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Three Dimensional Flow Field Measurements In A Transonic Turbine Cascade
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Book Synopsis Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade by : P. W. Geil
Download or read book Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade written by P. W. Geil and published by . This book was released on 1996 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.
Book Synopsis Three-Dimensional Flow Field Measurements In A Transonic Turbine Cascade... NASA-TM-107388... Apr. 7, 1997 by : United States. National Aeronautics and Space Administration
Download or read book Three-Dimensional Flow Field Measurements In A Transonic Turbine Cascade... NASA-TM-107388... Apr. 7, 1997 written by United States. National Aeronautics and Space Administration and published by . This book was released on 1998* with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-dimensional Flow Field Measurements in a Transonic Turbine Cascade by : P. W. Giel
Download or read book Three-dimensional Flow Field Measurements in a Transonic Turbine Cascade written by P. W. Giel and published by . This book was released on 1996 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three dimensional flow field measurements are presented for a large scale transonic turbine blade cascade. Flow field total pressures and pitch and yaw flow angles were measured at an inlet Reynolds number of 1.0 x 10(exp 6) and at an isentropic exit Mach number of 1.3 in a low turbulence environment. Flow field data was obtained on five pitchwise/spanwise measurement planes, two upstream and three downstream of the cascade, each covering three blade pitches. Three hole boundary layer probes and five hole pitch/yaw probes were used to obtain data at over 1200 locations in each of the measurement planes. Blade and endwall static pressures were also measured at an inlet Reynolds number of 0.5 x 10(exp 6) and at an isentropic exit Mach number of 1.0. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136 deg of turning and an axial chord of 12.7 cm. The flow field in the cascade is highly three dimensional as a result of thick boundary layers at the test section inlet and because of the high degree of flow turning. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781719398541 Total Pages :44 pages Book Rating :4.3/5 (985 download)
Book Synopsis Aerodynamic Measurements of a Variable-Speed Power-Turbine Blade Section in a Transonic Turbine Cascade by : National Aeronautics and Space Administration (NASA)
Download or read book Aerodynamic Measurements of a Variable-Speed Power-Turbine Blade Section in a Transonic Turbine Cascade written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this thesis is to document the impact of incidence angle and Reynolds number variations on the three-dimensional flow field and midspan loss and turning of a two-dimensional section of a variable-speed power-turbine (VSPT) rotor blade. Aerodynamic measurements were obtained in a transonic linear cascade at NASA Glenn Research Center in Cleveland, Ohio. Steady-state data were obtained for 10 incidence angles ranging from +15.8deg to -51.0deg. At each angle, data were acquired at five flow conditions with the exit Reynolds number (based on axial chord) varying over an order-of-magnitude from 2.12×105 to 2.12×106. Data were obtained at the design exit Mach number of 0.72 and at a reduced exit Mach number of 0.35 as required to achieve the lowest Reynolds number. Midspan tota lpressure and exit flow angle data were acquired using a five-hole pitch/yaw probe surveyed on a plane located 7.0 percent axial-chord downstream of the blade trailing edge plane. The survey spanned three blade passages. Additionally, three-dimensional half-span flow fields were examined with additional probe survey data acquired at 26 span locations for two key incidence angles of +5.8deg and -36.7deg. Survey data near the endwall were acquired with a three-hole boundary-layer probe. The data were integrated to determine average exit total-pressure and flow angle as functions of incidence and flow conditions. The data set also includes blade static pressures measured on four spanwise planes and endwall static pressures. Flegel, Ashlie B. Glenn Research Center REYNOLDS NUMBER; TURBINE BLADES; ROTOR BLADES (TURBOMACHINERY); TILT ROTOR AIRCRAFT; MACH NUMBER; THREE DIMENSIONAL FLOW; LOSSES; SURVEYS; COMPUTATIONAL FLUID DYNAMICS; PITCH (INCLINATION); EXPERIMENT DESIGN; TEST FACILITIES
Book Synopsis Endwall Heat Transfer Measurements in a Transonic Turbine Cascade by :
Download or read book Endwall Heat Transfer Measurements in a Transonic Turbine Cascade written by and published by . This book was released on 1996 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 x 10(exp 6), for isentropic exit Mach numbers of 1.0 and 1.3, and for freestream turbulence intensities of 0.25% and 7.0%. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136 deg of turning and an axial chord of 12.7 cm. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet. Endwall heat transfer data were obtained using a steady-state liquid crystal technique.
Book Synopsis Calculation of Two and Three-dimensional Flow in a Transonic Turbine Cascade with Particular Regard to the Losses by : H. Zimmermann
Download or read book Calculation of Two and Three-dimensional Flow in a Transonic Turbine Cascade with Particular Regard to the Losses written by H. Zimmermann and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Endwall Heat Transfer Measurements in a Transonic Turbine Cascade by : P. W. Giel
Download or read book Endwall Heat Transfer Measurements in a Transonic Turbine Cascade written by P. W. Giel and published by . This book was released on 1996 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 x 10(exp 6), for isentropic exit Mach numbers of 1.0 and 1.3, and for freestream turbulence intensities of 0.25% and 7.0%. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136 deg of turning and an axial chord of 12.7 cm. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet. Endwall heat transfer data were obtained using a steady-state liquid crystal technique.
