Patents by Inventor Charles Stanley ORKISZEWSKI
Charles Stanley ORKISZEWSKI 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: 11542820Abstract: The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.Type: GrantFiled: December 6, 2017Date of Patent: January 3, 2023Assignee: General Electric CompanyInventors: Jorg Arrien Tiemon, Charles Stanley Orkiszewski
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Patent number: 11485508Abstract: A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.Type: GrantFiled: October 29, 2019Date of Patent: November 1, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Gert Johannes Van Der Merwe, Charles Stanley Orkiszewski
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Patent number: 11187102Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.Type: GrantFiled: July 17, 2020Date of Patent: November 30, 2021Assignee: General Electric CompanyInventor: Charles Stanley Orkiszewski
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Patent number: 10947993Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ciType: GrantFiled: November 27, 2017Date of Patent: March 16, 2021Assignee: General Electric CompanyInventors: Kudum Shinde, Praveen Sharma, Shashank Suresh Puranik, Shivam Mittal, Charles Stanley Orkiszewski, Carl Lawrence MacMahon, Anthony Michael Metz, Brian Drummond
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Publication number: 20200347746Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.Type: ApplicationFiled: July 17, 2020Publication date: November 5, 2020Inventor: Charles Stanley Orkiszewski, III
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Patent number: 10801361Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.Type: GrantFiled: September 9, 2016Date of Patent: October 13, 2020Assignee: GENERAL ELECTRIC COMPANYInventors: Nagamohan Govinahalli Prabhakar, Steven Andrew Strang, Charles Stanley Orkiszewski, Subramanya Shankar, Nitesh Jain, Michael Riehle
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Patent number: 10760498Abstract: The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.Type: GrantFiled: January 4, 2018Date of Patent: September 1, 2020Assignee: General Electric CompanyInventors: Andrew Bryan Cannella, Charles Stanley Orkiszewski, Milind Chandrakant Dhabade, Praveen Sharma, Brian Drummond, Shivam Mittal
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Patent number: 10746222Abstract: A damper assembly includes a bearing assembly including a radially outer surface. A housing surrounds the bearing assembly and includes a radially inner surface facing the radially outer surface. The radially outer and inner surfaces define a plurality of annuli therebetween. The damper assembly further includes a plurality of fluid supplies coupled in flow communication with the plurality of annuli and configured to deliver a fluid to each annulus of the plurality of annuli. Each fluid supply of the plurality of fluid supplies independently controls the fluid within the respective annulus.Type: GrantFiled: April 22, 2016Date of Patent: August 18, 2020Assignee: General Electric CompanyInventors: Tod Robert Steen, Charles Stanley Orkiszewski
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Patent number: 10718231Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.Type: GrantFiled: December 15, 2017Date of Patent: July 21, 2020Assignee: General Electric CompanyInventor: Charles Stanley Orkiszewski
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Publication number: 20200062412Abstract: A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.Type: ApplicationFiled: October 29, 2019Publication date: February 27, 2020Inventors: Gert Johannes VAN DER MERWE, Charles Stanley ORKISZEWSKI
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Patent number: 10518891Abstract: A turbine engine assembly is provided. The assembly includes a stationary component, a drive shaft, and a gearbox coupled along the drive shaft, and coupled to the stationary component. The assembly also includes a vibration-reducing mechanism coupled between the stationary component and the gearbox. The vibration-reducing mechanism is configured to isolate a vibratory response of the gearbox from the stationary component.Type: GrantFiled: November 17, 2015Date of Patent: December 31, 2019Assignee: General Electric CompanyInventors: Gert Johannes Van Der Merwe, Charles Stanley Orkiszewski
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Patent number: 10502096Abstract: Dampers for bearing assemblies of gas turbine engines are provided. For example, a damper comprises a damper housing, a lubricant passage defined in the damper housing, and a valve positioned within the lubricant passage. The lubricant passage includes an inlet and an outlet. In one embodiment, the valve is configured to restrict a flow of lubricant from the inlet into the damper when a reference temperature is below a threshold temperature. In another embodiment, the valve is configured to increase leakage of a lubricant through the outlet when a reference temperature is below a threshold temperature. In other embodiments, the valve is passively actuated and is configured to move within the lubricant passage to control a flow of lubricant from the inlet to the outlet based on a reference temperature.Type: GrantFiled: December 15, 2017Date of Patent: December 10, 2019Assignee: General Electric CompanyInventor: Charles Stanley Orkiszewski
