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Test Of A Supersonic Compressor Cascade
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Book Synopsis Test of a Supersonic Compressor Cascade (Vol. 1) by : R. L. Holtman
Download or read book Test of a Supersonic Compressor Cascade (Vol. 1) written by R. L. Holtman and published by . This book was released on 1972 with total page 392 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes in detail the experimental investigation of a stationary, linear, supersonic compressor blade cascade. The cascade incorporated contoured sidewalls to control the change in stream-tube area in the quasi-axial direction. The blades had a constant spanwise geometry. The selected blade element was from a recent compressor configuration resulting from the Aerospace Research Laboratories supersonic axial compressor research program. The investigation covered a range of inlet relative Mach numbers of 1.40 - 1.50 and a range of static pressure ratios of approximately 1.5 - 2.1. Volume I describes the cascade design, instrumentation, data reduction techniques, test results, and correlation of results with design characteristics.
Book Synopsis Test of a Supersonic Compressor Cascade by : Robert L. Holtman
Download or read book Test of a Supersonic Compressor Cascade written by Robert L. Holtman and published by . This book was released on 1972 with total page 411 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes in detail the experimental investigation of a stationary, linear, supersonic compressor blade cascade. The cascade incorporated contoured sidewalls to control the change in stream-tube area in the quasi-axial direction. The blades had a constant spanwise geometry. The selected blade element was from a recent compressor configuration resulting from the Aerospace Research Laboratories supersonic axial compressor research program. The investigation covered a range of inlet relative Mach numbers of 1.40 - 1.50 and a range of static pressure ratios of approximately 1.5 - 2.1. Volume I describes the cascade design, instrumentation, data reduction techniques, test results, and correlation of results with design characteristics. (Author).
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722219574 Total Pages :32 pages Book Rating :4.2/5 (195 download)
Book Synopsis Experimental Investigation of the Performance of a Supersonic Compressor Cascade by : National Aeronautics and Space Administration (NASA)
Download or read book Experimental Investigation of the Performance of a Supersonic Compressor Cascade written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented from an experimental investigation of a linear, supersonic, compressor cascade tested in the supersonic cascade wind tunnel facility at the DFVLR in Cologne, Federal Republic of Germany. The cascade design was derived from the near-tip section of a high-through-flow axial flow compressor rotor with a design relative inlet Mach number of 1.61. Test data were obtained over a range of inlet Mach numbers from 1.23 to 1.71, and a range of static pressure ratios and axial-velocity-density ratios (AVDR) at the design inlet condition. Flow velocity measurements showing the wave pattern in the cascade entrance region were obtained using a laser transit anemometer. From these measurements, some unique-incidence conditions were determined, thus relating the supersonic inlet Mach number to the inlet flow direction. The influence of static pressure ratio and AVDR on the blade passage flow and the blade-element performance is described, and an empirical correlation is used to show the influence of these two (independent) parameters on the exit flow angle and total-pressure loss for the design inlet condition. Tweedt, D. L. and Schreiber, H. A. and Starken, H. Glenn Research Center RTOP 505-62-61...
Book Synopsis Test of a Supersonic Compressor Cascade (Vol. 2) by : R. L. Holtman
Download or read book Test of a Supersonic Compressor Cascade (Vol. 2) written by R. L. Holtman and published by . This book was released on 1972 with total page 309 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes in detail the experimental investigation of a stationary, linear, supersonic compressor blade cascade. The cascade incorporated contoured sidewalls to control the change in stream-tube area in the quasi-axial direction. The blades had a constant spanwise geometry. The selected blade element was from a recent compressor configuration resulting from the Aerospace Research Laboratories supersonic axial compressor research program. The investigation covered a range of inlet relative Mach numbers of 1.40 - 1.50 and a range of static pressure ratios of approximately 1.5 - 2.1. Volume I describes the cascade design, instrumentation, data reduction techniques, test results, and correlation of results with design characteristics. Volume 2 describes additional work with vortex generators mounted on the blades and compares these results with the plain blade results.
