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1 edition of Testing and Analysis of a Transonic Axial Compressor found in the catalog.

Testing and Analysis of a Transonic Axial Compressor

Testing and Analysis of a Transonic Axial Compressor

  • 130 Want to read
  • 27 Currently reading

Published by Storming Media .
Written in English

    Subjects:
  • SCI085000

  • The Physical Object
    FormatSpiral-bound
    ID Numbers
    Open LibraryOL11850744M
    ISBN 10142356457X
    ISBN 109781423564577

    A set of inlet guide vane (IGV) unsteady surface pressure measurements of a transonic compressor is presented. Using a flexible pressure sensor array, unsteady IGV suction-surface and pressure-surface pressures are acquired for six spanwise by five chordwise locations for various speed lines and throttle settings. Measurements from this sensor array are used to Author: Timothy M. Hutton. Ryan T. Kelly is a Senior Research Scientist at the Notre Dame Turbomachinery Laboratory (NDTL). Dr. Kelly serves as the programmatic and technical lead for research programs in the Notre Dame Transonic Axial Compressor (ND-TAC) facility where he has executed numerous test programs with a focus on axial compressor characterization, stall inception, and stall . @article{osti_, title = {The design, performance and analysis of a high work capacity transonic turbine}, author = {Bryce, J D and Leversuch, N P and Litchfield, M R}, abstractNote = {This paper describes the design and testing of a high work capacity single-stage transonic turbine of aerodynamic duty tailored to the requirements of driving the high-pressure core of a .   Transonic axial-flow compressors are used to obtain relatively high pressure ratios within a single stage. This reduces weight and size and offers a compact design. However, the transonic flow is sensitive to the profile shape and design of rotating and static components. Another important factor is rotor stability when approaching stall conditions. In recent years, .

    In transonic axial compressor, rotor tip leakage vortex interaction with shock layer and shroud boundary layer leads to total pressure loss and initiation of stall phenomenon. Effect of tip winglets are investigated in compressor rotor cascade.


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Testing and Analysis of a Transonic Axial Compressor Download PDF EPUB FB2

Testing and analysis of a transonic axial compressor [Bart L Grossman] on *FREE* shipping on qualifying offers. texts All Books All Texts latest This Just In Smithsonian Libraries FEDLINK (US) Genealogy Lincoln Collection. National Emergency Library.

Top American Libraries Canadian Libraries Universal Library Community Texts Project Gutenberg Biodiversity Heritage Library Children's Library. Open Library. A test program to evaluate a new transonic axial compressor stage was conducted. The stage was designed (by Nelson Sanger of NASA Lewis) relying heavily on CFD techniques while minimizing conventional empirical design methods.

The stage was installed in the NPS Transonic Compressor Test Rig and instrumented with fixed temperature and Pages: and analysis of a transonic axial compressor rotor with splitter blades.

Predictive numerical simulations were conducted experimental dataand were collected at the NPS TPL utilizing the Transonic Compressor Rig. This study advanced the understanding of splitter blade geometry, placement, and performancIn particular, it was e benefits.

Axial-flow compressor analysis under distorted phenomena at transonic flow conditions G Srinivas1, K Raghunandana2* and Shenoy B Satish3 Abstract: Today, the turbomachinery engineering plays a vital role in the field of air breathing propulsion,most importantly the components likecompressor, turbineand itsAuthor: G Srinivas, K Raghunandana, Shenoy B Satish.

Test runs of the transonic axial compressor test rig at the Naval Postgraduate School, Turbopropulsion Laboratory, were conducted in preparation for the installation of a new stage design. Modifications in the cooling air supply to the high speed bearings, and to the design of the torque measuring system were completed during subsequent overhaul.

The data from a two-stage transonic axial compressor (NASA TP) provides the basis for experimental comparisons. In general, the effects of important flow phenomena relative to off-design performance of the transonic compressor are adequately captured, which include the shock loss, second flow and boundary layer : W.

Du, H. Wu, L. Zhang. The influence of wall roughness on the performance of the axial transonic compressor stage was investigated with different values of roughness added to the blade, hub and shroud sections.

The dimensionless sand-grain roughness model was used to capture the roughness effect and the results indicated that the increment of both end wall and blade Author: Zhihui Li, Zhihui Li, Yanming Liu.

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: The overall and blade-element performance of a transonic compressor stage is presented over the stable operating flow range for speeds from 50 to percent of design.

