axial Flow Compressor Rotor Blade 23 Meshing of the computational domain is made using CFD as shown in Figurethe discretisation of the Hybrid structured grid elements were generated. Figure1. Rotor Blade with Circular Jet Enclosure Figure 2.

Wheel Rotor Assembly Figure 3. Mesh Rotor Blade III. A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory.

The design relied heavily on CFD techniques while minimizing conventional empirical design methods. The low aspect ratio () rotor has been designed for a specific head ratio of and a tip relative inlet Mach number of Transonic axial flow compressors are today widely used in aircraft engines to obtain maximum pressure ratios per single-stage.

Fig. 1 shows the fan of the EJ engine as an example for highly loaded, high performance transonic rotors. Download: Download full-size image Fig.

by: The study is focused on the analysis of the flow structure within the vaned diffuser of a transonic high-pressure centrifugal compressor stage. The analyzed time-dependent flow field comes from unsteady computations of the stage using a 3D Navier-Stokes code with a phase-lagged technique, at an operating point close to the design point.

A good comparison with available experimental data Cited by: redesign the NACA 8-stage transonic compressor [19] by using its design variables.

The velocity triangles and blade speci cations of the redesigned compressor are compared with those of the NACA 8-stage compres-sors and the three-dimensional geometry of redesigned compressor is presented.

Design variablesAuthor: R. Azizi, R. Ebrahimi, M. Ziabasharhagh. 3-D Compressor Rotor A low aspect ratio transonic inlet rotor for a core compressor, designated NASA ro was used as a 3-D compressor test case. The rotor was originally designed and tested at NASA Glenn Research Center in the late ’s by Reid and Moore.3,4 It has 36 multiple-circular-arc blades and a design pressure ratio of.

Automated Multidisciplinary Optimization of a Transonic Axial Compressor (AIAA) 47th AIAA Aerospace Sciences Meeting 5 – 8 JanuaryOrlando, USA Ulrich Siller, Christian Voß, Eberhard Nicke German Aerospace Center (DLR) Institute of Propulsion Technology Fan and Compressor Department Cologne, Germany @Abstract.

The use of a planar non-intrusive measurement techniques such as Digital Particle Image Velocimetry (DPIV) have made it possible to investigate many aspects of unsteady flows previously considered difficult due to the effect of a measurement probe on the flow field, or too time consuming because of the pointwise nature of Laser Doppler Velocimetry or Laser Transit by: 1.CFD investigation of a stage transonic axial compressor including real geometry e ects a preliminary design is set, CFD analysis using a higher delity model is desired to When designing a transonic multi-stage compressor it is desirable to keep the develop.