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).

  • COOLED CONDUIT FOR CONVEYING COMBUSTION GASES
    Publication number: 20110302924
    Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.
    Type: Application
    Filed: June 11, 2010
    Publication date: December 15, 2011
    Inventors: Ching-Pang Lee, Chander Prakash, Reinhard Schilp, David A. Little
  • COMPONENT WALL HAVING DIFFUSION SECTIONS FOR COOLING IN A TURBINE ENGINE
    Publication number: 20110305583
    Abstract: A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single cooling passage for directing cooling air toward a protuberance of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be-formed diffusion sections in the wall. A masking material can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.
    Type: Application
    Filed: June 11, 2010
    Publication date: December 15, 2011
    Inventors: Ching-Pang Lee, Jae Y. Um, Mrinal Munshi, Humberto A. Zuniga
  • METHOD OF CASTING A COMPONENT HAVING INTERIOR PASSAGEWAYS
    Publication number: 20110293434
    Abstract: A method of casting a component (42) having convoluted interior passageways (44). A desired three dimensional structure corresponding to a later-formed metal alloy component is formed by stacking a plurality of sheets (18, 20) of a fugitive material. The sheets contain void areas (22) corresponding to a desired interior passageway in the metal alloy component. A ceramic slurry material is cast into the three dimensional structure to form either a ceramic core (34) or a complete ceramic casting vessel (38). If just a ceramic core is formed, a wax pattern is formed around the ceramic core and an exterior ceramic shell (38) is formed around the wax pattern by a dipping process prior to the removal of the fugitive material and wax. An alloy component having the desired interior passageway is cast into the casting vessel after the fugitive material is removed.
    Type: Application
    Filed: April 15, 2011
    Publication date: December 1, 2011
    Inventors: Ching-Pang Lee, Gary B. Merrill, Andrew J. Burns
  • Discreetly Defined Porous Wall Structure for Transpirational Cooling
    Publication number: 20110262695
    Abstract: A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).
    Type: Application
    Filed: April 22, 2010
    Publication date: October 27, 2011
    Inventors: Ching-Pang Lee, Chander Prakash, Gary B. Merrill, Andreas Heselhaus, Andrew J. Burns
  • Airfoil Having Built-Up Surface with Embedded Cooling Passage
    Publication number: 20110223005
    Abstract: A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.
    Type: Application
    Filed: March 15, 2010
    Publication date: September 15, 2011
    Inventors: Ching-Pang Lee, Mrinal Munshi, Gm S. Azad, Jae Y. Um
  • AIRFOIL INCORPORATING TAPERED COOLING STRUCTURES DEFINING COOLING PASSAGEWAYS
    Publication number: 20110171023
    Abstract: A gas turbine engine (10) and an airfoil (50) for use therein, the airfoil (50) having a structure (128) containing cooling passageways (110, 120) extending between a chamber (100) and a series of apertures (78) positioned along the trailing edge (72) through which cooling fluid (144) received from the chamber (100) exits the airfoil (50), wherein the structure (128) is characterized by a variable thickness (t) between the pressure and suction sidewalls (74, 76) of the airfoil as a function of position along the cooling passageways (110, 120) such that each in a plurality of cooling passageways are characterized by a cross sectional flow area (170, 174) which decreases as a function of distance from the chamber (100).
    Type: Application
    Filed: October 20, 2010
    Publication date: July 14, 2011
    Inventors: Ching-Pang Lee, John J. Marra
  • Methods and apparatus for assembling turbine engines
    Patent number: 7976274
    Abstract: A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.
    Type: Grant
    Filed: December 8, 2005
    Date of Patent: July 12, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Joseph M. Guentert, Wenfeng Lu, Mitchell E. Iles
  • Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall
    Publication number: 20110150653
    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: Application
    Filed: December 17, 2009
    Publication date: June 23, 2011
    Inventors: Matthew D. Montgomery, Ching-Pang Lee, Chander Prakash
  • Methods and systems for forming cooling holes having circular inlets and non-circular outlets
    Patent number: 7964087
    Abstract: A method for forming a hole in an object is provided. The method includes forming a starter hole in the object, providing an electrochemical machining electrode that includes insulation that extends only partially around the electrode, and inserting the electrode into the starter hole to form a hole in the object that has an inlet defined by a first cross-sectional area and an outlet defined by a second cross-sectional area.
