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).

  • Patent number: 11306594
    Abstract: 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: Grant
    Filed: February 25, 2021
    Date of Patent: April 19, 2022
    Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
    Inventors: Matthew D. Montgomery, William Brian Diggs, Jaewook Song, Jerry W. Wood, John Orosa
  • Patent number: 10641177
    Abstract: 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: Grant
    Filed: March 23, 2016
    Date of Patent: May 5, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Joseph D. Brostmeyer, Russell B. Jones, Justin T. Cejka, John A. Orosa, John E. Ryznic
  • Patent number: 10533610
    Abstract: 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: Grant
    Filed: May 1, 2018
    Date of Patent: January 14, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Ross H Peterson, John A Orosa, Robert A Ress, Jr.
  • Patent number: 10473118
    Abstract: 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: Grant
    Filed: August 29, 2014
    Date of Patent: November 12, 2019
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: John A. Orosa
  • Publication number: 20190145314
    Abstract: 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: Application
    Filed: April 24, 2017
    Publication date: May 16, 2019
    Inventors: John A OROSA, Joseph D BROSTMEYER, Russell B JONES, Justin T CEJKA
  • Patent number: 10174763
    Abstract: 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: Grant
    Filed: August 2, 2018
    Date of Patent: January 8, 2019
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC
    Inventors: John A Orosa, Robert A Ress, Jr.
  • Publication number: 20180245512
    Abstract: 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: Application
    Filed: February 28, 2017
    Publication date: August 30, 2018
    Inventors: Joseph D. Brostmeyer, Russell B. Jones, John A. Orosa
  • Patent number: 9988931
    Abstract: 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: Grant
    Filed: April 17, 2015
    Date of Patent: June 5, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, John A. Orosa
  • Publication number: 20180066586
    Abstract: 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: Application
    Filed: March 23, 2016
    Publication date: March 8, 2018
    Inventors: Joseph D. BROSTMEYER, Russell B. JONES, Justin T. CEJKA, John A. OROSA, John E. Ryznic
  • Patent number: 9897413
    Abstract: 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: Grant
    Filed: July 22, 2016
    Date of Patent: February 20, 2018
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: John A Orosa
  • Patent number: 9810099
    Abstract: 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: Grant
    Filed: June 29, 2015
    Date of Patent: November 7, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Ali Akturk, Jose L. Rodriguez, David L. Wasdell, John A. Orosa, Matthew D. Montgomery
  • Publication number: 20170204878
    Abstract: 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: Application
    Filed: August 29, 2014
    Publication date: July 20, 2017
    Inventor: John A. Orosa
  • Patent number: 9644497
    Abstract: 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: Grant
    Filed: November 22, 2013
    Date of Patent: May 9, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Matthew R. Porter, Lijuan Han, Matthew J. Delisa, III
  • Patent number: 9598981
    Abstract: 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: Grant
    Filed: November 22, 2013
    Date of Patent: March 21, 2017
    Assignee: Siemens Energy, Inc.
    Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Lijuan Han, Matthew J. Delisa, III, Daniel F. Riveros
  • Patent number: 9587519
    Abstract: 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: Grant
    Filed: November 22, 2013
    Date of Patent: March 7, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Matthew R. Porter, Lijuan Han, Matthew J. Delisa, III, Daniel F. Riveros
  • Publication number: 20170022834
    Abstract: 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: Application
    Filed: May 4, 2016
    Publication date: January 26, 2017
    Inventor: John A. Orosa
  • Publication number: 20170022901
    Abstract: 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: Application
    Filed: April 18, 2016
    Publication date: January 26, 2017
    Inventor: John A. Orosa
  • Publication number: 20170022905
    Abstract: 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: Application
    Filed: April 25, 2016
    Publication date: January 26, 2017
    Inventors: John A. Orosa, Joseph D. Brostmeyer, Justin T. Cejka, Russell B. Jones
  • Patent number: 9540956
    Abstract: 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: Grant
    Filed: November 22, 2013
    Date of Patent: January 10, 2017
    Assignee: Siemens Energy, Inc.
    Inventors: Anil L. Salunkhe, John A. Orosa, Yevgeniy Shteyman, Matthew R. Porter, Lijuan Han, Matthew J. Delisa, III, Daniel F. Riveros
  • Publication number: 20160376929
    Abstract: 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: Application
    Filed: June 29, 2015
    Publication date: December 29, 2016
    Inventors: Ali Akturk, Jose L. Rodriguez, David L. Wasdell, John A. Orosa, Matthew D. Montgomery