Patents by Inventor Ching-Pang Lee

Ching-Pang Lee has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • COOLING SYSTEM IN A TURBINE AIRFOIL ASSEMBLY INCLUDING ZIGZAG COOLING PASSAGES INTERCONNECTED WITH RADIAL PASSAGEWAYS
    Publication number: 20140037461
    Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, a plurality of cooling fluid passages, and a plurality of radial passageways. The outer wall has leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge. The radial passageways interconnect radially adjacent cooling fluid passages.
    Type: Application
    Filed: October 8, 2013
    Publication date: February 6, 2014
    Inventor: Ching-Pang Lee
  • Flared tip turbine blade
    Patent number: 8632311
    Abstract: A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.
    Type: Grant
    Filed: August 21, 2006
    Date of Patent: January 21, 2014
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
  • FINNED SEAL ASSEMBLY FOR GAS TURBINE ENGINES
    Publication number: 20140003919
    Abstract: A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.
    Type: Application
    Filed: June 27, 2012
    Publication date: January 2, 2014
    Inventors: Ching-Pang Lee, Kok-Mun Tham, John M. Owen, Gary D. Lock, Carl M. Sangan, Vincent P. Laurello
  • Film cooled component wall in a turbine engine
    Patent number: 8608443
    Abstract: A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is defined by a bottom surface between the first and second surfaces, a first sidewall, and a second sidewall spaced from the first sidewall. The first sidewall extends radially outwardly continuously from the bottom surface of the trench to the second surface. The first sidewall includes a plurality of first protuberances extending toward the second sidewall. The cooling passages extend through the substrate from the first surface to the bottom surface of the trench. Outlets of the cooling passages are arranged within the trench such that cooling air exiting the cooling passages is directed toward respective ones of the first protuberances.
    Type: Grant
    Filed: June 11, 2010
    Date of Patent: December 17, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Jae Y. Um, Mrinal Munshi, Humberto A. Zuniga
  • TURBINE BLADE WITH CHAMFERED SQUEALER TIP FORMED FROM MULTIPLE COMPONENTS AND CONVECTIVE COOLING HOLES
    Publication number: 20130302166
    Abstract: A squealer tip usable in repair systems and formed from a pressure side outer weld rib and a suction side outer weld rib extending radially outward from a tip of the turbine blade and resting upon pressure side and suction side weld members separated by a mid-chord member is disclosed. The pressure and suction side outer weld ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure side outer weld rib may include a chamfered pressure side with film cooling holes having exhaust outlets positioned therein. The pressure and suction side weld members may be configured to retain the mid-chord member in position with over extending side surfaces.
    Type: Application
    Filed: May 9, 2012
    Publication date: November 14, 2013
    Inventors: CHING-PANG LEE, Mrinal Munshi
  • Near-Wall Serpentine Cooled Turbine Airfoil
    Publication number: 20130302167
    Abstract: Certain exemplary embodiments can provide a serpentine coolant flow path formed by inner walls in a cavity between pressure and suction side walls of a turbine airfoil and/or can be adapted to provide cooling matched to the heating topography of the airfoil, minimize differential thermal expansion, revive the coolant, and/or minimize the flow volume needed.
    Type: Application
    Filed: July 16, 2013
    Publication date: November 14, 2013
    Inventor: Ching-Pang Lee
  • METHOD OF PROVIDING A TURBINE BLADE TIP REPAIR
    Publication number: 20130298400
    Abstract: A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade tip. The method comprises removing at least a portion of the blade tip to form a repair surface and providing a tip cap having a radially outer side with an outer width that may be less than the internal cavity width, and having a radially inner side with an inner width that is substantially equal to or greater than the internal cavity width. The tip cap is positioned at the repair surface, and the tip cap is welded to the repair surface using a ductile welding material. A cap peripheral portion is formed by build-up welding around the tip cap, and a squealer portion is formed by build-up welding on the cap peripheral portion.
    Type: Application
    Filed: May 9, 2012
    Publication date: November 14, 2013
    Inventors: Mrinal Munshi, Ching-Pang Lee, Benjamin P. Swanson, Petya M. Georgieva, James A. Morin
  • TURBINE ENGINE COMPONENT WALL HAVING BRANCHED COOLING PASSAGES
    Publication number: 20130294898
    Abstract: A component wall in a turbine engine includes a substrate and at least one cooling passage that extends through the substrate for delivering cooling fluid from a chamber associated with an inner surface of the substrate to an outer surface of the substrate. Each cooling passage is divided into at least two branches that receive cooling fluid from an entrance portion of the cooling passage that is in communication with the chamber. The branches each include an intermediate portion that extends transversely from the entrance portion and that receives cooling fluid from the entrance portion, and an exit portion that extends transversely from the respective intermediate portion. The exit portions receive the cooling fluid from the intermediate portions and deliver the cooling fluid out of the respective branch through exit portion outlets.
    Type: Application
    Filed: May 4, 2012
    Publication date: November 7, 2013
    Inventor: Ching-Pang Lee
  • Near-wall serpentine cooled turbine airfoil
    Patent number: 8535006
    Abstract: A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.
