Volume 112 Issue 2 | J. Turbomach. | ASME Digital Collection

Design and Testing of the FT8 Gas Turbine Low-Pressure Compressor

R. J. Monhardt, J. H. Richardson, J. M. Boettcher

J. Turbomach. April 1990, 112(2): 159–164. doi: https://doi.org/10.1115/1.2927628

Abstract

View articletitled, Design and Testing of the FT8 Gas Turbine Low-Pressure Compressor

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Topics: Compressors , Design , Gas turbines , Pressure , Testing , Aircraft engines , Durability , Generators

A Variable-Geometry Power Turbine for Marine Gas Turbines

K. W. Karstensen, J. O. Wiggins

J. Turbomach. April 1990, 112(2): 165–174. doi: https://doi.org/10.1115/1.2927629

Abstract

View articletitled, A Variable-Geometry Power Turbine for Marine Gas Turbines

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Topics: Geometry , Marine gas turbines , Turbines , Engines , Nozzles , Gas turbines , Fuel consumption , Propulsion , Stress , Design

Surface Roughness Measurements on Gas Turbine Blades

R. P. Taylor

J. Turbomach. April 1990, 112(2): 175–180. doi: https://doi.org/10.1115/1.2927630

Abstract

View articletitled, Surface Roughness Measurements on Gas Turbine Blades

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Topics: Blades , Gas turbines , Surface roughness , Turbine blades , Boundary layers , Computation , Engines , Flow (Dynamics) , Heat transfer , Pressure

The Influence of Boundary Layer State on Vortex Shedding From Flat Plates and Turbine Cascades

C. H. Sieverding, H. Heinemann

J. Turbomach. April 1990, 112(2): 181–187. doi: https://doi.org/10.1115/1.2927631

Abstract

View articletitled, The Influence of Boundary Layer State on Vortex Shedding From Flat Plates and Turbine Cascades

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Topics: Boundary layers , Flat plates , Turbines , Vortex shedding , Blades , Turbine blades , Cascades (Fluid dynamics) , Geometry , Mach number , Reynolds number

A Theory for Wake-Induced Transition

R. E. Mayle, K. Dullenkopf

J. Turbomach. April 1990, 112(2): 188–195. doi: https://doi.org/10.1115/1.2927632

Abstract

View articletitled, A Theory for Wake-Induced Transition

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Topics: Airfoils , Boundary layers , Flat plates , Heat transfer , Turbulence , Wake turbulence , Wakes

Effects of Adverse Pressure Gradients on the Nature and Length of Boundary Layer Transition

G. J. Walker, J. P. Gostelow

J. Turbomach. April 1990, 112(2): 196–205. doi: https://doi.org/10.1115/1.2927633

Abstract

View articletitled, Effects of Adverse Pressure Gradients on the Nature and Length of Boundary Layer Transition

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Topics: Boundary layers , Pressure gradient , Waves , Flow (Dynamics) , Reynolds number , Separation (Technology) , Turbulence

Unsteady Transition in an Axial-Flow Turbine: Part 1—Measurements on the Turbine Rotor

J. S. Addison, H. P. Hodson

J. Turbomach. April 1990, 112(2): 206–214. doi: https://doi.org/10.1115/1.2927634

Abstract

View articletitled, Unsteady Transition in an Axial-Flow Turbine: Part 1—Measurements on the Turbine Rotor

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Topics: Axial flow , Rotors , Turbine components , Turbines , Boundary layers , Suction , Cascades (Fluid dynamics) , Cross section (Physics) , Gages , Stators

Unsteady Transition in an Axial-Flow Turbine: Part 2—Cascade Measurements and Modeling

J. S. Addison, H. P. Hodson

J. Turbomach. April 1990, 112(2): 215–221. doi: https://doi.org/10.1115/1.2927635

Abstract

View articletitled, Unsteady Transition in an Axial-Flow Turbine: Part 2—Cascade Measurements and Modeling

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Topics: Axial flow , Cascades (Fluid dynamics) , Modeling , Turbine components , Turbines , Rotors , Suction , Turbulence , Wakes

Compressor Blade Boundary Layers: Part 1—Test Facility and Measurements With No Incident Wakes

Y. Dong, N. A. Cumpsty

J. Turbomach. April 1990, 112(2): 222–230. doi: https://doi.org/10.1115/1.2927636

Abstract

View articletitled, Compressor Blade Boundary Layers: Part 1—Test Facility and Measurements With No Incident Wakes

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Topics: Blades , Boundary layers , Compressors , Test facilities , Wakes , Convection

Compressor Blade Boundary Layers: Part 2—Measurements With Incident Wakes

Y. Dong, N. A. Cumpsty

J. Turbomach. April 1990, 112(2): 231–240. doi: https://doi.org/10.1115/1.2927637

Abstract

View articletitled, Compressor Blade Boundary Layers: Part 2—Measurements With Incident Wakes

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Topics: Blades , Boundary layers , Compressors , Wakes , Momentum , Test facilities , Turbulence

The Measurement of Boundary Layers on a Compressor Blade in Cascade: Part 4—Flow Fields for Incidence Angles of −1.5 and −8.5 Degrees

W. C. Zierke, S. Deutsch

J. Turbomach. April 1990, 112(2): 241–255. doi: https://doi.org/10.1115/1.2927638

Abstract

View articletitled, The Measurement of Boundary Layers on a Compressor Blade in Cascade: Part 4—Flow Fields for Incidence Angles of −1.5 and −8.5 Degrees

