Patents by Inventor John A. Orosa
John A. Orosa 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: 11306594Abstract: Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: February 25, 2021Date of Patent: April 19, 2022Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.Inventors: Matthew D. Montgomery, William Brian Diggs, Jaewook Song, Jerry W. Wood, John Orosa
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Patent number: 10641177Abstract: A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.Type: GrantFiled: March 23, 2016Date of Patent: May 5, 2020Assignee: Florida Turbine Technologies, Inc.Inventors: Joseph D. Brostmeyer, Russell B. Jones, Justin T. Cejka, John A. Orosa, John E. Ryznic
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Patent number: 10533610Abstract: An aero gas turbine engine with a fan stage and a bearing rotatably supporting the fan stage, where the bearing is cooled by passing cooling air through the bearing, and the spent bearing cooling air is re-injected into the air flow path at a location where the effect is minimalized. The location is just downstream from a leading edge of a stator vane and along a pressure side surface of the vane. A fine mist of oil can be discharged into the bearing cooling air to also lubricate the bearing, where both the oil and the spent cooling air is reintroduced into the air flow path.Type: GrantFiled: May 1, 2018Date of Patent: January 14, 2020Assignee: Florida Turbine Technologies, Inc.Inventors: Ross H Peterson, John A Orosa, Robert A Ress, Jr.
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Patent number: 10473118Abstract: A controlled convergence compressor flowpath (10) configured to better distribute the limited flowpath (10) convergence within compressors (12) in turbine engines (14) is disclosed. The compressor (12) may have a flowpath (10) defined by circumferentially extending inner and outer boundaries (16, 18) that having portions in which the rate of convergence changes to better distribute fluid flow therethrough. The rate of convergence may increase at surfaces (20, 22) adjacent to roots (24) of airfoils (26) and decrease near airfoil tips (68) and in the axial gaps (28) between airfoil rows (30). In at least one embodiment, the compressor flowpath (10) between leading and trailing edges (44, 46) of a first compressor blade (42) may increase convergence moving downstream to a trailing edge (46) of the first compressor blade (42) due to increased convergence of the inner compressor surface (22).Type: GrantFiled: August 29, 2014Date of Patent: November 12, 2019Assignee: SIEMENS AKTIENGESELLSCHAFTInventor: John A. Orosa
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Publication number: 20190145314Abstract: An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.Type: ApplicationFiled: April 24, 2017Publication date: May 16, 2019Inventors: John A OROSA, Joseph D BROSTMEYER, Russell B JONES, Justin T CEJKA
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Patent number: 10174763Abstract: A variable pitch fan assembly for an aero gas turbine engine that includes a row of fixed pitch blades in a core stream flow and a row of variable pitch blades in a bypass stream flow, and where a sync ring with a number of hydraulic actuators within a flow splitter of the fan stage is used to vary a pitch of each of the bypass stream flow blades. Hydraulic fluid lines pass through the shaft and through the fixed pitch fan blades into the hydraulic actuators to move the sync ring and vary a pitch of the variable pitch bypass flow fan blades.Type: GrantFiled: August 2, 2018Date of Patent: January 8, 2019Assignee: FLORIDA TURBINE TECHNOLOGIES, INCInventors: John A Orosa, Robert A Ress, Jr.
