Ultrasonic de-icing of wind-tunnel impact icing

Jose Palacios; Edward Smith; Joseph Rose; Roger Royer

doi:10.2514/1.C031201

Ultrasonic de-icing of wind-tunnel impact icing

Jose Palacios, Edward Smith, Joseph Rose, Roger Royer

Research output: Contribution to journal › Article › peer-review

95 Scopus citations

Abstract

Ultrasonic excitation has proven to provide ice-interface transverse shear stresses exceeding the adhesion strength of freezer ice to various metals, promoting instantaneous ice delamination. Wind-tunnel impact ice presents challenges that are not encountered when removing freezer ice. The low-power, nonthermal ultrasonic de-icing concept is investigated under impact-icing conditions in an icing wind tunnel. In this research effort, ultrasonic actuator disks excite isotropic plates and airfoil-shaped structures that are representative of helicopter leading-edge protection-cap shapes. Off-the-shelf ultrasonic actuators are used to create ice-interface shear stresses sufficient to promote instantaneous ice delamination of thin layers of impact ice (less than 3 mm thick). A steel plate of 30:48 cm × 30:48 cm × 1 mm was actuated by three lead zirconate titanate disks excited at their ultrasonic radial mode. The ultrasonic vibration introduced transverse shear stresses that prevented ice formation on top of the actuator locations for a fraction of the power required with electrothermal systems used in helicopter rotor blades (0:18 W=cm² vs 3:8 W=cm²). Experiments also showed ice delamination in areas of the plates where transverse shear stresses were concentrated. As ice thicknesses reached a critical value of approximately 1.2 mm, ice debonded from those steel-plate areas. A model of the three disk actuated steel plate was created and correlated with experimental results observed during impact-icing test experiments. Both, the predicted ultrasonic modes of the system and the ice-shedding areas agreed with experimental results. In addition, a second set of experiments involving NACA 0012 airfoil-shaped structures were conducted. Actuators located on the top and bottom surfaces of the leading-edge cap were actuated with an input power as low as 200W(32 kHz ultrasonic mode). Thin layers of ice (less than 2 mm thick) constantly delaminated from the leading edge of the airfoil on those regions where stress concentrations were predicted.

Original language	English (US)
Pages (from-to)	1020-1027
Number of pages	8
Journal	Journal of Aircraft
Volume	48
Issue number	3
DOIs	https://doi.org/10.2514/1.C031201
State	Published - 2011

All Science Journal Classification (ASJC) codes

Aerospace Engineering

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10.2514/1.C031201

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title = "Ultrasonic de-icing of wind-tunnel impact icing",

abstract = "Ultrasonic excitation has proven to provide ice-interface transverse shear stresses exceeding the adhesion strength of freezer ice to various metals, promoting instantaneous ice delamination. Wind-tunnel impact ice presents challenges that are not encountered when removing freezer ice. The low-power, nonthermal ultrasonic de-icing concept is investigated under impact-icing conditions in an icing wind tunnel. In this research effort, ultrasonic actuator disks excite isotropic plates and airfoil-shaped structures that are representative of helicopter leading-edge protection-cap shapes. Off-the-shelf ultrasonic actuators are used to create ice-interface shear stresses sufficient to promote instantaneous ice delamination of thin layers of impact ice (less than 3 mm thick). A steel plate of 30:48 cm × 30:48 cm × 1 mm was actuated by three lead zirconate titanate disks excited at their ultrasonic radial mode. The ultrasonic vibration introduced transverse shear stresses that prevented ice formation on top of the actuator locations for a fraction of the power required with electrothermal systems used in helicopter rotor blades (0:18 W=cm2 vs 3:8 W=cm2). Experiments also showed ice delamination in areas of the plates where transverse shear stresses were concentrated. As ice thicknesses reached a critical value of approximately 1.2 mm, ice debonded from those steel-plate areas. A model of the three disk actuated steel plate was created and correlated with experimental results observed during impact-icing test experiments. Both, the predicted ultrasonic modes of the system and the ice-shedding areas agreed with experimental results. In addition, a second set of experiments involving NACA 0012 airfoil-shaped structures were conducted. Actuators located on the top and bottom surfaces of the leading-edge cap were actuated with an input power as low as 200W(32 kHz ultrasonic mode). Thin layers of ice (less than 2 mm thick) constantly delaminated from the leading edge of the airfoil on those regions where stress concentrations were predicted.",

author = "Jose Palacios and Edward Smith and Joseph Rose and Roger Royer",

note = "Funding Information: The authors would like to thank the U.S. Army and the Aviation Applied Technology Directorate (AATD) for sponsoring this research. Initial work presented on this research regarding impact-icing tests to flat plates is partially funded by the U.S. Army Rotorcraft Centers of Excellence under agreement no. W911W6-06-2-0008. Work done regarding airfoil-shaped structures is partially funded by Phase II Small Business Innovation Research provided by the Aviation Applied Technology Directorate to FBS Worldwide, Inc. (contract no. W911W6-08-C-0064). The authors would also like to thank Galdemir Botura for graciously allowing us to use the Goodrich Icing Wind Tunnel, as well as Bell Helicopters, a Textron Company, for partially funding this research (icing wind-tunnel testing of plates excited by ultrasonic vibration). The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the U.S. Government.",

year = "2011",

doi = "10.2514/1.C031201",

language = "English (US)",

volume = "48",

pages = "1020--1027",

journal = "Journal of Aircraft",

issn = "0021-8669",

publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",

number = "3",

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T1 - Ultrasonic de-icing of wind-tunnel impact icing