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Topics: Blades , Boundary layers , Cascades (Fluid dynamics) , Compressors , Flow (Dynamics) , Bubbles , Pressure , Separation (Technology) , Chords (Trusses) , Turbulence

Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence

Y. Elazar, R. P. Shreeve

J. Turbomach. April 1990, 112(2): 256–265. doi: https://doi.org/10.1115/1.2927642

Abstract

View articletitled, Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence

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Topics: Cascades (Fluid dynamics) , Compressors , Diffusion (Physics) , Viscous flow , Boundary layers , Blades , Bubbles , Design , Flow (Dynamics) , Geometry

An Improved Incidence Losses Prediction Method for Turbine Airfoils

S. H. Moustapha, S. C. Kacker, B. Tremblay

J. Turbomach. April 1990, 112(2): 267–276. doi: https://doi.org/10.1115/1.2927647

Abstract

View articletitled, An Improved Incidence Losses Prediction Method for Turbine Airfoils

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Topics: Airfoils , Turbines , Design

The Trailing Edge Loss of Transonic Turbine Blades

J. D. Denton, L. Xu

J. Turbomach. April 1990, 112(2): 277–285. doi: https://doi.org/10.1115/1.2927648

Abstract

View articletitled, The Trailing Edge Loss of Transonic Turbine Blades

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Topics: Turbine blades , Pressure , Suction , Coolants , Flow (Dynamics) , Momentum , Blades , Boundary layers , Mach number , Shock (Mechanics)

An Experimental Assessment of the Influence of Downstream Conditions on the Performance of a Transonic Turbine Nozzle of High Turning

U. W. Schaub, R. G. Williamson, J.-P. Huot, S. H. Moustapha

J. Turbomach. April 1990, 112(2): 286–293. doi: https://doi.org/10.1115/1.2927651

Abstract

View articletitled, An Experimental Assessment of the Influence of Downstream Conditions on the Performance of a Transonic Turbine Nozzle of High Turning

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Topics: Nozzles , Turbines , Turning , Rotors , Flow (Dynamics) , Design , Mach number , Pressure , Probes , Turning angles

The Use of Circumferentially Varying Stagger Guide Vanes in an Axial Flow Pump or Compressor

J. H. Horlock

J. Turbomach. April 1990, 112(2): 294–297. doi: https://doi.org/10.1115/1.2927652

Abstract

View articletitled, The Use of Circumferentially Varying Stagger Guide Vanes in an Axial Flow Pump or Compressor

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Topics: Axial flow , Compressors , Guide vanes , Pumps , Pressure , Rotors , Actuators , Disks , Flow (Dynamics)

Inlet Distortion Generated Periodic Aerodynamic Rotor Response

S. R. Manwaring, S. Fleeter

J. Turbomach. April 1990, 112(2): 298–307. doi: https://doi.org/10.1115/1.2927654

Abstract

View articletitled, Inlet Distortion Generated Periodic Aerodynamic Rotor Response

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Topics: Rotors , Pressure , Blades , Suction , Aerodynamics , Axial flow , Compressors , Design , Flow (Dynamics)

Research Papers

Design and Testing of the FT8 Gas Turbine Low-Pressure Compressor

A Variable-Geometry Power Turbine for Marine Gas Turbines

Surface Roughness Measurements on Gas Turbine Blades

The Influence of Boundary Layer State on Vortex Shedding From Flat Plates and Turbine Cascades

A Theory for Wake-Induced Transition

Effects of Adverse Pressure Gradients on the Nature and Length of Boundary Layer Transition

Unsteady Transition in an Axial-Flow Turbine: Part 1—Measurements on the Turbine Rotor

Unsteady Transition in an Axial-Flow Turbine: Part 2—Cascade Measurements and Modeling

Compressor Blade Boundary Layers: Part 1—Test Facility and Measurements With No Incident Wakes

Compressor Blade Boundary Layers: Part 2—Measurements With Incident Wakes

The Measurement of Boundary Layers on a Compressor Blade in Cascade: Part 4—Flow Fields for Incidence Angles of −1.5 and −8.5 Degrees

Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence

An Improved Incidence Losses Prediction Method for Turbine Airfoils

The Trailing Edge Loss of Transonic Turbine Blades

An Experimental Assessment of the Influence of Downstream Conditions on the Performance of a Transonic Turbine Nozzle of High Turning

The Use of Circumferentially Varying Stagger Guide Vanes in an Axial Flow Pump or Compressor

Inlet Distortion Generated Periodic Aerodynamic Rotor Response

Discussions

Discussion: “The Measurement of Boundary Layers on a Compressor Blade in Cascade: Part 4—Flow Fields for Incidence Angles of −1.5 and −8.5 Degrees” (Zierke, W. C., and Deutsch, S., 1990, ASME J. Turbomach., 112, pp. 241–255)

Closure to “Discussion of ‘The Measurement of Boundary Layers on a Compressor Blade in Cascade: Part 4—Flow Fields for Incidence Angles of −1.5 and −8.5 Degrees’” (1990, ASME J. Turbomach., 112, p. 255)

Discussion: “Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence” (Elazar, Y., and Shreeve, R. P., 1990, ASME J. Turbomach., 112, pp. 256–265)

Closure to “Discussion of ‘Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence’” (1990, ASME J. Turbomach., 112, p. 266)

Technical Briefs

Visualization Studies in Rotating Disk Cavity Flows

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