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Redesign Of The Low Speed Three Stage Axial Flow Compressor Test Facility
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Book Synopsis Redesign of the Low Speed Three Stage Axial Flow Compressor Test Facility by : Michael Hans Vavra
Download or read book Redesign of the Low Speed Three Stage Axial Flow Compressor Test Facility written by Michael Hans Vavra and published by . This book was released on 1973 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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).
Book Synopsis Design and Tests of a Six-stage Axial-flow Compressor Having a Tip Speed of 550 Feet Per Second and a Flat Operating Characteristic at Constant Speed by : Willard R. Westphal
Download or read book Design and Tests of a Six-stage Axial-flow Compressor Having a Tip Speed of 550 Feet Per Second and a Flat Operating Characteristic at Constant Speed written by Willard R. Westphal and published by . This book was released on 1958 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: A six-stage axial-flow compressor with a tip speed of 550 feet per second and a flat operating characteristics at constant speed has been designed and tested. It was designed for a constant power input per pound of flow in expectation that this would result in a wider mass-flow operating range at a given stagnation-presssure ratio. The design specific weight flow was 21.3 pounds per second per square foot of frontal area at atmospheric discharge with a stagnation-pressure ratio of 3.25 and an inlet hub-tip radius ratio of 0.7. Several configurations consisting of various blade setting angles and solidities were tested. Tests showed that the design flow, pressure ratio, and flat operating characteristic were obtained over a range of 10 percent of design flow at a peak efficiency of 82 percent for design conditions. The compressor had a possible immediate application for air removal from a large slotted-throat transonic wind tunnel, but the design theory could apply to any low-speed industrial compressor or second spool of a turbojet engine.
Book Synopsis The Design and Installation of a Three-stage, Medium Speed, Axial-flow Research Compressor Test Rig by : Kevin Eugene Thompson
Download or read book The Design and Installation of a Three-stage, Medium Speed, Axial-flow Research Compressor Test Rig written by Kevin Eugene Thompson and published by . This book was released on 1987 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Announcements by :
Download or read book Government Reports Announcements written by and published by . This book was released on 1974 with total page 1000 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Stalled and Stall-free Performance of Axial-flow Compressor Stage with Three Inlet-guide-vane and Stator-blade Settings by : Donald C. Urasek
Download or read book Stalled and Stall-free Performance of Axial-flow Compressor Stage with Three Inlet-guide-vane and Stator-blade Settings written by Donald C. Urasek and published by . This book was released on 1977 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Design of Axial-flow Compressors by : Lewis Research Center
Download or read book Aerodynamic Design of Axial-flow Compressors written by Lewis Research Center and published by . This book was released on 1965 with total page 542 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1984 with total page 784 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor by : Frans A. E. Breugelmans
Download or read book The Low Hub-Tip Ratio Supersonic Axial-Flow Compressor written by Frans A. E. Breugelmans and published by . This book was released on 1972 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes the test results of a supersonic axial-flow compressor stage with a tip Mach number of 2.0. Volume 2 discusses a method to eliminate the inlet problem. Volume 3 describes the overall and detailed performance of the original model FB III with an interblade row bleed system. The bleed area represents 10% of the inlet area and a minimum bleed flow of 7% of the total inlet flow could be achieved. The stage performance data are presented for the 60% to 107% N over the square root of theta of the nominal speed. (Author).
Book Synopsis Detailed Flow Measurements in Casing Boundary Layer of 429-meter-per-second-tip-speed Two-stage Fan by : William T. Gorrell
Download or read book Detailed Flow Measurements in Casing Boundary Layer of 429-meter-per-second-tip-speed Two-stage Fan written by William T. Gorrell and published by . This book was released on 1984 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Detailed flow measurements made in the casing boundary layer of a two-stage transonic fan are summarized. These measurements were taken at stations upstream of the fan, between all blade rows, and downstream of the last blade row. At the design tip speed (429 m/sec) the fan achieved a peak efficiency of 0.846 at a pressure ratio of 2.471. The boundary layer data were obtained at three weight flows at the design speed: one near choke flow, one near peak efficiency, and one near stall. The data presented show steep axial velocity profiles at the stator exits were not as steep as those at the rotor exits. The data also show overturning of the flow at the tip at the stator exits. The effect of mixing is shown by the redistribution of the first-stage rotor-exit total temperature profile as is passes through the following stator.
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1984-07 with total page 1034 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Technical Paper by : United States. National Aeronautics and Space Administration
Download or read book NASA Technical Paper written by United States. National Aeronautics and Space Administration and published by . This book was released on 1984 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Modeling of a Three Stage Axial-flow Compressor with Flow Corrections by : Brahmaji Rao Kadium
Download or read book Modeling of a Three Stage Axial-flow Compressor with Flow Corrections written by Brahmaji Rao Kadium and published by . This book was released on 2006 with total page 358 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Gas Turbines for Electric Power Generation by : S. Can Gülen
Download or read book Gas Turbines for Electric Power Generation written by S. Can Gülen and published by Cambridge University Press. This book was released on 2019-02-14 with total page 735 pages. Available in PDF, EPUB and Kindle. Book excerpt: Everything you wanted to know about industrial gas turbines for electric power generation in one source with hard-to-find, hands-on technical information.
Book Synopsis Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased 0.020 Inch (Configuration 3). by : C. Herbert Law
Download or read book Investigation of a High-Through-Flow, Single-Stage Axial-Flow Compressor with Tip Clearance Increased 0.020 Inch (Configuration 3). written by C. Herbert Law and published by . This book was released on 1981 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: Complete experimental results are presented from tests of an axial compressor. The design objectives were for a flow per unit frontal area of 39.7 lb/sec/sq ft, a total pressure ratio of 1.912 and a tip speed of 1500 ft/sec. These experimental results were achieved with one of a series of minor parametric modifications to the baseline compressor stage. No conclusions concerning the effects of these modifications will be drawn until the complete series of tests has been reported. (Author).
Book Synopsis Design of a Single Stage Axial Flow Compressor for Test Purposes by : Rocco Anthony Petrone
Download or read book Design of a Single Stage Axial Flow Compressor for Test Purposes written by Rocco Anthony Petrone and published by . This book was released on 1952 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by :
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by and published by . This book was released on 1957 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
