Plasma actuator for wake flow control of high camber blades during part load operation

Robert Van Dyken, Aaron Byerley, Horacio Perez-Blanco, Tom McLaughlin

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)

Abstract

Plasma actuators, composed of two electrodes with a constant or time-varying voltage difference applied between them are known to impart a directed momentum on the gas in the vicinity of one of the electrodes. This work focuses on a plasma actuator installed on one blade of a gas turbine blade cascade. These high-camber angle blades are used for transportation and stationary applications, and at partial load (i.e. low flow speeds) they exhibit flow separation on the suction side. A plasma actuator, optimized in terms of insulation thickness and applied voltage waveform, is placed on the suction-side, near the trailing edge of the blade, and airfoil plasma-off performance compared to plasma-on. Separation is detected via surface pressure measurements, and loss of stagnation pressure via measurements of total pressure with Pitot tubes. Flow directions are measured in a few cases as well. The actuator is found to decrease the stagnation pressure loss at most experimental conditions, and to increase the flow turning angle. Conclusions as to the plasma actuator effectiveness are derived from blade loss coefficients. The plasma actuator can reduce stagnation pressure losses by 50% with the most effective actuator of those investigated thus far in this cascade. An approximate ratio of electrical to dynamic forces is defined and calculated as a means of characterizing the relative magnitude of the plasma force required to avert separation. Since the loss is measured in the wake of the blade, the term "wake filling configuration" seems an appropriate description of this specific actuator location.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2004: Volume 5A: Electric Power; Turbomachinery; Gen. Interest; Axial Flow Fan and Compressor Aerodynamics; Radial Turbomachinery Aerodynamics;Unsteady Flows in Turb
Pages351-363
Number of pages13
Volume5 A
StatePublished - 2004
Event2004 ASME Turbo Expo - Vienna, Austria
Duration: Jun 14 2004Jun 17 2004

Other

Other2004 ASME Turbo Expo
CountryAustria
CityVienna
Period6/14/046/17/04

Fingerprint

Cambers
Flow control
Actuators
Plasmas
Turbomachine blades
Electrodes
Cascades (fluid mechanics)
Flow separation
Surface measurement
Electric potential
Pressure measurement
Airfoils
Gas turbines
Insulation
Momentum

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Van Dyken, R., Byerley, A., Perez-Blanco, H., & McLaughlin, T. (2004). Plasma actuator for wake flow control of high camber blades during part load operation. In Proceedings of the ASME Turbo Expo 2004: Volume 5A: Electric Power; Turbomachinery; Gen. Interest; Axial Flow Fan and Compressor Aerodynamics; Radial Turbomachinery Aerodynamics;Unsteady Flows in Turb (Vol. 5 A, pp. 351-363)
Van Dyken, Robert ; Byerley, Aaron ; Perez-Blanco, Horacio ; McLaughlin, Tom. / Plasma actuator for wake flow control of high camber blades during part load operation. Proceedings of the ASME Turbo Expo 2004: Volume 5A: Electric Power; Turbomachinery; Gen. Interest; Axial Flow Fan and Compressor Aerodynamics; Radial Turbomachinery Aerodynamics;Unsteady Flows in Turb. Vol. 5 A 2004. pp. 351-363
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abstract = "Plasma actuators, composed of two electrodes with a constant or time-varying voltage difference applied between them are known to impart a directed momentum on the gas in the vicinity of one of the electrodes. This work focuses on a plasma actuator installed on one blade of a gas turbine blade cascade. These high-camber angle blades are used for transportation and stationary applications, and at partial load (i.e. low flow speeds) they exhibit flow separation on the suction side. A plasma actuator, optimized in terms of insulation thickness and applied voltage waveform, is placed on the suction-side, near the trailing edge of the blade, and airfoil plasma-off performance compared to plasma-on. Separation is detected via surface pressure measurements, and loss of stagnation pressure via measurements of total pressure with Pitot tubes. Flow directions are measured in a few cases as well. The actuator is found to decrease the stagnation pressure loss at most experimental conditions, and to increase the flow turning angle. Conclusions as to the plasma actuator effectiveness are derived from blade loss coefficients. The plasma actuator can reduce stagnation pressure losses by 50{\%} with the most effective actuator of those investigated thus far in this cascade. An approximate ratio of electrical to dynamic forces is defined and calculated as a means of characterizing the relative magnitude of the plasma force required to avert separation. Since the loss is measured in the wake of the blade, the term {"}wake filling configuration{"} seems an appropriate description of this specific actuator location.",
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Van Dyken, R, Byerley, A, Perez-Blanco, H & McLaughlin, T 2004, Plasma actuator for wake flow control of high camber blades during part load operation. in Proceedings of the ASME Turbo Expo 2004: Volume 5A: Electric Power; Turbomachinery; Gen. Interest; Axial Flow Fan and Compressor Aerodynamics; Radial Turbomachinery Aerodynamics;Unsteady Flows in Turb. vol. 5 A, pp. 351-363, 2004 ASME Turbo Expo, Vienna, Austria, 6/14/04.