The stage was designed for a pressure ratio of at a flow kg/sec and a tip speed of m/sec. CFD Validation and Analysis of a Single-Stage Axial Compressor 1 October | Applied Mechanics and Materials, Vol. Stall inception and warning in a single-stage transonic axial compressor with axial skewed slot casing treatmentCited by:   Dunker, R., Rechter, H., Starken, H., and Weyer, H.

"Redesign and Performance Analysis of a Transonic Axial Compressor Stator and Equivalent Plane Cascades With Subsonic Controlled Diffusion Blades." Proceedings of the ASME International Gas Turbine Conference and Exhibit. Volume 1: Turbomachinery.

Phoenix, Arizona, USA. March 27–31,   An experimental investigation is conducted to study the details of instability inception in a transonic axial flow compressor. Testing and Analysis of a Transonic Axial Compressor book The experimental results indicate that the compressor instability is initiated through the development of a Cited by: 6.

The design of radial compressor inlets for transonic flow is examined. A theoretical model [1] quantifies the losses in the tip sections caused by the choke margin (incidence) and the blockage of the blades. It identifies clear design rules for the tip sections: to achieve the highest efficiency.

In this work, the tip clearance uncertainties inherent in a transonic axial compressor are quantified to determine their effect on performance. The validated tip clearance losses model in conjunction with the 3D reynolds averaged navier-stokes (RANS) solver are utilized to simulate these uncertainties and quantify their effect on the adiabatic efficiency, total pressure ratio and Cited by: 1.

Although recent advancements in computer capacity have brought computational fluid dynamics to forefront of turbomachinery design and analysis, the grid and turbulence model still limit Reynolds-average Navier-Stokes (RANS) approximations in the multi-stage transonic axial compressor flow : W.

Du, H. Wu, L. Zhang. The information provided in this report is a summary of the research activities completed during the period of July to January Complete details on these research activities are provided in the 48 technical reports and 26 journal articles that were generated throughout the effort.

A listing of these reports and journal articles are provided in the appendix of this : William W. Copenhaver. configuration. Another design and optimization study of a tandem cascade for a transonic compressor was carried out in [10]. Lastly, in [11], a three-dimensional CFD analysis of a transonic axial compressor rotor blade was carried out in order to evaluate its performance at various off-design by: 1.

The objectives of this investigation are 1) to study the shock I vortex interaction in a high speed compressor and its impact on the endwall blockage, and 2) to study the development of the tip leakage vortex within and downstream of the compressor rotor with and without the presence of a rotor passage Size: 1MB.

Design and Analysis of Stator, Rotor and Blades of Axial flow Compressor | ISSN: with transonic relative inlet Mach numbers designed as research unit to study the potentialities and problems arising from the compounding of transonic stages.

Design and Test of a Transonic Axial Splittered Rotor A new design procedure was developed that uses commercial-off-the-shelf software (MATLAB, SolidWorks, and ANSYS-CFX) for the geometric rendering and analysis of a transonic axial compressor rotor with splitter by: 2. continuous operating cold flow transonic test turbine facility, which is a unique combination of a 2 MW axial test turbine and a direct coupled brake compressor.

To cover the losses additional air is provided through aero design strongly supported by nonsteady flow analysis and testing to provide still acceptable stage efficiencies. Much of the theory and research concerning flow in axial compressors is based on studies of isolated airfoils.

The nomenclature and methods used in research in axial compressors, elementary airfoil theory and laminar-flow airfoils are described. Energy increase in. Numerical and experimental investigations were conducted in a transonic centrifugal compressor stage composed of a backswept splittered unshrouded impeller and a vaned diffuser.

A detailed analysis of the flow in the inducer (i.e. the entry zone of the impeller between the main blade leading edge and the splitter blade leading edge) is proposed from Cited by: 4.

An axial compressor is a gas compressor that can continuously pressurize gases. It is a rotating, airfoil -based compressor in which the gas or working fluid principally flows parallel to the axis of rotation, or axially.

This differs from other rotating compressors such as centrifugal compressor. CFD investigation of a stage transonic axial compressor including real geometry e ects Master’s Thesis in Solid and Fluid Mechanics ANTON PERSSON JOSEF RUNSTEN Department of Applied Mechanics Division of Fluid Mechanics Chalmers University of Technology Abstract When designing a transonic multi-stage compressor it is desirable to keep the.

Tip leakage significantly affects the axial-compressor performance (i.e., its pressure ratio, peak efficiency, and surge margin). The size of the clearance is one of the most important parameters in compressor design.