    Type: Grant
    Filed: July 14, 2010
    Date of Patent: September 17, 2013
    Assignee: Siemens Energy, Inc.
    Inventor: Ching-Pang Lee
  • TURBINE AIRFOIL WITH AN INTERNAL COOLING SYSTEM HAVING VORTEX FORMING TURBULATORS
    Publication number: 20130236330
    Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The configuration of turbulators may create a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance.
    Type: Application
    Filed: March 12, 2012
    Publication date: September 12, 2013
    Inventor: Ching-Pang Lee
  • Tip ramp turbine blade
    Patent number: 8512003
    Abstract: A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.
    Type: Grant
    Filed: August 21, 2006
    Date of Patent: August 20, 2013
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
  • Cascade tip baffle airfoil
    Patent number: 8500396
    Abstract: A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.
    Type: Grant
    Filed: August 21, 2006
    Date of Patent: August 6, 2013
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
  • COMPOSITE CORE DIE, METHODS OF MANUFACTURE THEREOF AND ARTICLES MANUFACTURED THEREFROM
    Publication number: 20130186585
    Abstract: A composite core die includes a reusable core die; and a disposable core die. The disposable core die is in physical communication with the reusable core die and surfaces of communication between the disposable core die and the reusable core die serve as barriers to prevent the leakage of a slurry that is disposed in the composite core die.
    Type: Application
    Filed: March 13, 2013
    Publication date: July 25, 2013
    Applicant: General Electric Company
    Inventors: Ching-Pang Lee, Hsin-Pang Wang, Ram Kumar Upadhyay, Paul Richard Myers, Marc Thomas Edgar, Thomas Donald Martyn, Eric Alan Estill
  • AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING
    Publication number: 20130156579
    Abstract: A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.
    Type: Application
    Filed: February 14, 2013
    Publication date: June 20, 2013
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Eric Schroeder, Jamie Meeroff, Samuel R. Miller, JR., John J. Marra
  • GAS TURBINE ENGINE WITH OUTER CASE AMBIENT EXTERNAL COOLING SYSTEM
    Publication number: 20130149120
    Abstract: A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.
    Type: Application
    Filed: December 8, 2011
    Publication date: June 13, 2013
    Inventors: Mrinal Munshi, John Finneran, Ching-Pang Lee, Yevgeniy Shteyman, Daryl Graber, Matthew R. Porter, Jonathan M. Leagon
  • COMPONENT HAVING COOLING CHANNEL WITH HOURGLASS CROSS SECTION
    Publication number: 20130149169
    Abstract: A cooling channel (36, 36B, 63-66) cools inner surfaces (48, 50) of exterior walls (41, 43) of a component (20, 60). Interior side surfaces (52, 54) of the channel converge to a waist (W2), forming an hourglass shaped transverse profile (46). The inner surfaces (48, 50) may have fins (44) aligned with the coolant flow (22). The fins may have a transverse profile (56A, 56B) highest at mid-width of the inner surfaces (48, 50). Turbulators (92) may be provided on the side surfaces (52, 54) of the channel, and may urge the coolant flow toward the inner surfaces (48, 50). Each turbulator (92) may have a peak (97) that defines the waist of the cooling channel. Each turbulator may have a convex upstream side (93). These elements increase coolant flow in the corners (C) of the channel to more uniformly and efficiently cool the exterior walls (41, 43).
    Type: Application
    Filed: February 6, 2013
    Publication date: June 13, 2013
    Inventors: Christian X. Campbell, Ching-Pang Lee
  • Curved platform turbine blade
    Patent number: 8459956
    Abstract: A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.
    Type: Grant
    Filed: December 24, 2008
    Date of Patent: June 11, 2013
    Assignee: General Electric Company
    Inventors: Vidhu Shekhar Pandey, Ching-Pang Lee, Jan Christopher Schilling, Aspi Rustom Wadia, Brian David Keith, Jeffrey Donald Clements
  • TURBINE BLADE INCORPORATING TRAILING EDGE COOLING DESIGN
    Publication number: 20130142666
    Abstract: A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one embodiment a first wall portion (70-2) between first and second chambers (60, 52) includes first and second pluralities of flow paths (86P, 86S) extending through the first wall portion. The first wall portion includes a first region R1 having a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening (78) in the first chamber (60), through the first region and to an exit opening (82) in the second chamber (52) which path distance is greater than the first thickness.
    Type: Application
    Filed: December 6, 2011
    Publication date: June 6, 2013
    Inventors: Ching-Pang Lee, Glenn E. Brown, Benjamin E. Heneveld
  • Plasma induced flow control of boundary layer at airfoil endwall
    Patent number: 8435001
    Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.
    Type: Grant
    Filed: December 17, 2009
    Date of Patent: May 7, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Matthew D. Montgomery, Ching-Pang Lee, Chander Prakash
  • Triforial tip cavity airfoil
    Patent number: 8425183
    Abstract: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.
    Type: Grant
    Filed: November 20, 2006
    Date of Patent: April 23, 2013
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Kevin Samuel Klasing, Paul Hadley Vitt, Brian David Keith