Patents by Inventor William W Pankey

William W Pankey 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).

  • Patent number: 10024180
    Abstract: An arrangement for a gas turbine engine includes a combustor for producing a working medium by combustion of a mixture of fuel and an oxidant, a turbine section comprising a stationary vane carrier on which a first row of stationary vanes is arranged, and a transition duct for leading the working medium from the combustor to the turbine section. The transition duct has a forward end that adjoins the combustor and an aft end that adjoins the stationary vane carrier. The transition duct has a transition duct axis extending from the forward end to the aft end along a straight line. The transition duct axis is normal to a vane axis of a stationary vane in the first row of stationary vanes.
    Type: Grant
    Filed: November 20, 2014
    Date of Patent: July 17, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Paul G. Hicks, William W. Pankey
  • Publication number: 20180023404
    Abstract: A ring segment system (100) for a gas turbine engine (10) is disclosed. The ring segment system (100) may be formed from ring segments (50) that circumferentially surround a rotor assembly (40). The ring segments (50) may each include a carrier portion (34) that is coupled to a vane carrier (28), and a heat shielding portion (38) that is detachably coupled to the carrier portion (34). The detachable coupling may allow the heat shielding portion (38) to be uncoupled from the carrier portion (34) and removed from the gas turbine engine (10) axially. The ring segments (50) may further include cooling fluid supply channels (72) that allow cooling fluid to flow from a radially outward facing backside (42) of the ring segments (50) to a radially inward facing front side (46). Additionally, the ring segments (50) may also include ingestion prevention channels (76) that allow cooling fluid to create a barrier over the gap (80) between the ring segments (50) and the adjacent vane (18).
    Type: Application
    Filed: February 16, 2015
    Publication date: January 25, 2018
    Inventors: Marco Claudio Pio Brunelli, Sameer Ahmed Khan, Matthew J. LaGrow, William W. Pankey, Walter H. Marussich, Beatriz Suarez-Crosse, Kenneth K. Landis
  • Patent number: 9709276
    Abstract: In a method for installation of a transition duct in a gas turbine engine, a guide structure is positioned that extends in an inclined direction with respect to a gas turbine axis. At least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine. The transition duct is engaged with the guide structure such that the transition duct is movable along the guide structure. Motion is imparted to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: July 18, 2017
    Assignee: Siemens Energy, Inc.
    Inventor: William W. Pankey
  • Patent number: 9677767
    Abstract: A combustion turbine engine combustor section includes a plurality of annularly arrayed combustors housed within paired combustor portals of a combustor casing. Each combustor portal has a corresponding top hat cover having a peripheral flange. The paired combustor portals are formed in combustor housings having a figure eight-shaped sleeve wall planform. The paired adjoining combustor portals share a common Siamesed portion of the sleeve wall. A combustor portal mating surface is formed on an axial distal end of the sleeve wall, having a figure eight planform and defining a first array of fastener receiving apertures. A top hat cover retention bracket assembly having a composite planform conforming to the combustor portal mating surface planform and a second array of apertures that conform to the first array pattern apertures, is placed over the peripheral flanges of the paired combustor top hat covers and secured by top hat cover fasteners.
    Type: Grant
    Filed: May 29, 2014
    Date of Patent: June 13, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Andrew Carlson, William W. Pankey
  • Patent number: 9593853
    Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.
    Type: Grant
    Filed: February 20, 2014
    Date of Patent: March 14, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Matthew D. Montgomery, Richard C. Charron, Gary D. Snyder, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
  • Patent number: 9574460
    Abstract: A support arrangement (10) for a transition piece (12) of a gas turbine engine (14). The support arrangement includes a mounting bracket (16) for the transition piece and a pin (18) supporting the mounting bracket in an interior (20) of the gas turbine engine and extending through an opening (22) in a casing (24) to an exterior (26) of the gas turbine engine. The support arrangement further includes a spherical washer (28, 38) positioned between the pin and either the mounting bracket or the casing.
    Type: Grant
    Filed: October 30, 2014
    Date of Patent: February 21, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Andrew Carlson, William W. Pankey
  • Publication number: 20160238252
    Abstract: A gas turbine engine (GTE) including a thermally expandable transition piece is disclosed. The GTE includes at least a combustor section having a combustor sleeve, also known as top hat, and a transition piece. The transition piece includes a transition duct having an upstream end, a downstream end, a outer surface and a forward end face. The transition piece also includes one or more struts selectively attached to the transition duct proximate to the upstream end. The strut extends radially upward from the outer surface, and axially outward beyond the forward end face for interfacing the strut with at least a portion of the combustor sleeve.
    Type: Application
    Filed: February 17, 2015
    Publication date: August 18, 2016
    Inventor: William W. Pankey
  • Patent number: 9404421
    Abstract: A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.
    Type: Grant
    Filed: January 23, 2014
    Date of Patent: August 2, 2016
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard C. Charron, William W. Pankey, Clinton A. Mayer, Benjamin G Hettinger
  • Publication number: 20160215698
    Abstract: A support arrangement (10) for a transition piece (12) of a gas turbine engine (14). The support arrangement includes a mounting bracket (16) for the transition piece and a pin (18) supporting the mounting bracket in an interior (20) of the gas turbine engine and extending through an opening (22) in a casing (24) to an exterior (26) of the as turbine engine.