AU - Palacios, Jose

AU - Smith, Edward

AU - Rose, Joseph

AU - Royer, Roger

N1 - Funding Information: The authors would like to thank the U.S. Army and the Aviation Applied Technology Directorate (AATD) for sponsoring this research. Initial work presented on this research regarding impact-icing tests to flat plates is partially funded by the U.S. Army Rotorcraft Centers of Excellence under agreement no. W911W6-06-2-0008. Work done regarding airfoil-shaped structures is partially funded by Phase II Small Business Innovation Research provided by the Aviation Applied Technology Directorate to FBS Worldwide, Inc. (contract no. W911W6-08-C-0064). The authors would also like to thank Galdemir Botura for graciously allowing us to use the Goodrich Icing Wind Tunnel, as well as Bell Helicopters, a Textron Company, for partially funding this research (icing wind-tunnel testing of plates excited by ultrasonic vibration). The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the U.S. Government.

PY - 2011

Y1 - 2011

N2 - Ultrasonic excitation has proven to provide ice-interface transverse shear stresses exceeding the adhesion strength of freezer ice to various metals, promoting instantaneous ice delamination. Wind-tunnel impact ice presents challenges that are not encountered when removing freezer ice. The low-power, nonthermal ultrasonic de-icing concept is investigated under impact-icing conditions in an icing wind tunnel. In this research effort, ultrasonic actuator disks excite isotropic plates and airfoil-shaped structures that are representative of helicopter leading-edge protection-cap shapes. Off-the-shelf ultrasonic actuators are used to create ice-interface shear stresses sufficient to promote instantaneous ice delamination of thin layers of impact ice (less than 3 mm thick). A steel plate of 30:48 cm × 30:48 cm × 1 mm was actuated by three lead zirconate titanate disks excited at their ultrasonic radial mode. The ultrasonic vibration introduced transverse shear stresses that prevented ice formation on top of the actuator locations for a fraction of the power required with electrothermal systems used in helicopter rotor blades (0:18 W=cm2 vs 3:8 W=cm2). Experiments also showed ice delamination in areas of the plates where transverse shear stresses were concentrated. As ice thicknesses reached a critical value of approximately 1.2 mm, ice debonded from those steel-plate areas. A model of the three disk actuated steel plate was created and correlated with experimental results observed during impact-icing test experiments. Both, the predicted ultrasonic modes of the system and the ice-shedding areas agreed with experimental results. In addition, a second set of experiments involving NACA 0012 airfoil-shaped structures were conducted. Actuators located on the top and bottom surfaces of the leading-edge cap were actuated with an input power as low as 200W(32 kHz ultrasonic mode). Thin layers of ice (less than 2 mm thick) constantly delaminated from the leading edge of the airfoil on those regions where stress concentrations were predicted.

AB - Ultrasonic excitation has proven to provide ice-interface transverse shear stresses exceeding the adhesion strength of freezer ice to various metals, promoting instantaneous ice delamination. Wind-tunnel impact ice presents challenges that are not encountered when removing freezer ice. The low-power, nonthermal ultrasonic de-icing concept is investigated under impact-icing conditions in an icing wind tunnel. In this research effort, ultrasonic actuator disks excite isotropic plates and airfoil-shaped structures that are representative of helicopter leading-edge protection-cap shapes. Off-the-shelf ultrasonic actuators are used to create ice-interface shear stresses sufficient to promote instantaneous ice delamination of thin layers of impact ice (less than 3 mm thick). A steel plate of 30:48 cm × 30:48 cm × 1 mm was actuated by three lead zirconate titanate disks excited at their ultrasonic radial mode. The ultrasonic vibration introduced transverse shear stresses that prevented ice formation on top of the actuator locations for a fraction of the power required with electrothermal systems used in helicopter rotor blades (0:18 W=cm2 vs 3:8 W=cm2). Experiments also showed ice delamination in areas of the plates where transverse shear stresses were concentrated. As ice thicknesses reached a critical value of approximately 1.2 mm, ice debonded from those steel-plate areas. A model of the three disk actuated steel plate was created and correlated with experimental results observed during impact-icing test experiments. Both, the predicted ultrasonic modes of the system and the ice-shedding areas agreed with experimental results. In addition, a second set of experiments involving NACA 0012 airfoil-shaped structures were conducted. Actuators located on the top and bottom surfaces of the leading-edge cap were actuated with an input power as low as 200W(32 kHz ultrasonic mode). Thin layers of ice (less than 2 mm thick) constantly delaminated from the leading edge of the airfoil on those regions where stress concentrations were predicted.

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Ultrasonic de-icing of wind-tunnel impact icing

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