Book Synopsis Test of a Supersonic Compressor Cascade with Splitter Vanes by : George R. Frost
Download or read book Test of a Supersonic Compressor Cascade with Splitter Vanes written by George R. Frost and published by . This book was released on 1973 with total page 471 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes experimental research conducted with a linear, stationary, supersonic compressor cascade with blades of constant spanwise geometry and contoured sidewalls. The cascade incorporated splitter vanes midway between blades in the latter half of each blade passage. A prior investigation with this cascade was conducted without splitter vanes and was reported previously. The principal objective of that program was to obtain cascade-type data for a selected blade element from a compressor configuration resulting from the Aerospace Research Laboratories in-house program of research on supersonic axial compressors. Splitter vanes, designed in a manner similar to those used in the rotor, were incorporated in the supersonic compressor cascade. Additional work was conducted and the primary objective was to obtain cascade-type data for the particular compressor blade-splitter vane combination. (Modified author abstract).
Book Synopsis Test of a Supersonic Compressor Cascade with Splitter Vanes and Vortex Generators on Blades by : Robert L. Holtman
Download or read book Test of a Supersonic Compressor Cascade with Splitter Vanes and Vortex Generators on Blades written by Robert L. Holtman and published by . This book was released on 1973 with total page 431 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes experimental research conducted with a linear, stationary, supersonic compressor cascade with blades of constant spanwise geometry and contoured sidewalls. The cascade incorporated splitter vanes midway between blades in the latter half of each blade passage. The influence of splitter vane orientation was investigated. The investigation covered a range of Mach numbers from 1.40 to 1.50 and a range of static pressure ratios. This report describes work accomplished with vortex generators mounted on the suction surfaces of the blades. (Modified author abstract).
Book Synopsis Test of a Supersonic Compressor Cascade by : Robert L. Holtman
Download or read book Test of a Supersonic Compressor Cascade written by Robert L. Holtman and published by . This book was released on 1972 with total page 323 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes in detail the experimental investigation of a stationary, linear, supersonic compressor blade cascade. The cascade incorporated contoured sidewalls to control the change in stream-tube area in the quasi-axial direction. The blades had a constant spanwise geometry. The selected blade element was from a recent compressor configuration resulting from the Aerospace Research Laboratories supersonic axial compressor research program. The investigation covered a range of inlet relative Mach numbers of 1.40 - 1.50 and a range of static pressure ratios of approximately 1.5 - 2.1. Volume I describes the cascade design, instrumentation, data reduction techniques, test results, and correlation of results with design characteristics. Volume 2 describes additional work with vortex generators mounted on the blades and compares these results with the plain blade results. (Author).
Book Synopsis Supersonic Axial Velocity Compressor Study. Volume Iv. Two-dimensional Cascade Test Results by : F. W. Lipfert
Download or read book Supersonic Axial Velocity Compressor Study. Volume Iv. Two-dimensional Cascade Test Results written by F. W. Lipfert and published by . This book was released on 1967 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: This volume presents a description of the cascade tests conducted to establish feasibility of the supersonic axial velocity compressor concept. Two series of tests were conducted at a free stream Mach number of 2.7 using a cascade of four two-dimensional impulse blades, having about 60 deg. turning. The blade profile was modified slightly for the second test series to alleviate suction surface boundary layer separation. The angle of attack of the cascade was varied roughly plus or minus 15 deg. Measurements consisted of pressure distributions along the blade surfaces and the total pressure recovery at the passage exit. The maximum mass-weighted recovery was 80%. (Author).
Book Synopsis Experimental Investigation of a Transonic Compressor Cascade and Test Results for Four Blade Sections by : James C. Emery
Download or read book Experimental Investigation of a Transonic Compressor Cascade and Test Results for Four Blade Sections written by James C. Emery and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Theoretical and Experimental Investigation of the Supersonic Compressor Cascade by : Aly Mohamed El Zahaby
Download or read book The Theoretical and Experimental Investigation of the Supersonic Compressor Cascade written by Aly Mohamed El Zahaby and published by . This book was released on 1977 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Cascade Aerodynamics by : J. P. Gostelow
Download or read book Cascade Aerodynamics written by J. P. Gostelow and published by Pergamon. This book was released on 1984 with total page 296 pages. Available in PDF, EPUB and Kindle. Book excerpt: Good,No Highlights,No Markup,all pages are intact, Slight Shelfwear,may have the corners slightly dented, may have slight color changes/slightly damaged spine.