    Type: Application
    Filed: October 30, 2014
    Publication date: July 28, 2016
    Inventors: Andrew Carlson, William W. Pankey
  • Patent number: 9359955
    Abstract: An apparatus for supporting an aft portion of a transition duct in a gas turbine engine includes a transition aft frame that engages with an annular shaped stator component disposed in a turbine section of the gas turbine engine. The transition aft frame includes radially inner and outer panels and circumferentially spaced first and second side panels connecting the inner and outer panels. A forward face of the stator component includes first and second connection points circumferentially spaced apart. The transition aft frame includes first and second attachment structures that respectively engage with the first and second connection points when the transition duct is aligned axially with the stator component. The first and second attachment structures are spaced apart in a manner effective to transfer moment load from the first and second attachment structures to the first and second side panels respectively.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: June 7, 2016
    Assignee: Siemens Energy, Inc.
    Inventor: William W. Pankey
  • Publication number: 20160146026
    Abstract: An arrangement for a gas turbine engine includes a combustor for producing a working medium by combustion of a mixture of fuel and an oxidant, a turbine section comprising a stationary vane carrier on which a first row of stationary vanes is arranged, and a transition duct for leading the working medium from the combustor to the turbine section. The transition duct has a forward end that adjoins the combustor and an aft end that adjoins the stationary vane carrier. The transition duct has a transition duct axis extending from the forward end to the aft end along a straight line. The transition duct axis is normal to a vane axis of a stationary vane in the first row of stationary vanes.
    Type: Application
    Filed: November 20, 2014
    Publication date: May 26, 2016
    Inventors: Paul G. Hicks, William W. Pankey
  • Patent number: 9322335
    Abstract: An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: April 26, 2016
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard C. Charron, William W. Pankey
  • Publication number: 20160061449
    Abstract: In a method for installation of a transition duct in a gas turbine engine, a guide structure is positioned that extends in an inclined direction with respect to a gas turbine axis. At least a portion of the guide structure is disposed between a turbine section and a combustor section of the gas turbine engine. The transition duct is engaged with the guide structure such that the transition duct is movable along the guide structure. Motion is imparted to the transition duct along the guide structure in a forward-to-aft direction, to move the transition duct to an installed position in which an aft end of the transition duct is aligned for attachment to a forward face of a stator component of the turbine section.
    Type: Application
    Filed: August 28, 2014
    Publication date: March 3, 2016
    Inventor: William W. Pankey
  • Publication number: 20160061450
    Abstract: An apparatus for supporting an aft portion of a transition duct in a gas turbine engine includes a transition aft frame that engages with an annular shaped stator component disposed in a turbine section of the gas turbine engine. The transition aft frame includes radially inner and outer panels and circumferentially spaced first and second side panels connecting the inner and outer panels. A forward face of the stator component includes first and second connection points circumferentially spaced apart. The transition aft frame includes first and second attachment structures that respectively engage with the first and second connection points when the transition duct is aligned axially with the stator component. The first and second attachment structures are spaced apart in a manner effective to transfer moment load from the first and second attachment structures to the first and second side panels respectively.
    Type: Application
    Filed: August 28, 2014
    Publication date: March 3, 2016
    Inventor: William W. Pankey
  • Publication number: 20150345796
    Abstract: A combustion turbine engine combustor section includes a plurality of annularly arrayed combustors housed within paired combustor portals of a combustor casing. Each combustor portal has a corresponding top hat cover having a peripheral flange. The paired combustor portals are formed in combustor housings having a figure eight-shaped sleeve wall planform. The paired adjoining combustor portals share a common Siamesed portion of the sleeve wall. A combustor portal mating surface is formed on an axial distal end of the sleeve wall, having a figure eight planform and defining a first array of fastener receiving apertures. A top hat cover retention bracket assembly having a composite planform conforming to the combustor portal mating surface planform and a second array of apertures that conform to the first array pattern apertures, is placed over the peripheral flanges of the paired combustor top hat covers and secured by top hat cover fasteners.
    Type: Application
    Filed: May 29, 2014
    Publication date: December 3, 2015
    Applicant: SIEMENS ENERGY, INC.
    Inventors: Andrew Carlson, William W. Pankey
  • Publication number: 20150233582
    Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.
    Type: Application
    Filed: February 20, 2014
    Publication date: August 20, 2015
    Applicant: SIEMENS ENERGY, INC.
    Inventors: Matthew D. Montgomery, Richard C. Charron, Gary D. Snyder, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
  • Publication number: 20150204243
    Abstract: A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.
    Type: Application
    Filed: January 23, 2014
    Publication date: July 23, 2015
    Inventors: Richard C. Charron, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
  • Patent number: 9017012
    Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes a cooling fluid supply trench having an open top portion and extending radially inwardly from a central recessed portion of the panel. The cooling system further includes a plurality of cooling fluid passages extending from the cooling fluid supply trench to a leading edge and/or a trailing edge of the panel. The cooling fluid passages receive cooling fluid from the cooling fluid supply trench, wherein the cooling fluid provides convective cooling to the panel as it passes through the cooling fluid passages.
    Type: Grant
    Filed: October 26, 2011
    Date of Patent: April 28, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Marco Claudio Pio Brunelli, Sameer A. Khan, Kenneth K. Landis, Walter H. Marussich, Nicholas F. Martin, Beatriz Suarez-Crosse, William W. Pankey
  • Publication number: 20140260317
    Abstract: An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Inventors: Richard C. Charron, William W. Pankey
  • Patent number: 8534996
    Abstract: A compressor stator vane and rotor blade tip clearance control assembly in which a plurality of stator vane segments each with vanes extending inward are connected to an annular sync ring through eccentric cranks so that circumferential movement of the sync ring will produce radial displacement of the vane segments and control the clearance between the blade tips. An actuator piston is rigidly fixed to the sync ring and forms an actuator chamber with stationary actuator housing. Bleed off pressure from one of the compressor stages is used to move the actuator piston, which moves the sync ring to radially displace the vane segments.
    Type: Grant
    Filed: September 14, 2009
    Date of Patent: September 17, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: William W. Pankey, Jack W. Wilson, Jr.