Book Synopsis Experimental and Computational Study of Transonic Three-dimensional Flow in a Turbine Cascade by : J. -J. Camus
Download or read book Experimental and Computational Study of Transonic Three-dimensional Flow in a Turbine Cascade written by J. -J. Camus and published by . This book was released on 1983 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Computational Investigation of Flow Through an Annular Turbine Cascade by :
Download or read book Experimental and Computational Investigation of Flow Through an Annular Turbine Cascade written by and published by . This book was released on 1995 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this research was to compare numerical predictions with experimental results and to devise an accurate laser anemometry technique to measure in the endwall region of a confined annulus. Flowfield characteristics were computed using a three-dimensional flow solver with the numerical plane coincident with the experimental measurement location. An annular turbine cascade, designed for laser-Doppler velocimetry, was modified to obtain blade passage midspan surface pressure measurements. A range of predicted subsonic and transonic midspan surface pressures were compared favorably with experimental measurements. Two-dimensional Mach number, flow angle, and turbulence intensity measurements were obtained with a fiber-optics laser-Doppler velocimeter. These measurements were performed through a 1.0922 millimeter opening in the endwall at depths ranging from 0.01 mm to 3.34 mm and the results were compared with numerical predictions. (AN).
Book Synopsis Experimental and Computational Investigation of Flow Through an Annular Turbine Cascade by : William Howard Donovan
Download or read book Experimental and Computational Investigation of Flow Through an Annular Turbine Cascade written by William Howard Donovan and published by . This book was released on 1995 with total page 81 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of this research was to compare numerical predictions with experimental results and to devise an accurate laser anemometry technique to measure in the endwall region of a confined annulus. Flowfield characteristics were computed using a three-dimensional flow solver with the numerical plane coincident with the experimental measurement location. An annular turbine cascade, designed for laser-Doppler velocimetry, was modified to obtain blade passage midspan surface pressure measurements. A range of predicted subsonic and transonic midspan surface pressures were compared favorably with experimental measurements. Two-dimensional Mach number, flow angle, and turbulence intensity measurements were obtained with a fiber-optics laser- Doppler velocimeter. These measurements were performed through a 1.0922 millimeter opening in the endwall at depths ranging from 0.01 mm to 3.34 mm and the results were compared with numerical predictions. (AN).
Book Synopsis Aerodynamic Measurements of a Variable-speed Power-turbine Blade Section in a Transonic Turbine Cascade by : Ashlie B. Flegel
Download or read book Aerodynamic Measurements of a Variable-speed Power-turbine Blade Section in a Transonic Turbine Cascade written by Ashlie B. Flegel and published by . This book was released on 2013 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The purpose of this thesis is to document the impact of incidence angle and Reynolds number variations on the 3-D flow field and midspan loss and turning of a 2-D section of a variable-speed power-turbine (VSPT) rotor blade. Aerodynamic measurements were obtained in a transonic linear cascade at NASA Glenn Research Center in Cleveland, OH. Steady-state data were obtained for ten incidence angles ranging from +15.8° to -51.0°. At each angle, data were acquired at five flow conditions with the exit Reynolds number (based on axial chord) varying over an order-of-magnitude from 2.12 × 105 to 2.12 × 106. Data were obtained at the design exit Mach number of 0.72 and at a reduced exit Mach number of 0.35 as required to achieve the lowest Reynolds number. Midspan total-pressure and exit flow angle data were acquired using a five-hole pitch/yaw probe surveyed on a plane located 7.0 percent axial-chord downstream of the blade trailing edge plane. The survey spanned three blade passages. Additionally, three-dimensional half-span flow fields were examined with additional probe survey data acquired at 26 span locations for two key incidence angles of +5.8° and -36.7°. Survey data near the endwall were acquired with a three-hole boundary-layer probe. The data were integrated to determine average exit total-pressure and flow angle as functions of incidence and flow conditions. The data set also includes blade static pressures measured on four spanwise planes and endwall static pressures.
Book Synopsis Measurement and Prediction of the Flow Through an Annular Turbine Cascade by : Gregory David Thomas
Download or read book Measurement and Prediction of the Flow Through an Annular Turbine Cascade written by Gregory David Thomas and published by . This book was released on 1993 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An annular turbine cascade was designed and manufactured for laser Doppler velocimetry and probe measurements in a small-scale rig. The purpose of the experiment was to determine the limitations of these measurements in a confined annulus, and to compare the experimental results with numerical predictions. Downstream probe surveys were conducted at a Reynolds number of 500000. Total pressure and temperature measurements were taken upstream of the test section, and hub static pressure was measured downstream of the cascade. A two-dimensional laser anemometer was used to obtain preliminary velocity field measurements for code validation. The two main problem areas identified were the type of seeding material used and the configuration of the optical access window. Flowfield characteristics were predicted using a three-dimensional viscous code, which were then compared to experimental measurements. The comparison showed that the numerical simulator predicted well the general features of the flow field that were measured in the experiment. Recommendations are made which would improve the mapping of the velocity field for a more complete code validation.
Book Synopsis The Three Dimensional Flow Field at the Exit of an Axial-Flow Turbine Rotor by : B. Lakshminarayana
Download or read book The Three Dimensional Flow Field at the Exit of an Axial-Flow Turbine Rotor written by B. Lakshminarayana and published by . This book was released on 1998 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three Dimensional Viscous Flow Field in an Axial Flow Turbine Nozzle Passage by : D. Ristic
Download or read book Three Dimensional Viscous Flow Field in an Axial Flow Turbine Nozzle Passage written by D. Ristic and published by . This book was released on 1997 with total page 206 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 1975 with total page 978 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book STAR written by and published by . This book was released on 1973 with total page 888 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-dimensional Navier-Stokes Analysis and Redesign of an Imbedded Bellmouth Nozzle in a Turbine Cascade Inlet Section by :
Download or read book Three-dimensional Navier-Stokes Analysis and Redesign of an Imbedded Bellmouth Nozzle in a Turbine Cascade Inlet Section written by and published by . This book was released on 1996 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
