Patents by Inventor Jan Christopher Schilling
Jan Christopher Schilling 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).
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Patent number: 11879349Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.Type: GrantFiled: December 30, 2021Date of Patent: January 23, 2024Assignee: General Electric CompanyInventors: Jan Christopher Schilling, Andrew John Breslin, Bryce Loring Heitman
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Publication number: 20230265769Abstract: A shroud hanger assembly (30) or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger (32), for example having a forward hanger portion (34) and a rearward hanger portion (36). A cavity (46) is formed between the parts; wherein a shroud (50) may be positioned which is formed of a low coefficient of thermal expansion material. The hanger (32) and shroud (50) may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud (50) is positioned within the hanger opening or cavity (46), one of the forward (34) and rearward hanger (36) portions may be press fit or otherwise connected into the other of the forward (34) and rearward (36) hanger portion.Type: ApplicationFiled: April 28, 2023Publication date: August 24, 2023Inventors: Jason David Shapiro, Jan Christopher Schilling, Michael John Franks
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Patent number: 11668207Abstract: A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.Type: GrantFiled: April 23, 2015Date of Patent: June 6, 2023Assignee: General Electric CompanyInventors: Jason David Shapiro, Jan Christopher Schilling, Michael John Franks
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Publication number: 20220120198Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.Type: ApplicationFiled: December 30, 2021Publication date: April 21, 2022Inventors: Jan Christopher Schilling, Andrew John Breslin, Bryce Loring Heitman
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Patent number: 11215081Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud, which is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.Type: GrantFiled: May 6, 2015Date of Patent: January 4, 2022Assignee: General Electric CompanyInventors: Jan Christopher Schilling, Andrew John Breslin, Bryce Loring Heitman
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Patent number: 10917036Abstract: An example device for mounting for a solar array may include a solar panel carrier configured to receive a solar array to form a panel assembly; a pivot configured to pivotably secure the solar panel carrier with respect to a support structure; and/or a restoring moment element operatively connected to the solar panel carrier and configured to exert a restoring moment on the solar panel carrier opposite in direction and approximately equal in magnitude to a gravitational moment of the panel assembly when the solar panel carrier is tilted to various angular positions. When the solar panel carrier is at a nominal angular position, a center of gravity of the panel assembly may be above and substantially vertically aligned with the pivot axis.Type: GrantFiled: April 23, 2020Date of Patent: February 9, 2021Inventor: Jan Christopher Schilling
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Publication number: 20200350853Abstract: An example device for mounting for a solar array may include a solar panel carrier configured to receive a solar array to form a panel assembly; a pivot configured to pivotably secure the solar panel carrier with respect to a support structure; and/or a restoring moment element operatively connected to the solar panel carrier and configured to exert a restoring moment on the solar panel carrier opposite in direction and approximately equal in magnitude to a gravitational moment of the panel assembly when the solar panel carrier is tilted to various angular positions. When the solar panel carrier is at a nominal angular position, a center of gravity of the panel assembly may be above and substantially vertically aligned with the pivot axis.Type: ApplicationFiled: April 23, 2020Publication date: November 5, 2020Inventor: Jan Christopher Schilling
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Publication number: 20190284958Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud, which is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.Type: ApplicationFiled: May 6, 2015Publication date: September 19, 2019Inventors: Jan Christopher Schilling, Andrew John Breslin, Bryce Loring Heitman
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Patent number: 10145382Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.Type: GrantFiled: December 30, 2015Date of Patent: December 4, 2018Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, Jan Christopher Schilling, Nitesh Jain, Abhijit Roy
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Patent number: 10138752Abstract: A gas turbine engine clearance control system includes a cooling air passage extending from a cooling air inlet port to a cooling air outlet port. The cooling air inlet port and outlet port are formed within an external surface of a compressor casing of a compressor and are also axially spaced on the external surface of the compressor casing. The cooling air passage extends from the cooling air inlet port radially inwardly to at least one of a flange joint, a radially outer surface of a compressor casing ring, and a radially outer surface of a connector case. The cooling air passage further extends aftward along the radially outer surfaces of the connector case and the compressor casing ring. The cooling air passage further extends radially outward to the cooling air outlet port.Type: GrantFiled: February 25, 2016Date of Patent: November 27, 2018Assignee: General Electric CompanyInventor: Jan Christopher Schilling
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Publication number: 20170248028Abstract: A gas turbine engine clearance control system includes a cooling air passage extending from a cooling air inlet port to a cooling air outlet port. The cooling air inlet port and outlet port are formed within an external surface of a compressor casing of a compressor and are also axially spaced on the external surface of the compressor casing. The cooling air passage extends from the cooling air inlet port radially inwardly to at least one of a flange joint, a radially outer surface of a compressor casing ring, and a radially outer surface of a connector case. The cooling air passage further extends aftward along the radially outer surfaces of the connector case and the compressor casing ring. The cooling air passage further extends radially outward to the cooling air outlet port.Type: ApplicationFiled: February 25, 2016Publication date: August 31, 2017Inventor: Jan Christopher Schilling
