Patents by Inventor John Giaimo
John Giaimo 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: 11248478Abstract: An exhaust apparatus for a gas turbine includes an annular duct with struts extending from an outer duct-wall to an inner duct-wall of the annular duct. Each strut is encapsulated in a respective strut shield. An interface of the strut shield with a respective duct-wall includes a collar extending along a partial length of the perimeter of the strut shield at the respective interface. The collar includes a first section extending radially and aligned with the strut shield, and a second section oriented at an angle to the first section and aligned with the respective duct-wall. The first section is attached to the strut shield along a first joint and the second section is attached to the respective duct-wall along a second joint. An intersection of the first and second sections is formed by a smooth curve defined by a radius configured to distribute stresses at the respective interface.Type: GrantFiled: June 7, 2019Date of Patent: February 15, 2022Assignee: Siemens AktiengesellschaftInventors: Shashikant Maurya, John Giaimo, Ryan David Wiebe, Keith L. Nickols, Andre Correa
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Publication number: 20210231021Abstract: An exhaust apparatus for a gas turbine includes an annular duct with struts extending from an outer duct-wall to an inner duct-wall of the annular duct. Each strut is encapsulated in a respective strut shield. An interface of the strut shield with a respective duct-wall includes a collar extending along a partial length of the perimeter of the strut shield at the respective interface. The collar includes a first section extending radially and aligned with the strut shield, and a second section oriented at an angle to the first section and aligned with the respective duct-wall. The first section is attached to the strut shield along a first joint and the second section is attached to the respective duct-wall along a second joint. An intersection of the first and second sections is formed by a smooth curve defined by a radius configured to distribute stresses at the respective interface.Type: ApplicationFiled: June 7, 2019Publication date: July 29, 2021Inventors: Shashikant Maurya, John Giaimo, Ryan David Wiebe, Keith L. Nickols, Andre Correa
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Patent number: 10077676Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A trailing edge full span flap is removable secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface where the full span flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: GrantFiled: November 19, 2015Date of Patent: September 18, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Yevgeniy P. Shteyman, John Giaimo, Randy Tindell
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Patent number: 9988931Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: GrantFiled: April 17, 2015Date of Patent: June 5, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, John A. Orosa
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Patent number: 9880059Abstract: A thermocouple probe assembly for monitoring the temperature of an exhaust gas flow at an output of a gas turbine engine. The probe assembly includes a plenum pipe positioned within an opening extending through an outer casing wall and a plenum plate of the engine, where an air gap is provided between the casing wall and the plate. The plenum pipe is rigidly secured to the plenum plate and resiliently mounted to the casing wall so that the plenum pipe is operable to slide relative to the wall. The probe assembly further includes a diffuser liner boss rigidly secured to an outer liner of an exhaust gas diffuser in the gas turbine engine, where the liner boss includes a central bore, and where the shaft of the thermocouple probe extends through the central bore in the liner boss so that the sensor is positioned within the exhaust gas diffuser.Type: GrantFiled: June 8, 2015Date of Patent: January 30, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Gerald A. Myers, John Giaimo, James Buttice, Stephen Brooks
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Patent number: 9840937Abstract: Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.Type: GrantFiled: January 14, 2015Date of Patent: December 12, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, Thomas Heylmun
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Patent number: 9695713Abstract: Disclosed are a system for damping vibrations of a gas turbine exhaust and a method to damp vibrations of a gas turbine exhaust. The system includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer clamped by a plurality of studs.Type: GrantFiled: February 11, 2015Date of Patent: July 4, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Daniel M. Eshak, Yevgeniy P. Shteyman, John Giaimo, George J. Obranic, Jr., Sudeep Bosu
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Patent number: 9617873Abstract: Disclosed are a casing arrangement and a method to reduce critical panel mode response in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A plurality of stiffening ribs are coupled to a surface of the inner flow path which effectively increases the stiffness reducing the critical panel mode response.Type: GrantFiled: January 14, 2015Date of Patent: April 11, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Daniel M. Eshak, John Giaimo, Thomas Heylmun, Yevgeniy P. Shteyman
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Publication number: 20160356174Abstract: A thermocouple probe assembly for monitoring the temperature of an exhaust gas flow at an output of a gas turbine engine. The probe assembly includes a plenum pipe positioned within an opening extending through an outer casing wall and a plenum plate of the engine, where an air gap is provided between the casing wall and the plate. The plenum pipe is rigidly secured to the plenum plate and resiliently mounted to the casing wall so that the plenum pipe is operable to slide relative to the wall. The probe assembly further includes a diffuser liner boss rigidly secured to an outer liner of an exhaust gas diffuser in the gas turbine engine, where the liner boss includes a central bore, and where the shaft of the thermocouple probe extends through the central bore in the liner boss so that the sensor is positioned within the exhaust gas diffuser.Type: ApplicationFiled: June 8, 2015Publication date: December 8, 2016Inventors: Gerald A. Myers, John Giaimo, James Buttice, Stephen Brooks
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Publication number: 20160208642Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A trailing edge full span flap is removable secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface where the full span flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: ApplicationFiled: November 19, 2015Publication date: July 21, 2016Inventors: Yevgeniy P. Shteyman, John Giaimo, Randy Tindell