Generally, the tip clearance is uniform from the leading edge to the trailing edge of the compressor-blade section at the by: 1. Features of the Existing Compressor. • 3-stage axial compressor with inlet guide vanes (IGVs) and exit guide vane (EGVs).

• 54 IGVs, 52 rotor blades per stage, 34 stator 1&2 vanes, 58 stator 3 vanes, 60 Size: 3MB. justification of compressor codes with the accessibility of dependable experimental test data by [15].

Since then the analysis of single and multistage axial flow compressor blade passage flow has been developed using a number of three dimensional.

Transonic axial compressor active boundary layer control concept Work motivation Transonic compressors are in wide use now for more than a decade. done in their development allow to steadily increase their performance. The potential pressure ratio, that can be achieved depends mainly on the kinematics of the working channel flo.

transonic stages, an experimental axial-flow compressor having three high-pressure-ratio transonic stages was designed, constructed, and tested at the NACA-Langley laboratory. The design overall total pres- sure ratio was which corresponded to an average stage pressure ratio of approximately Cited by: 1.

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 @ This paper describes the introduction of three-dimension (3-D) blade designs into a 5-stage axial compressor with multi-stage computational fluid dynamic (CFD) methods.

Prior to a redesign, a validation study is conducted for the overall performance and flow details based on full-scale test data, proving that the multi-stage CFD applied is a relatively reliable tool for the analysis of the Cited by: 4.

Transonic Axial Flow Compressor Research Facility [AFCR] Send E-Mail The Axial Flow Compressor Research Rig has been established for undertaking performance evaluation and parametric studies on subsonic and transonic model compressor/fan stages of aircraft and industrial gas turbines and other air pumping machinery.

axial-flow transonic compressor stage is presented. This stage is one of a series of single stages that was designed and tested to investigate the effects of aspect ratio and pressure ratio on the performance characteristics of inlet stages of an advanced-core compressor File Size: 5MB.

(source: Nielsen Book Data) Summary Provides readers with an understanding of aerodynamic design and performance of fans and compressors. The book includes practical emphasis on design problems, experimental facilities and data analysis, together with some design examples and novel concepts.

(source: Nielsen Book Data). Fig. Coordinate System for Axial-Flow Compressor Figure 5 shows the pressure, velocity, and total temperature variation for flow through several stages of an axial compressor. As indicated earlier in figure 3, the length of the blades, and the annulus area, this is the area between the shaft and shroud, decreases.

An axial compressor is a gas compressor that can continuously pressurize gases. It is a rotating, airfoil-based compressor in which the gas or working fluid principally flows parallel to the axis of rotation, or axially. Stalling is an important phenomenon that affects the performance of the compressor.

An analysis is made of rotating stall Author: Rrhb. an Aft-Swept Axial Transonic Compressor Stage Stephan Kablitz, J¨org Bergner, and Dietmar K.

Hennecke compressor test rig (Fig. 1) and a cross-sectional drawing of the compressor stage (Fig. ANALYSIS OF A TRANSONIC COMPRESSOR STAGE FIGURE 7 Speedlines at 80%, 90% and % speed.

Transonic blades are widely used in modern fans/compressor, and are often prone to transonic stall flut-ter at off-design conditions. The flutter problem becomes more and more challenging with the modern light structures of compressor/fan such as blisk or integrated blade disks, which have little mechanical Size: 4MB.

HIGH-FIDELITY SIMULATION OF THE TURBULENT FLOW IN A TRANSONIC AXIAL COMPRESSOR A. Gomar - N. Gourdain - G. Dufour CFD Team, 42 avenue Gaspard Coriolis, CERFACS, Toulouse, France, [email protected] ABSTRACT The present work proposes to use LES in a 3D transonic axial compressor configuration, the NASARotorA small, two-stage, transonic axial compressor was selected for a 5 lb/s airflow, lb/hp h, sfc turboshaft engine at F turbine-inlet gas temperature.

The axial compressor was configured to supercharge a single-stage centrifugal compressor to provide an overall axial/centrifugal pressure ratio of Author: J. V. Davis. Design And Development Of Transonic Axial Flow Compressor Rotor Blade 24 The comparative performance of the baseline compressor and injection compressor at on- design speed and off-design speed.

It is monitored that among the off/on design conditions, the flow follows the consistent patterns and the highest efficiency, stall margin of the.