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Publication number: 20170198607Abstract: A shroud hanger assembly or shroud assembly is provided for dimensionally incompatible components wherein the assembly includes a multi-piece hanger, for example having a forward hanger portion and a rearward hanger portion. A cavity is formed between the parts; wherein a shroud may be positioned which is formed of a low coefficient of thermal expansion material. The hanger and shroud may be formed of the same material or differing materials in order to better match the thermal growth between the hanger and the shroud. When the shroud is positioned within the hanger opening or cavity, one of the forward and rearward hanger portions may be press fit or otherwise connected into the other of the forward and rearward hanger portion.Type: ApplicationFiled: April 23, 2015Publication date: July 13, 2017Inventors: Jason David SHAPIRO, Jan Christopher SCHILLING, Michael John FRANKS
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Publication number: 20170191493Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.Type: ApplicationFiled: December 30, 2015Publication date: July 6, 2017Inventors: Nicholas Joseph Kray, Jan Christopher Schilling, Nitesh Jain, Abhijit Roy
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Patent number: 9309772Abstract: A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the recess. The outer composite structure and the at least one composite section having a first density. The at least two insert sections having a second mass density, which is less than the first mass density. The composite outer structure and the alternating stack of at least one composite section and at least two insert sections together define an airfoil portion that meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections.Type: GrantFiled: February 22, 2013Date of Patent: April 12, 2016Assignee: General Electric CompanyInventors: Ross Ashely Spoonire, Wendy Wen-Ling Lin, Jan Christopher Schilling, Dong Jin Shim, Gregory Carl Gemeinhardt, Prakash Kashiram Jadhav
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Patent number: 8517661Abstract: A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions.Type: GrantFiled: January 22, 2007Date of Patent: August 27, 2013Assignee: General Electric CompanyInventor: Jan Christopher Schilling
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Patent number: 8459956Abstract: 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: GrantFiled: December 24, 2008Date of Patent: June 11, 2013Assignee: General Electric CompanyInventors: Vidhu Shekhar Pandey, Ching-Pang Lee, Jan Christopher Schilling, Aspi Rustom Wadia, Brian David Keith, Jeffrey Donald Clements
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Publication number: 20130101385Abstract: A variable vane assembly for a gas turbine engine having a casing, including: a variable vane including a platform and a vane stem extending outwardly from the platform; a bushing surrounding the vane stem; a lever for moving the vane between a closed position and an open position; and, a mechanism for incrementally rotating the bushing to a new circumferential position with respect to the vane stem as the vane is cycled each time between the closed and open positions.Type: ApplicationFiled: January 22, 2007Publication date: April 25, 2013Inventor: Jan Christopher Schilling
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Patent number: 8375695Abstract: An aircraft gas turbine engine includes a counter-rotatable generator driven by a turbine includes a generator stator and counter-rotatable radially inner pole and outer magnet rotors. A gearbox may be used for counter-rotating the pole and magnet rotors. Counter-rotatable first and second sets of booster stages may be co-rotatable with corresponding ones of the pole and magnet rotors. The generator and the gearbox may be disposed within a booster cavity or a tail cone of the engine. The magnet rotor, the pole rotor, and the stator may be concentric. A particular embodiment of generator includes the magnet rotor encircling the pole rotor, the pole rotor encircling the stator, a rotor air gap between the magnet and pole rotors, and a transformer air gap between the pole rotor and the stator. The counter-rotatable generator may be driven directly by a counter-rotatable turbine.Type: GrantFiled: June 30, 2009Date of Patent: February 19, 2013Assignee: General Electric CompanyInventors: Jan Christopher Schilling, Peter David Toot
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Patent number: 8205426Abstract: A method for assembling a turbine engine to facilitate reducing an operating temperature of a lubrication fluid during engine operation, the gas turbine engine including a fan assembly, a booster downstream from the fan assembly, and a splitter circumscribing the booster. The method includes coupling a radially inner wall and a radially outer wall at a leading edge to form a splitter body, and coupling an inner support structure within the splitter body such that a cooling circuit is defined between at least a portion of the inner support structure and the inner and outer walls, said cooling circuit configured to circulate lubrication fluid therethrough such that as a temperature of the lubrication fluid is reduced and a temperature of at least a portion of the inner and outer walls is increased.Type: GrantFiled: July 31, 2006Date of Patent: June 26, 2012Assignee: General Electric CompanyInventor: Jan Christopher Schilling
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Patent number: 8191352Abstract: A counter-rotatable low pressure turbine includes counter-rotatable outer and inner drum rotors. The outer drum rotor is connected to a sole shaft for transmitting torque and power out of the low pressure turbine. Low pressure outer drum turbine blade rows extend radially inwardly from an outer shell of the outer drum rotor. Low pressure inner drum turbine blade rows extend radially outwardly from the low pressure inner drum rotor. The outer drum turbine blade rows are interdigitated with the inner drum turbine blade rows. The drum rotors are geared together through an epicyclic gearbox for transmitting all the torque and power produced by the drum rotors to the shaft. The gearbox may be located aft of the drum rotors. A differential thrust bearing is disposed between the drum rotors. A single stage fan section of an engine is connected to the turbine by the shaft.Type: GrantFiled: December 19, 2008Date of Patent: June 5, 2012Assignee: General Electric CompanyInventor: Jan Christopher Schilling