    Type: Grant
    Filed: March 22, 2007
    Date of Patent: June 21, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Bin Wei, Chen-Yu Jack Chou
  • Ceramic cores, methods of manufacture thereof and articles manufactured from the same
    Patent number: 7938168
    Abstract: Disclosed herein is an integral casting core including a solidified first portion of a ceramic core and a solidified second portion of the ceramic core; wherein the solidified second portion is disposed upon the solidified first portion of the ceramic core by laser consolidation. The first solidified portion of the integral casting core, is manufactured by a process which includes disposing a slurry including ceramic particles into a metal core die; wherein an internal volume of the metal core die has a geometry equivalent to a portion of the geometry of the integral casting core; curing the slurry to form a cured first portion of the ceramic core; and firing the cured first portion of the ceramic core to form a solidified first portion of the ceramic core.
    Type: Grant
    Filed: December 6, 2006
    Date of Patent: May 10, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Hsin-Pang Wang
  • Methods and systems for forming tapered cooling holes
    Patent number: 7938951
    Abstract: A method for forming holes in an object is provided. The method includes providing an electrochemical machining (ECM) electrode including a first section having insulation that circumscribes the first section, and a second section having insulation that extends only partially around the second section. The method also includes inserting the electrode into the object, such that in a single pass the electrode forms a hole that includes a first portion having a first cross-sectional area and a second portion having a second cross-sectional area.
    Type: Grant
    Filed: March 22, 2007
    Date of Patent: May 10, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Bin Wei, Chen-Yu Jack Chou
  • Dual interstage cooled engine
    Patent number: 7926289
    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.
    Type: Grant
    Filed: November 10, 2006
    Date of Patent: April 19, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
  • COMPOUND COOLING FLOW TURBULATOR FOR TURBINE COMPONENT
    Publication number: 20110033312
    Abstract: Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.
    Type: Application
    Filed: September 17, 2010
    Publication date: February 10, 2011
    Inventors: Ching-Pang Lee, Nan Jiang, John J. Marra, Ronald J. Rudolph
  • Compound nozzle cooled engine
    Patent number: 7870743
    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.
    Type: Grant
    Filed: November 10, 2006
    Date of Patent: January 18, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
  • Plasma enhanced rapidly expanded gas turbine engine transition duct
    Patent number: 7870719
    Abstract: A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes.
    Type: Grant
    Filed: October 13, 2006
    Date of Patent: January 18, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Aspi Rustom Wadia, David Glenn Cherry, Scott Michael Carson
  • Interstage cooled turbine engine
    Patent number: 7870742
    Abstract: A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.
    Type: Grant
    Filed: November 10, 2006
    Date of Patent: January 18, 2011
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
  • Reciprocal cooled turbine nozzle
    Patent number: 7836703
    Abstract: A turbine nozzle includes first and second vanes joined to outer and inner bands. The vanes include outboard sides defining outboard flow passages containing axial splitlines, and opposite inboard sides defining an inboard flow passage without axial splitline. The two vanes include different cooling circuits for differently cooling the inboard and outboard vane sides.
    Type: Grant
    Filed: June 20, 2007
    Date of Patent: November 23, 2010
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Robert Joseph Orlando
  • Method of Operating a Compressor
    Publication number: 20100284780
    Abstract: A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.
    Type: Application
    Filed: December 28, 2007
    Publication date: November 11, 2010
    Inventors: Aspi Rustom Wadia, David Scott Clark, Ching-Pang Lee, Andrew Breeze-Stringfellow, Gregory Scott McNulty
  • Plasma Clearance Controlled Compressor
    Publication number: 20100284795
    Abstract: A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.
    Type: Application
    Filed: December 28, 2007
    Publication date: November 11, 2010
    Inventors: Aspi Rustom Wadia, David Scott Clark, Ching-Pang Lee, Andrew Breeze-Stringfellow, Gregory Scott McNulty
  • SYSTEM AND METHOD FOR IMPROVED FILM COOLING
    Publication number: 20100282721
    Abstract: A system for producing at least one trench to improve film cooling in a sample is provided. The system includes at least one laser source outputting at least one pulsed laser beam. The pulsed laser beam includes a pulse duration including a range less than about 50 ?s, an energy per pulse having a range less than about 0.1 Joule, and a repetition rate with a range greater than about 1000 Hz. The system also includes a control subsystem coupled to the laser source, the control subsystem configured to synchronize a position of the sample with the pulse duration and energy level in order to selectively remove at least one of a thermal barrier coating, a bondcoat and a substrate metal in the sample to form the at least one trench.
    Type: Application
    Filed: May 5, 2009
    Publication date: November 11, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Ronald Scott Bunker, Wenwu Zhang, Wilbur Douglas Scheidt, Magdi Naim Azer, Marshall Gordon Jones, Ching-Pang Lee