Book Synopsis Development of the Supersonic Compressor Test Facilities at the Arnold Ngineering Development Center by : C. T. Carman
Download or read book Development of the Supersonic Compressor Test Facilities at the Arnold Ngineering Development Center written by C. T. Carman and published by . This book was released on 1965 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt: The design characteristics, operational capabilities, and instrumentation systems of the supersonic compressor test facilities at AEDC are described and the results of shakedown tests are presented. These facilities consist of (1) a high-speed rotating machine to test 22-in.-diam, single-stage, axial-flow compressor rotors from 5,000 to 17,000 rpm at rotor tip speeds up to 1630 ft/sec and (2) a continuous-flow cascade rig with a 1- by 1.3-in. test section to test the effects of various blade parameters such as area ratio and angle of attack. The primary purpose of these facilities is for further development and evaluation of the concept of blunt-trailing edge, supersonic compressor blades. (Author).
Book Synopsis Aerodynamic Research Into High Cambered MCA-type Supersonic Compressor Cascade by : Karel Čelikovský
Download or read book Aerodynamic Research Into High Cambered MCA-type Supersonic Compressor Cascade written by Karel Čelikovský and published by . This book was released on 1986 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Supersonic Through-flow Compressor Concept. Volume Ii. Analytical and Experimental Investigations of Supersonic Cascades and Diffusers by : Stuart E. Gadbois
Download or read book Investigation of the Supersonic Through-flow Compressor Concept. Volume Ii. Analytical and Experimental Investigations of Supersonic Cascades and Diffusers written by Stuart E. Gadbois and published by . This book was released on 1967 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical and experimental investigation of supersonic cascades and supersonic diffusers having entrance conditions representative of the flow discharging from a supersonic through-flow compressor was conducted. The performance of these cascades was predicted over a range of operating conditions using a one-dimensional analysis which included shock and friction losses. Cascade configurations designed to provide up to 65 deg of total turning were tested at supersonic approach Mach numbers over a range of incidence angles. The experimental results were in general agreement with the theoretical performance predicted by the one-dimensional analysis. The test results indicate that rotor efficiencies on the order of 80 percent can be obtained with a supersonic through-flow compressor. A theoretical analysis of the supersonic diffuser was conducted to evaluate the effects of diffuser geometry, bleed flow ratio, and entrance Mach number on the diffuser pressure recovery. Tests of an annular diffuser model ingesting supersonic flows with various amounts of wakes, swirl and boundary layer were conducted. The experimental results showed these flows can be diffused with a process efficiency greater than 90 percent. (Author).
Book Synopsis Supersonic Cascade Studies. Part 1. Passage Studies by :
Download or read book Supersonic Cascade Studies. Part 1. Passage Studies written by and published by . This book was released on 1961 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study was made of supersonic flow through various convergent and convergent-divergant passage configurations. The details of the flows were examined by means of total and static pressure surveys and Schlieren photographs and the effects of some changes in passage geometry on the characteristics of the passages were observed. Based on the tests, some design criteria were determined for supersonic passages capable of operating at high static pressure ratios. It was concluded that long and narrow convergent- divergent passages are capable of producing a significant pressure rise without extensive separation in the divergent region. However, the values of obtainable pressure rise appears to be substantially lower than anticipated by early designers of supersonic compressor cascades.
Book Synopsis Nonuniform Flow Field Generation for Supersonic Compressor Stator Development: Design and Preliminary Results by :
Download or read book Nonuniform Flow Field Generation for Supersonic Compressor Stator Development: Design and Preliminary Results written by and published by . This book was released on 1972 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
