Download or read book Investigation of a 1500 Ft sec Transonic High through Flow Single Stage Axial Flow Compressor with Low Hub Tip Ratio written by and published by . This book was released on 1976 with total page 375 pages. Available in PDF, EPUB and Kindle. Book excerpt: Complete experimental results are presented from tests of an axial compressor stage designed for a flow per frontal area of 39.7 lb/sec/ft square, a total pressure ratio of 1.912 and a tip speed of 1500 ft/sec. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. Since the most serious aerodynamic design problems of the over-all compressor were observed to be associated with the first stage, this stage was chosen as the subject of a research program. Results of the tests indicated that, at design speed, design flow was achieved with a rotor isentropic efficiency of 90.4 percent, a stage isentropic efficiency of 88.2 percent and a stage total pressure ratio of 2.065.
Download or read book Design of a 1500 Ft Sec Transonic High through Flow Single Stage Axial Flow Compressor with Low Hub Tip Ratio written by and published by . This book was released on 1976 with total page 298 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report describes the aerodynamic design of a transonic axial- flow compressor inlet stage designed for high flow rate per unit frontal area and relatively high aerodynamic loading. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. The design goals chosen included a tip speed of 1500 ft/sec, a flow rate of 39.7 lb/sec per square foot of frontal area, a stage total pressure ratio of 1.91 and a stage isentropic efficiency of 0.83. The techniques used in the preliminary and detail designs are described. The complete aerodynamic flow field pertaining to the design point is defined on twenty-one stream surfaces, and radial and meridional distributions of significant parameters are presented. Finally, the detailed flowpath geometry is defined and airfoil coordinates are included for both stream surfaces and cartesian manufacturing sections.
Download or read book ASME Technical Papers written by and published by . This book was released on 1999 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Symposium Papers written by and published by . This book was released on 1987 with total page 798 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Paper written by and published by . This book was released on 2000 with total page 498 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Rotating Stall Investigation of the 0 72 Hub tip Ratio Single stage Compressor written by Robert W. Graham and published by . This book was released on 1954 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Journal of Turbomachinery written by and published by . This book was released on with total page 852 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Notices of Changes in Classification Distribution and Availability written by and published by . This book was released on 1983 with total page 350 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of A High through Flow Single Stage Axial Flow Compressor with Tip Clearance Increased 0 020 Inch and Casing Vortex Generator Configuration B Configuration 3B written by C. Herbert Law and published by . This book was released on 1981 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Complete experimental results are presented from tests of an axial compressor with casing vortex generators. 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).
Download or read book Investigation of a High Through Flow Single Stage Axial Flow Compressor with Tip Clearance Increased O 010 Inch and Casing Vortex Generator Configuration C Configuration 2C written by C. Herbert Law and published by . This book was released on 1981 with total page 103 pages. Available in PDF, EPUB and Kindle. Book excerpt: Complete experimental results are presented from tests of an axial compressor with casing vortex generators. 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).
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).
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.
Download or read book Investigation of a High Through Flow Single Stage Axial Flow Compressor with Tip Clearance Increased 0 010 Inch and Casing Vortex Generator Configuration A Configuration 2A written by C. Herbert Law and published by . This book was released on 1981 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: Complete experimental results are presented from tests of an axial compressor with casing vortex generators. 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).
Download or read book AIAA ASME SAE ASEE 24th Joint Propulsion Conference written by and published by . This book was released on 1988 with total page 400 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1980 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of a High Through Flow Single Stage Axial Flow Compressor with Tip Clearance Increased 0 020 Inch and Rotor Tip Vortex Generators Configuration 3 1 written by Arthur J. Wennerstrom and published by . This book was released on 1982 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt: Complete experimental results are presented from tests of an axial compressor with rotor-mounted vortex generators. The design objectives were for a flow per unit frontal area of 39.7 1b/sec sq. ft., a total pressure ratio of 1.912 and a tip spread 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).
Download or read book Investigation of a High Through Flow Single Stage Axial Flow Compressor with Tip Clearance Increased 0 020 Inch and Casing Vortex Generator Configuration C Configuration 3C written by C. Herbert Law and published by . This book was released on 1981 with total page 101 pages. Available in PDF, EPUB and Kindle. Book excerpt: Complete experimental results are presented from tests of an axial compressor with casing vortex generators. The design objectives were for a flow per unit frontal area of 39.7 lb/sec/ft2, 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).
