Rotary kinetic fluid motors or pumps – With sound or vibratory wave absorbing or preventing means...
Reexamination Certificate
2005-09-27
2005-09-27
Look, Edward K. (Department: 3745)
Rotary kinetic fluid motors or pumps
With sound or vibratory wave absorbing or preventing means...
C415S914000, C416S09000A, C416S09000A, C416S091000
Reexamination Certificate
active
06948906
ABSTRACT:
A rotor blade system with reduced blade-vortex interaction noise includes a plurality of tube members embedded in proximity to a tip of each rotor blade. The inlets of the tube members are arrayed at the leading edge of the blade slightly above the chord plane, while the outlets are arrayed at the blade tip face. Such a design rapidly diffuses the vorticity contained within the concentrated tip vortex because of enhanced flow mixing in the inner core, which prevents the development of a laminar core region.
REFERENCES:
patent: 3692259 (1972-09-01), Yuan
patent: 3936013 (1976-02-01), Yuan
patent: 4045146 (1977-08-01), Crimi
patent: 4655685 (1987-04-01), Fradenburgh
patent: 5562414 (1996-10-01), Azuma
patent: 5791875 (1998-08-01), Ngo
patent: 6203269 (2001-03-01), Lorber et al.
patent: 6283406 (2001-09-01), Remington et al.
patent: 6295006 (2001-09-01), Kohlhepp
patent: 06199295 (1994-07-01), None
Leishman, J.G., and Bagai, A., “Challenges in Understanding the Vortex Dynamics of Helicopter Rotor Wakes,” A/AA Journal, vol. 36, No. 7, Jul. 1998, pp. 1130-1140.
Leishman, J.G., Principles of Helicopter Aerodynamics, Cambridge University Press, 2000, Chapter 10.
Schmitz, F.H., “Rotor Noise,” Chapter 2, Aeroacoustics of Flight Vehicles: Theory and Practice, vol. 1, NASA Reference Publication 1258, Aug. 1991.
Berry, J.D., and Mineck, R.E., “Wind Tunnel Test for an Articulated Helicopter Rotor Model with Several Tip Shapes,” NASA-TM-80080, Dec., 1980.
Martin, P.B. and Leishman, J.G., “Trailing Vortex Measurements in the Wake of a Hovering Rotor Blade with Various Tip Shapes,” Proceedings of the 58th Annual Forum of the.
Tangler, J.L., “Experimental Investigation of the Sub-wing Tip and Its Vortex Structure,” NASA CR-3058, 1978.
Marchman, J.F. III, and Uzel, J.N., “Effect of Several Wing Tip Modifications on a Trailing Vortex” Journal of Aircraft, vol. 9, No. 9, 1972, pp. 684-686.
McAlister, K.W., Tung, C., and Heineck, J.T., “Devices that Alter the Tip Vortex of a Rotor,” NASA/TM-2001-209625 (AFDD/TR-01-A-003), 2001.
Kantha, H.L., Lewellen, W.S., and Durgin, F.H., “Response of a Trailing Vortex to Axial Injection into the Core,” Journal of Aircraft, vol. 9, No. 3, 1972, pp. 254-256.
Liu, Z., Russel, J.W. and Sankar, L.N., “A study of Rotor Tip Structure Alteration Technique,” Journal of Aircraft, vol. 38, No. 3, 2001, pp. 473-477.
Han, Y.O., and Bae, H., “Modification of the Tip Vortex by Span-wise Slots,” KSAS Korean Journal, vol. 27, No. 5, 1998, pp. 1-7.
Han, Y.O., and Chung, W.J., “Mean and Turbulent Characteristics of Tip Vortices Generated by a Slotted Model Blade,” Proceedings of 5th Engineering Turbulence Modeling.
Martin, P.B., Bhagwat, M.J., and Leishman, J.G., “Strobed Laser-Sheet Visualization of a Helicopter Rotor Wake,” 2nd Pacific Symposium on Flow Visualization and Image Pro.
Bhagwat, M.J., and Leishman, J.G., “Stability Analysis of Rotor Wakes in Axial Flight,” Journal of the American Helicoptor Society, vol. 45, No. 3, 2000, pp. 165-178.
Leishman, J.G., “Seed Particle Dynamics in Tip Vortex Flow,” Journal of Aircraft, vol. 33, No. 4, 1996, pp. 823-825.
Martin, P.B., Pugliese, G.J., and Leishman, J.G., “Laser Doppler Velocimetry Uncertainty Analysis For Rotor Blade Tip Vortex Measurements,” AIAA CP 2000-0263, 38th Ae.
Barrett, R.V., and Swales, C., “Realisation of the Full Potential of the Laser Doppler Anemometer in the Analysis of Complex Flows,” Aeronautical Journal, vol. 102, No. 1.
Tung, C., Caradonna, F.X., and Morse, H.A., “The Structure of Trailing Vortices Generated by Model Rotor Blades,” Vertica, vol. 7, 1983, pp. 33-43.
Tennekes, H, and Lumley, J.L., A First Course in Turbulence, MIT Press, 1972.
Vatistas, G.H., Kozel, V., and Mih, W.C., “Simpler Model for Concentrated Vorticies,” Experiments in Fluids, vol. 24, No. 11, 1991, pp. 73-76.
Lamb, H., Hydrodynamics, 6th Ed. Cambridge University Press, Cambridge, UK 1932.
Oseen, C.W., “Uber Wirbelbewegung in Einer Reiben den Flussigkeit,” Ark. J. Mat. Astrom. Fys., vol. 7, 1912, pp. 14-21.
Bhagwat, M.J., and Leishman, J.G., “Viscous Vortex Core Models for Free-Vortex Wake Calculations,” Proceedings of the 58th Annual Forum of the American Helicopter Societ.
Bhagwat, M.J., and Leishman, J.G., “Correlation of Helicopter Rotor Tip Vortex Measurements,” AIAA Journal, vol. 38, No. 2, 2000, pp. 301-308.
Squire, H.B., “The Growth of a Vortex in Turbulent Flow,” The Aeronautical Quarterly, Aug. 1965, pp. 302-305.
Cotel, A.J., and Breidenthal, R.E., “Turbulence Inside a Vortex,” Physics of Fluids, vol. 11, No. 10, 1999, pp. 3026-3029.
Bradshaw, P., “The analogy Between Streamline Curvature and Bouyancy in Turbulent Shear Flows,” Journal of Fluid Mechanics, vol. 36, Part 1, pp. 177-191.
Iverson, J.D., “Correlation of Turbulent Trailing Vortex Decay Data,” Journal of Aircraft, vol. 13, No. 3, 1976, pp. 338-342.
Devenport, W.J., Rife, M.C., Liapis, S.I., and Follin, G.J., “The Structure and Development of a Wing-Tip Vortex,” Journal of Fluid Mechanics, vol. 312, 1996, pp. 67-106.
Leishman, J.G., “Measurements of the Aperiodic Wake of a hovering Rotor,” Experiments in Fluids, vol. 25, 1998, pp. 352-361.
Gursul, I., and Xie, W., “Origin of Vortex Wandering Over Delta Wings,” Journal of Aircraft, vol. 37, No. 2, 1999, pp. 348-350.
Han Yong Oun
Leishman John G.
Kershteyn Igor
Look Edward K.
Rosenberg , Klein & Lee
University of Maryland
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