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Publication number: 20190203646Abstract: The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.Type: ApplicationFiled: January 4, 2018Publication date: July 4, 2019Inventors: Andrew Bryan Cannella, Charles Stanley Orkiszewski, Milind Chandrakant Dhabade, Praveen Sharma, Brian Drummond, Shivam Mittal
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Publication number: 20190186284Abstract: Embodiments of systems and methods for operating a gas turbine engine defining a bowed rotor condition are generally provided. The systems and methods include rotating a rotor assembly defining a bowed rotor condition from approximately zero revolutions per minute (RPM) to within a bowed rotor mitigation speed range, in which the bowed rotor mitigation speed range is defined by a lower speed limit greater than zero RPM and an upper speed limit less than or equal to an idle speed condition of the gas turbine engine; applying a load at the rotor assembly via an energy storage device; adjusting the load to limit rotational speed or acceleration of the rotor assembly to within the bowed rotor mitigation speed range for a period of time; and removing the load to enable rotation of the rotor assembly to the idle speed condition following the period of time.Type: ApplicationFiled: December 15, 2017Publication date: June 20, 2019Inventor: Charles Stanley Orkiszewski
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Publication number: 20190186296Abstract: Dampers for bearing assemblies of gas turbine engines are provided. For example, a damper comprises a damper housing, a lubricant passage defined in the damper housing, and a valve positioned within the lubricant passage. The lubricant passage includes an inlet and an outlet. In one embodiment, the valve is configured to restrict a flow of lubricant from the inlet into the damper when a reference temperature is below a threshold temperature. In another embodiment, the valve is configured to increase leakage of a lubricant through the outlet when a reference temperature is below a threshold temperature. In other embodiments, the valve is passively actuated and is configured to move within the lubricant passage to control a flow of lubricant from the inlet to the outlet based on a reference temperature.Type: ApplicationFiled: December 15, 2017Publication date: June 20, 2019Inventor: Charles Stanley Orkiszewski
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Publication number: 20190169992Abstract: The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.Type: ApplicationFiled: December 6, 2017Publication date: June 6, 2019Inventors: Jorg Arrien Tiemon, Charles Stanley Orkiszewski
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Publication number: 20190162203Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ciType: ApplicationFiled: November 27, 2017Publication date: May 30, 2019Inventors: Kudum Shinde, Praveen Sharma, Shashank Suresh Puranik, Shivam Mittal, Charles Stanley Orkiszewski, Carl Lawrence MacMahon, Anthony Michael Metz, Brian Drummond
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Publication number: 20180073388Abstract: The turbine assembly includes a shaft, a plurality of rotor disks, a plurality of blades, and at least one cutting mechanisms. The rotor disks are spaced axially along, and coupled to, the shaft and include a radially outer portion. The blades are spaced circumferentially around the radially outer portion. The cutting mechanisms are configured to cut the blades from the rotor disk during a disk over speed condition.Type: ApplicationFiled: September 9, 2016Publication date: March 15, 2018Inventors: Nagamohan Govinahalli Prabhakar, Steven Andrew Strang, Charles Stanley Orkiszewski, Subramanya Shankar, Nitesh Jain, Michael Riehle
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Publication number: 20170307046Abstract: A damper assembly includes a bearing assembly including a radially outer surface. A housing surrounds the bearing assembly and includes a radially inner surface facing the radially outer surface. The radially outer and inner surfaces define a plurality of annuli therebetween. The damper assembly further includes a plurality of fluid supplies coupled in flow communication with the plurality of annuli and configured to deliver a fluid to each annulus of the plurality of annuli. Each fluid supply of the plurality of fluid supplies independently controls the fluid within the respective annulus.Type: ApplicationFiled: April 22, 2016Publication date: October 26, 2017Inventors: Tod Robert Steen, Charles Stanley Orkiszewski
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Publication number: 20160144970Abstract: A turbine engine assembly is provided. The assembly includes a stationary component, a drive shaft, and a gearbox coupled along the drive shaft, and coupled to the stationary component. The assembly also includes a vibration-reducing mechanism coupled between the stationary component and the gearbox. The vibration-reducing mechanism is configured to isolate a vibratory response of the gearbox from the stationary component.Type: ApplicationFiled: November 17, 2015Publication date: May 26, 2016Inventors: Gert Johannes VAN DER MERWE, Charles Stanley ORKISZEWSKI