Plasma actuator for wake flow control of high camber blades during part load operation. / Van Dyken, Robert; Byerley, Aaron; Perez-Blanco, Horacio; McLaughlin, Tom.

Proceedings of the ASME Turbo Expo 2004: Volume 5A: Electric Power; Turbomachinery; Gen. Interest; Axial Flow Fan and Compressor Aerodynamics; Radial Turbomachinery Aerodynamics;Unsteady Flows in Turb. Vol. 5 A 2004. p. 351-363.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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T1 - Plasma actuator for wake flow control of high camber blades during part load operation

AU - Van Dyken, Robert

AU - Byerley, Aaron

AU - Perez-Blanco, Horacio

AU - McLaughlin, Tom

PY - 2004

Y1 - 2004

N2 - Plasma actuators, composed of two electrodes with a constant or time-varying voltage difference applied between them are known to impart a directed momentum on the gas in the vicinity of one of the electrodes. This work focuses on a plasma actuator installed on one blade of a gas turbine blade cascade. These high-camber angle blades are used for transportation and stationary applications, and at partial load (i.e. low flow speeds) they exhibit flow separation on the suction side. A plasma actuator, optimized in terms of insulation thickness and applied voltage waveform, is placed on the suction-side, near the trailing edge of the blade, and airfoil plasma-off performance compared to plasma-on. Separation is detected via surface pressure measurements, and loss of stagnation pressure via measurements of total pressure with Pitot tubes. Flow directions are measured in a few cases as well. The actuator is found to decrease the stagnation pressure loss at most experimental conditions, and to increase the flow turning angle. Conclusions as to the plasma actuator effectiveness are derived from blade loss coefficients. The plasma actuator can reduce stagnation pressure losses by 50% with the most effective actuator of those investigated thus far in this cascade. An approximate ratio of electrical to dynamic forces is defined and calculated as a means of characterizing the relative magnitude of the plasma force required to avert separation. Since the loss is measured in the wake of the blade, the term "wake filling configuration" seems an appropriate description of this specific actuator location.

AB - Plasma actuators, composed of two electrodes with a constant or time-varying voltage difference applied between them are known to impart a directed momentum on the gas in the vicinity of one of the electrodes. This work focuses on a plasma actuator installed on one blade of a gas turbine blade cascade. These high-camber angle blades are used for transportation and stationary applications, and at partial load (i.e. low flow speeds) they exhibit flow separation on the suction side. A plasma actuator, optimized in terms of insulation thickness and applied voltage waveform, is placed on the suction-side, near the trailing edge of the blade, and airfoil plasma-off performance compared to plasma-on. Separation is detected via surface pressure measurements, and loss of stagnation pressure via measurements of total pressure with Pitot tubes. Flow directions are measured in a few cases as well. The actuator is found to decrease the stagnation pressure loss at most experimental conditions, and to increase the flow turning angle. Conclusions as to the plasma actuator effectiveness are derived from blade loss coefficients. The plasma actuator can reduce stagnation pressure losses by 50% with the most effective actuator of those investigated thus far in this cascade. An approximate ratio of electrical to dynamic forces is defined and calculated as a means of characterizing the relative magnitude of the plasma force required to avert separation. Since the loss is measured in the wake of the blade, the term "wake filling configuration" seems an appropriate description of this specific actuator location.

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M3 - Conference contribution

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BT - Proceedings of the ASME Turbo Expo 2004: Volume 5A: Electric Power; Turbomachinery; Gen. Interest; Axial Flow Fan and Compressor Aerodynamics; Radial Turbomachinery Aerodynamics;Unsteady Flows in Turb

ER -

Van Dyken R, Byerley A, Perez-Blanco H, McLaughlin T. Plasma actuator for wake flow control of high camber blades during part load operation. In Proceedings of the ASME Turbo Expo 2004: Volume 5A: Electric Power; Turbomachinery; Gen. Interest; Axial Flow Fan and Compressor Aerodynamics; Radial Turbomachinery Aerodynamics;Unsteady Flows in Turb. Vol. 5 A. 2004. p. 351-363