PDF Publication Title:
Text from PDF Page: 001
S iL THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS 345 E. 47 St., New York, N.Y. 10017 The Society shall not be responsible for statements or opinions advanced in papers or in dis- cussion at meetings of the Society or of its Divisions or Sections, or printed in its publications. Discussion is printed only if the paper is published in an ASME Journal. Papers are available from ASME for fifteen months after the meeting. 91-GT-220 Printed in USA. Copyright © 1991 by ASME The Design and Testing of a Radial Flow Turbine for Aerodynamic Research ABSTRACT This paper describes the design of a high-speed radial inflow turbine for use as part of a gas-generator, and the design of a large- scale (1.2 m tip dia.) low-speed model of the high-speed turbine. Stream-line curvature throughflow, two-dimensional blade-to-blade and fully three-dimensional inviscid and viscous calculation methods have been used extensively in the analysis of the designs. The use of appropriate scaling parameters and their impact on turbine performance is discussed. A simple model shows, for example, how to model the blade lean in the inducer which serves to balance the effect of meridional curvature at inlet to the rotor and can be used to unload the rotor tip. A brief description of the low speed experimental facility is followed by a presentation and discussion of experimental results. These include surface flow visualisation patterns on both the rotor and stator blades and blade row exit traverses. INTRODUCTION Radial inflow turbines offer several advantages for use in small turboshaft applications when compared with axial turbines for the same duty. This is because the radial inflow turbine offers greater work extraction per stage at comparable or higher efficiencies, increased ruggedness, lower costs of manufacture and improved packaging when used in conjunction with a reversed flow combustor. Studies at Rolls-Royce have shown that a cooled, high-efficiency radial turbine could offer significant improvements in performance as the gas-generator turbine of a high technology turboshaft engine, if small improvements in current levels of technology could be achieved. An un-cooled radial turbine of a similar aerodynamic duty would also present an attractive proposition in smaller power-plants. However, the problems facing the designers of today's radial turbines are not inconsiderable, particularly in the areas of rotor cooling and rotor aerodynamics. Many of the published design methods are largely based on the design rules developed by NASA and others (e.g. Hiett and Johnston (1963), Rohlik (1975) and Glassman (1976)). These methods or their adaptations for specific applications are essentially based on observations of the overall performance of radial turbines. Very few are based on observed physical processes even though many of the flow and loss models purport to model the details of the flow. In such circumstances, the possession of one-dimensional information and models places potentially unnecessary restrictions on the design process. Today, commercial organisations are replacing costly experimental development programmes by the use of modern CFD codes such as the viscous analysis code of Dawes (1986) but until the reasons behind such phenomena as 'incidence shock-loss' or tip clearance losses are understood trial and error will play a large part in any design process. This paper describes the initial stages of a research and development programme in radial turbines which addresses the identification and understanding of the major sources of loss and the assessment of aerodynamic design and analysis methods. A large- scale, low-speed radial inflow model turbine has been constructed at the Whittle Laboratory, Cambridge University as part of the research programme. The model is based on a low cost, high pressure ratio, un-cooled turbine which is designed to be scaled for turboshaft applications in the range of 50 to 300 kW. This paper describes the design of the base turbine, the scaling of this turbine which is required to produce the aerodynamic model and presents the results of an initial investigation using the model turbine. NOMENCLATURE b c „1 Re U V W Yp Z μ V p 0 S2 Subscripts m 9 0 1 2 3 4shroud 4hub rotor span radial chord Reynolds number blade speed absolute velocity relative velocity pressure loss coefficient: 1 I U32) - (pOre1pU 2)) (P03re1 P03 - P3 number of blades dynamic viscosity kinematic viscosity density boundary layer momentum thickness rotational speed meridional tangential (pitchwise) stagnation conditions stator inlet stator exit rotor inlet rotor exit shroud rotor exit hub I. HUNTSMAN & H. P. HODSON Whittle Laboratory Cambridge University England S. H. HILL Rolls-Royce plc Leavesden England Presented at the International Gas Turbine and Aeroengine Congress and Exposition Orlando, FL June 3-6, 1991 This paper has been accepted for publication in the Transactions of the ASME Discussion of it will be accepted at ASME Headquarters until September 30, 1991 Downloaded from http://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1991/78989/V001T01A077/2400491/v001t01a077-91-gt-220.pdf by guest on 23 January 2021PDF Image | Design and Testing of a Radial Flow Turbine for Aerodynamic Research
PDF Search Title:
Design and Testing of a Radial Flow Turbine for Aerodynamic ResearchOriginal File Name Searched:
v001t01a077-91-gt-220.pdfDIY PDF Search: Google It | Yahoo | Bing
NFT (Non Fungible Token): Buy our tech, design, development or system NFT and become part of our tech NFT network... More Info
IT XR Project Redstone NFT Available for Sale: NFT for high tech turbine design with one part 3D printed counter-rotating energy turbine. Be part of the future with this NFT. Can be bought and sold but only one design NFT exists. Royalties go to the developer (Infinity) to keep enhancing design and applications... More Info
Infinity Turbine IT XR Project Redstone Design: NFT for sale... NFT for high tech turbine design with one part 3D printed counter-rotating energy turbine. Includes all rights to this turbine design, including license for Fluid Handling Block I and II for the turbine assembly and housing. The NFT includes the blueprints (cad/cam), revenue streams, and all future development of the IT XR Project Redstone... More Info
Infinity Turbine ROT Radial Outflow Turbine 24 Design and Worldwide Rights: NFT for sale... NFT for the ROT 24 energy turbine. Be part of the future with this NFT. This design can be bought and sold but only one design NFT exists. You may manufacture the unit, or get the revenues from its sale from Infinity Turbine. Royalties go to the developer (Infinity) to keep enhancing design and applications... More Info
Infinity Supercritical CO2 10 Liter Extractor Design and Worldwide Rights: The Infinity Supercritical 10L CO2 extractor is for botanical oil extraction, which is rich in terpenes and can produce shelf ready full spectrum oil. With over 5 years of development, this industry leader mature extractor machine has been sold since 2015 and is part of many profitable businesses. The process can also be used for electrowinning, e-waste recycling, and lithium battery recycling, gold mining electronic wastes, precious metals. CO2 can also be used in a reverse fuel cell with nafion to make a gas-to-liquids fuel, such as methanol, ethanol and butanol or ethylene. Supercritical CO2 has also been used for treating nafion to make it more effective catalyst. This NFT is for the purchase of worldwide rights which includes the design. More Info
NFT (Non Fungible Token): Buy our tech, design, development or system NFT and become part of our tech NFT network... More Info
Infinity Turbine Products: Special for this month, any plans are $10,000 for complete Cad/Cam blueprints. License is for one build. Try before you buy a production license. May pay by Bitcoin or other Crypto. Products Page... More Info
| CONTACT TEL: 608-238-6001 Email: greg@infinityturbine.com | RSS | AMP |