Fluid reaction surfaces (i.e. – impellers) – Method of operation
Reexamination Certificate
2006-12-15
2009-12-08
Look, Edward (Department: 3745)
Fluid reaction surfaces (i.e., impellers)
Method of operation
C415S010000, C415S914000, C416S09600A
Reexamination Certificate
active
07628585
ABSTRACT:
A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.
REFERENCES:
patent: 5181379 (1993-01-01), Wakeman et al.
patent: 5233828 (1993-08-01), Napoli
patent: 5241827 (1993-09-01), Lampes
patent: 5320309 (1994-06-01), Nosenchuck et al.
patent: 5337568 (1994-08-01), Lee et al.
patent: 5419681 (1995-05-01), Lee
patent: 5465572 (1995-11-01), Nicoll et al.
patent: 5503529 (1996-04-01), Anselmi et al.
patent: 5651662 (1997-07-01), Lee et al.
patent: 5660525 (1997-08-01), Lee et al.
patent: 5747769 (1998-05-01), Rockstroh et al.
patent: 6283713 (2001-09-01), Harvey et al.
patent: 6570333 (2003-05-01), Miller et al.
patent: 6619030 (2003-09-01), Seda et al.
patent: 6655149 (2003-12-01), Farmer et al.
patent: 6708482 (2004-03-01), Seda
patent: 6732502 (2004-05-01), Seda et al.
patent: 6761956 (2004-07-01), Lee et al.
patent: 6805325 (2004-10-01), Malmuth et al.
patent: 6991430 (2006-01-01), Stec et al.
patent: 7008179 (2006-03-01), Rinck et al.
patent: 7094027 (2006-08-01), Turner et al.
patent: 2006/0005545 (2006-01-01), Samimy et al.
patent: 2006/0104807 (2006-05-01), Lee
patent: 1906136 (2008-09-01), None
patent: WO2005/114013 (2005-12-01), None
European Search Report and Opinion, Application No. EP07254056, Mar. 12, 2009, 10 pages.
AIAA 2007-647, Stereo PIV of a Turbine Tip Clearance Flow with Plasma Actuation, Daniel K. Van Ness II, Thomas C. Corke, and Scott C. Morris, 22 pages.
AIAA 2006-20, “Turbine Blade Tip Leakage Flow Control by Partial Squealer Tip and Plasma Actuators”, Travis Douville, Julia Stephens, Thomas Corke, and Scott Morris, 18 pages.
AIAA 2005-782, “Tip Clearance Control Using Plasma Actuators”, Scott C. Morris, Thomas C. corke, Daniel Van Ness, Julia Stephens, and Travis Douville, 8 pages.
XP007907306, “Active Flow Control in Turbomachinery Using Phased Plasma Actuators”, B. Goksel and I. Rechenberg, 2 pages.
XP009112404, “Turbine Tip Clearance Flow Control using Plasma Actuators”, Daniel K. Van Ness II, Thomas Co. Corke, and Scott C. Morris, 12 pages.
Science Direct, “SDBD plasma enhanced aerodynamics: concepts optimization and applications”, Thomas C. Corke, Martiqua L. Post, and Dmitry M. Orlov, 26 pages.
XP007907356, “Plasma (physics)”, From Wikipedia, 16 pages.
XP007907353, “Dielectric barrier discharge”, From Wikipedia, 2 pages.
“Overview of Plasma Flow Control: Concepts, Optimization, and Applications”, Thomas C. Corke and Martiqua L. Post, 43rd AIAA Aerospace Sciences Meeting and Exhibit, Jan. 10-13, 2005, Reno, Nevada, AIAA 2005-563, 15 pages.
“Plasma Control Of Boundary Layer Using Low-Temperature Non-Equilibrium Plasma Of Gas Discharge”, D.F. Opaits, D.V. Roupassov, S.M. Starikovskaia, A.Yu. Starikovskii, I.N. Zavialov, and S.G. Saddoughi, 43rd AIAA Aerospace Sciences Meeting and Exhibit, Jan. 10-13, 2005, Reno, Nevada, AIAA 2005-1180, 6 pages.
“Demonstration Of Separation Delay With Glow-Discharge Plasma Actuators”, Lennart S. Hultgren and David E. Ashpis, 41st AIAA Aerospace Sciences Meeting and Exhibit, Jan. 6-9, 2003, Reno, Nevada, AIAA 2003-1025, 10 pages.
“Unsteady Plasma Actuators for Separation Control of Low-Pressure Turbine Blades”, Junhui Huang, Thomas C. Corke and Flint O. Thomas, AIAA Journal, vol. 44, No. 7, Jul. 2006, pp. 1477-1487.
“Control of Separation in Turbine Boundary Layers”, R.B. Rivir, R. Sondergaard, J.P. Bons, and N. Yurchenko, 2nd AIAA Flow Control Conference, Jun. 28-Jul. 1, 2004, Portland, Oregon, 16 pages.
“Plasma Flow Control Optimized Airfoil”, Thomas C. Corke, Benjamin Mertz, and Mehul P. Patel, 44th AIAA Aerospace Sciences Meeting and Exhibit, Jan. 9-12, 2006, Reno, Nevada, AIAA 2006-1208, 13 pages.
“Control of Transitional and Turbulent Flows Using Plasma-Based Actuators”, Miguel R. Visbal, Datta V. Gaitonde, and Subrata Roy, 36th AIAA Fluid Dynamics Conference and Exhibit, Jun. 5-8, 2006, San Francisco, California, AIAA 2006-3230, 22 pages.
“AC And Pulsed Plasma Flow Control”, R. Rivir, A. White, C. Carter, B. Ganguly, J. Jacob, A. Forelines, and J. Crafton, 42nd AIAA Aerospace Sciences Meeting and Exhibit, Jan. 5-8, 2004, Reno, Nevada, AIAA 2004-847, 9 pages.
“Effects Of Plasma Induced Velocity On Boundary Layer Flow”, Brian E. Balcer, Milton E. Franke, and Richard B. Rivir, 44th AIAA Aerospace Sciences Meeting and Exhibit, Jan. 9-12, 2006, Reno, Nevada, AIAA 2006-875, 12 pages.
“Flow Control Using Plasma Actuators and Linear / Annular Plasma Synthetic Jet Actuators”, Arvind Santhanakrishan, Jamey D. Jacob, and Yildirim B. Suzen, 3rd AIAA Flow Control Conference, Jun. 5-8, 2006, San Francisco, California, AIAA 2006-3033, 31 pages.
“Turbulent Drag Reduction by Surface Plasma through Spanwise Flow Oscillation”, Timothy N. Jukes, Kwing-So Choi, Graham A. Johnson, and Simon J. Scott, 3rd AIAA Flow Control Conference, Jun. 5-8, 2006, San Francisco, California, AIAA 2006-3693, 14 pages.
Cherry David Glenn
Han Je-Chin
Lee Ching-Pang
Wadia Aspi Rustom
Andes William Scott
General Electric Company
Look Edward
Rosen Steven J.
Younger Sean J
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