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Publication number: 20160201506Abstract: Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.Type: ApplicationFiled: January 14, 2015Publication date: July 14, 2016Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, Thomas Heylmun
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Publication number: 20160076396Abstract: Disclosed are a casing arrangement and a method to reduce critical panel mode response in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A plurality of stiffening ribs are coupled to a surface of the inner flow path which effectively increases the stiffness reducing the critical panel mode response.Type: ApplicationFiled: January 14, 2015Publication date: March 17, 2016Inventors: Daniel M. Eshak, John Giaimo, Thomas Heylmun, Yevgeniy P. Shteyman
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Publication number: 20160076398Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: ApplicationFiled: April 17, 2015Publication date: March 17, 2016Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, John A. Orosa
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Publication number: 20160076397Abstract: Disclosed are a system for damping vibrations of a gas turbine exhaust and a method to damp vibrations of a gas turbine exhaust. The system includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer clamped by a plurality of studs.Type: ApplicationFiled: February 11, 2015Publication date: March 17, 2016Inventors: Daniel M. Eshak, Yevgeniy P. Shteyman, John Giaimo, George J. Obranic, JR., Sudeep Bosu
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Patent number: 7901178Abstract: A variable vane mechanism comprises a variable vane, an inner diameter shroud and a synchronizing mechanism. The variable vane comprises a vane body, an inner diameter trunnion extending radially inwardly from the vane body, and a button connected to the inner diameter trunnion and displaced radially inwardly from the inner diameter trunnion. The shroud comprises a shroud body, a socket extending into the shroud body for receiving the inner diameter trunnion, a flange extending into the socket for engaging the button and inhibiting radial movement of the variable vane, and a synchronizing channel extending through the inner diameter shroud aft of the socket so as to be bounded by the shroud body and opening to the socket. The synchronizing mechanism is disposed inside the synchronizing channel and connects to the inner diameter trunnion.Type: GrantFiled: March 18, 2009Date of Patent: March 8, 2011Assignee: United Technologies CorporationInventors: John A. Giaimo, John P. Tirone, III
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Patent number: 7753647Abstract: An inner diameter vane shroud for use in a gas turbine engine is comprised of lightweight cast forward and aft shroud components. The forward and aft shroud components are made with an investment casting technique that creates a hollow cavity that runs in a circumferential direction through each component. The forward and aft shroud components are matable to form sockets that receive inner diameter ends of variable stator vanes.Type: GrantFiled: July 20, 2005Date of Patent: July 13, 2010Assignee: United Technologies CorporationInventors: John A. Giaimo, John P. Tirone, III
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Patent number: 7690889Abstract: A variable vane actuation mechanism is comprised of a first drive vane arm and a second drive vane arm for driving a first variable vane array and a second variable vane array, respectively, of a stator vane section of a gas turbine engine. The first drive vane arm and second drive vane arm are connected to each other at a first end by a linkage. The first drive vane arm and second drive vane arm are connected at a second end to a first drive vane and a second drive vane, respectively, of the first and second variable vane arrays. The first drive vane arm and second drive vane arm respond in unison to a single actuation source connected to one of the first drive vane arm and second drive vane arm.Type: GrantFiled: July 20, 2005Date of Patent: April 6, 2010Assignee: United Technologies CorporationInventors: John A. Giaimo, John P. Tirone, III
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Patent number: 7665959Abstract: An inner diameter vane shroud of a variable vane assembly accommodates a synchronization mechanism for coordinating rotation of an array of variable vanes. The inner diameter vane shroud has a gear track that runs circumferentially through the vane shroud. An array of variable vanes is rotatably mounted in the vane shroud at an inner end. Each vane has a gear pinion at its inner end, which interfaces with the gear track. As one of the individual variable vanes is rotated by an actuation source, the other variable vanes of the variable vane array are rotated a like amount by the rack and pinion gear interface.Type: GrantFiled: July 20, 2005Date of Patent: February 23, 2010Assignee: United Technologies CorporationInventors: John A. Giaimo, John P. Tirone, III
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Patent number: 7628579Abstract: An inner diameter vane shroud accommodates a mechanism for synchronously rotating an away of variable vanes. Particularly, the inner diameter vane shroud has a gear channel that runs circumferentially through the vane shroud. An array of variable vanes is rotatably mounted in the vane shroud at an inner end. The variable vanes comprise vane gears at their inner end, which are rotatable in the gear channel. Disposed between the vane gears of the variable vanes are idler gears. As one of the individual variable vanes is rotated by an actuation source, the other variable vanes of the variable vane away are rotated a like amount by the vane gears and idler gears.Type: GrantFiled: July 20, 2005Date of Patent: December 8, 2009Assignee: United Technologies CorporationInventors: John A. Giaimo, John P. Tirone, III
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Publication number: 20090285673Abstract: A variable vane mechanism comprises a variable vane, an inner diameter shroud and a synchronizing mechanism. The variable vane comprises a vane body, an inner diameter trunnion extending radially inwardly from the vane body, and a button connected to the inner diameter trunnion and displaced radially inwardly from the inner diameter trunnion. The shroud comprises a shroud body, a socket extending into the shroud body for receiving the inner diameter trunnion, a flange extending into the socket for engaging the button and inhibiting radial movement of the variable vane, and a synchronizing channel extending through the inner diameter shroud aft of the socket so as to be bounded by the shroud body and opening to the socket. The synchronizing mechanism is disposed inside the synchronizing channel and connects to the inner diameter trunnion.Type: ApplicationFiled: March 18, 2009Publication date: November 19, 2009Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: John A. Giaimo, John P. Tirone, III