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Publication number: 20180245512Abstract: An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.Type: ApplicationFiled: February 28, 2017Publication date: August 30, 2018Inventors: Joseph D. Brostmeyer, Russell B. Jones, John A. Orosa
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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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Publication number: 20180066586Abstract: A process for retrofitting an electric power plant that uses two 60 Hertz large frame heavy duty industrial gas turbine engines to drive electric generators and produce electricity, where each of the two industrial engines can produce up to 350 MW of output power. The process replaces the two 350 MW industrial engines with one twin spool industrial gas turbine engine that is capable of producing at least 700 MW of output power. Thus, two prior art industrial engines can be replaced with one industrial engine that can produce power equal to the two prior art industrial engines.Type: ApplicationFiled: March 23, 2016Publication date: March 8, 2018Inventors: Joseph D. BROSTMEYER, Russell B. JONES, Justin T. CEJKA, John A. OROSA, John E. Ryznic
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Patent number: 9897413Abstract: A process for starting an engine in a cruise missile that is launched from an aircraft during flight, where the cruise missile is ejected from a weapons bay of the aircraft and towed using a tow line, where the cruise missile engine is started while being towed and then released after the engine has started. The tow line is a low radar signature line and the weapons bay door is closed quickly after the cruise missile has been ejected to reduce radar signatures.Type: GrantFiled: July 22, 2016Date of Patent: February 20, 2018Assignee: Florida Turbine Technologies, Inc.Inventor: John A Orosa
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Patent number: 9810099Abstract: An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.Type: GrantFiled: June 29, 2015Date of Patent: November 7, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Ali Akturk, Jose L. Rodriguez, David L. Wasdell, John A. Orosa, Matthew D. Montgomery
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Publication number: 20170204878Abstract: A controlled convergence compressor flowpath (10) configured to better distribute the limited flowpath (10) convergence within compressors (12) in turbine engines (14) is disclosed. The compressor (12) may have a flowpath (10) defined by circumferentially extending inner and outer boundaries (16, 18) that having portions in which the rate of convergence changes to better distribute fluid flow therethrough. The rate of convergence may increase at surfaces (20, 22) adjacent to roots (24) of airfoils (26) and decrease near airfoil tips (68) and in the axial gaps (28) between airfoil rows (30). In at least one embodiment, the compressor flowpath (10) between leading and trailing edges (44, 46) of a first compressor blade (42) may increase convergence moving downstream to a trailing edge (46) of the first compressor blade (42) due to increased convergence of the inner compressor surface (22).Type: ApplicationFiled: August 29, 2014Publication date: July 20, 2017Inventor: John A. Orosa
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Patent number: 9644497Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.Type: GrantFiled: November 22, 2013Date of Patent: May 9, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Matthew R. Porter, Lijuan Han, Matthew J. Delisa, III
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Patent number: 9598981Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.Type: GrantFiled: November 22, 2013Date of Patent: March 21, 2017Assignee: Siemens Energy, Inc.Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Lijuan Han, Matthew J. Delisa, III, Daniel F. Riveros
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Patent number: 9587519Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.Type: GrantFiled: November 22, 2013Date of Patent: March 7, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Matthew R. Porter, Lijuan Han, Matthew J. Delisa, III, Daniel F. Riveros
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Publication number: 20170022834Abstract: A gas turbine engine with an air cooled turbine part in which spent cooling air for the turbine part is discharged into the combustor instead of into the hot gas stream of the turbine in order to increase efficiency of the engine. Turbine rotor blades and stator vanes are cooled. The spent cooling air is passed into a diffuser located between the HPC outlet and the combustor inlet where the spent cooling air is discharged along the inner and outer endwalls of the diffuser in directions substantially parallel to the inner and outer diffuser endwalls and at a greater velocity in order to energize the diffuser endwall boundary layers so that they can sustain higher diffusion rates and levels.Type: ApplicationFiled: May 4, 2016Publication date: January 26, 2017Inventor: John A. Orosa
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Publication number: 20170022905Abstract: An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.Type: ApplicationFiled: April 25, 2016Publication date: January 26, 2017Inventors: John A. Orosa, Joseph D. Brostmeyer, Justin T. Cejka, Russell B. Jones
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Publication number: 20170022901Abstract: A gas turbine engine with an air cooled turbine component in which spent cooling air from the turbine component is routed through a rotor disk and into a static vaned diffuser on a static part of the engine so that the spent cooling air can be discharged into the combustor instead of into the turbine hot gas stream. The static vaned diffuser includes de-swirling vanes that de-swirl the flow coming off of the rotor and then diffuses the de-swirled air to increase a pressure for discharge into the combustor.Type: ApplicationFiled: April 18, 2016Publication date: January 26, 2017Inventor: John A. Orosa
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Patent number: 9540956Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.Type: GrantFiled: November 22, 2013Date of Patent: January 10, 2017Assignee: Siemens Energy, Inc.Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Matthew R. Porter, Lijuan Han, Matthew J. Delisa, III, Daniel F. Riveros
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Publication number: 20160376929Abstract: An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.Type: ApplicationFiled: June 29, 2015Publication date: December 29, 2016Inventors: Ali Akturk, Jose L. Rodriguez, David L. Wasdell, John A. Orosa, Matthew D. Montgomery