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Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade

Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade PDF Author: P. W. Geil
Publisher:
ISBN:
Category :
Languages : en
Pages : 20

Book Description
Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.

Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade

Three-Dimensional Flow Field Measurements in a Transonic Turbine Cascade PDF Author: P. W. Geil
Publisher:
ISBN:
Category :
Languages : en
Pages : 20

Book Description
Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.

Three-Dimensional Flow Field Measurements In A Transonic Turbine Cascade... NASA-TM-107388... Apr. 7, 1997

Three-Dimensional Flow Field Measurements In A Transonic Turbine Cascade... NASA-TM-107388... Apr. 7, 1997 PDF Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :

Book Description


Three-dimensional Flow Field Measurements in a Transonic Turbine Cascade

Three-dimensional Flow Field Measurements in a Transonic Turbine Cascade PDF Author: P. W. Giel
Publisher:
ISBN:
Category :
Languages : en
Pages : 14

Book Description
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.

Endwall Heat Transfer Measurements in a Transonic Turbine Cascade

Endwall Heat Transfer Measurements in a Transonic Turbine Cascade PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 20

Book Description
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.

Calculation of Two and Three-dimensional Flow in a Transonic Turbine Cascade with Particular Regard to the Losses

Calculation of Two and Three-dimensional Flow in a Transonic Turbine Cascade with Particular Regard to the Losses PDF Author: H. Zimmermann
Publisher:
ISBN:
Category :
Languages : en
Pages :

Book Description


Aerodynamic Measurements of a Variable-Speed Power-Turbine Blade Section in a Transonic Turbine Cascade

Aerodynamic Measurements of a Variable-Speed Power-Turbine Blade Section in a Transonic Turbine Cascade PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781719398541
Category :
Languages : en
Pages : 44

Book Description
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

Experimental and Computational Study of Transonic Three-dimensional Flow in a Turbine Cascade

Experimental and Computational Study of Transonic Three-dimensional Flow in a Turbine Cascade PDF Author: J. -J. Camus
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

Book Description


Computational Studies of Three-dimensional Transonic Shear Flow

Computational Studies of Three-dimensional Transonic Shear Flow PDF Author: David Anthony Oliver
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 44

Book Description


Endwall Heat Transfer Measurements in a Transonic Turbine Cascade

Endwall Heat Transfer Measurements in a Transonic Turbine Cascade PDF Author: P. W. Giel
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 15

Book Description
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.

Three Dimensional Viscous Flow Field in an Axial Flow Turbine Nozzle Passage

Three Dimensional Viscous Flow Field in an Axial Flow Turbine Nozzle Passage PDF Author: D. Ristic
Publisher:
ISBN:
Category : Turbines
Languages : en
Pages : 206

Book Description