Patents by Inventor John Joseph Rahaim
John Joseph Rahaim 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).
-
Publication number: 20220349316Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.Type: ApplicationFiled: July 14, 2022Publication date: November 3, 2022Inventors: Bhaskar Nanda Mondal, John Joseph Rahaim, Thomas Moniz, Steven A. Ross, Joel Kirk, Scott Hunter, Daniel Fusinato
-
Patent number: 11391173Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.Type: GrantFiled: October 29, 2019Date of Patent: July 19, 2022Assignee: General Electric CompanyInventors: Bhaskar Nanda Mondal, John Joseph Rahaim, Thomas Moniz, Steven A. Ross, Joel Kirk, Scott Hunter, Daniel Fusinato
-
Patent number: 11092013Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: GrantFiled: December 28, 2018Date of Patent: August 17, 2021Assignee: General Electric CompanyInventors: John Joseph Rahaim, Daniel John Fusinato, Scott David Hunter, Joel Francis Kirk, Michael Robert Melzak, Curtis Walton Stover
-
Publication number: 20200131922Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.Type: ApplicationFiled: October 29, 2019Publication date: April 30, 2020Inventors: Bhaskar Nanda MONDAL, John Joseph RAHAIM, Thomas MONIZ, Steven A. ROSS, Joel KIRK, Scott HUNTER, Daniel FUSINATO
-
Patent number: 10450951Abstract: A gas turbine engine comprising a cyclonic separator provides fluid communication between the compressor section and the turbine section. The cyclonic separator comprises an annular volume receiving a flow of cooling fluid from an inlet and dividing the airflow into a cleaner air outlet and a scavenge outlet. The flow of cooling fluid is provided to the cyclonic separator in a direction tangential to the annular volume such that a cyclonic flow of cooling fluid moves within the annular volume centrifugally separating particles entrained within the airflow to the radial outer area of the annular volume for removal through the scavenge outlet and providing a cleaner airflow to the cleaner air outlet.Type: GrantFiled: October 28, 2015Date of Patent: October 22, 2019Assignee: General Electric CompanyInventors: John Joseph Rahaim, Corey Bourassa, Jared Peter Buhler, Jonathan Russell Ratzlaff
-
Publication number: 20190136714Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: ApplicationFiled: December 28, 2018Publication date: May 9, 2019Inventors: John Joseph RAHAIM, Daniel John FUSINATO, Scott David HUNTER, Joel Francis KIRK, Michael Robert MELZAK, Curtis Walton STOVER
-
Patent number: 10202867Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: GrantFiled: March 14, 2014Date of Patent: February 12, 2019Assignee: General Electric CompanyInventors: John Joseph Rahaim, Daniel John Fusinato, Scott David Hunter, Joel Francis Kirk, Michael Robert Melzak, Curtis Walton Stover
-
Patent number: 10125686Abstract: A turbine engine assembly is provided. The assembly includes a booster compressor that discharges a flow of first compressed air at a first temperature, and a high-pressure compressor (HPC). The HPC receives a first portion of the flow of first compressed air and discharges the first portion at a second temperature higher than the first temperature such that a flow of second compressed air is formed. The assembly also includes a heat exchanger (HEX) that receives a second portion of the flow of first compressed air from the booster compressor and a first portion of the flow of second compressed air from the HPC such that heat is transferred therebetween. The HEX discharges the first portion of the flow of second compressed air at a third temperature lower than the second temperature and higher than the first temperature such that a flow of cooled bleed air is formed.Type: GrantFiled: December 3, 2015Date of Patent: November 13, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Carlos E. Diaz, John Joseph Rahaim, Jorge de Luis, Noel Istvan Macsotai
-
Publication number: 20170122202Abstract: A gas turbine engine comprising a cyclonic separator provides fluid communication between the compressor section and the turbine section. The cyclonic separator comprises an annular volume receiving a flow of cooling fluid from an inlet and dividing the airflow into a cleaner air outlet and a scavenge outlet. The flow of cooling fluid is provided to the cyclonic separator in a direction tangential to the annular volume such that a cyclonic flow of cooling fluid moves within the annular volume centrifugally separating particles entrained within the airflow to the radial outer area of the annular volume for removal through the scavenge outlet and providing a cleaner airflow to the cleaner air outlet.Type: ApplicationFiled: October 28, 2015Publication date: May 4, 2017Inventors: John Joseph Rahaim, Corey Bourassa, Jared Peter Buhler, Jonathan Russell Ratzlaff
-
Publication number: 20160160684Abstract: A turbine engine assembly is provided. The assembly includes a booster compressor that discharges a flow of first compressed air at a first temperature, and a high-pressure compressor (HPC). The HPC receives a first portion of the flow of first compressed air and discharges the first portion at a second temperature higher than the first temperature such that a flow of second compressed air is formed. The assembly also includes a heat exchanger (HEX) that receives a second portion of the flow of first compressed air from the booster compressor and a first portion of the flow of second compressed air from the HPC such that heat is transferred therebetween. The HEX discharges the first portion of the flow of second compressed air at a third temperature lower than the second temperature and higher than the first temperature such that a flow of cooled bleed air is formed.Type: ApplicationFiled: December 3, 2015Publication date: June 9, 2016Inventors: Carlos E. Diaz, John Joseph Rahaim, Jorge de Luis, Noel Istvan Macsotai
-
Publication number: 20160123172Abstract: A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.Type: ApplicationFiled: June 4, 2014Publication date: May 5, 2016Inventors: Bhaskar Nanda MONDAL, John Joseph RAHAIM, Thomas MONIZ, Steven A. ROSS, Joel KIRK, Scott HUNTER, Daniel FUSINATO
-
Publication number: 20160040552Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers , the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.Type: ApplicationFiled: March 14, 2014Publication date: February 11, 2016Inventors: John Joseph RAHAIM, Daniel John FUSINATO, Scott David HUNTER, Joel Francis KIRK, Michael Robert MELZAK, Curtis Walton STOVER
-
Patent number: 8393855Abstract: A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.Type: GrantFiled: June 29, 2007Date of Patent: March 12, 2013Assignee: General Electric CompanyInventors: Zhifeng Dong, John Joseph Rahaim
-
Patent number: 8197186Abstract: A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.Type: GrantFiled: June 29, 2007Date of Patent: June 12, 2012Assignee: General Electric CompanyInventors: Zhifeng Dong, John Joseph Rahaim
-
Publication number: 20090003990Abstract: A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.Type: ApplicationFiled: June 29, 2007Publication date: January 1, 2009Inventors: Zhifeng Dong, John Joseph Rahaim
-
Publication number: 20090004002Abstract: A gas turbine engine annular turbine casing having an annular shell, axially spaced apart forward and aft flanges extending radially outwardly from the shell, forward and aft case hooks depending radially inwardly from the annular shell, and an axially curved surface at an outer diameter of the aft flange. The axially curved surface may be a semi-spherical surface. The forward and aft case hooks may be located axially near or at the forward and aft flanges respectively. A circular row of holes may be axially disposed through the aft flange circumscribing the central axis and radially located between the outer diameter of the aft flange and the annular shell. An annular manifold spaced radially outwardly of the shell forming an annular space between the manifold and the shell and having impingement holes disposed through the manifold may be used for impinging cooling air on the axially curved surface.Type: ApplicationFiled: June 29, 2007Publication date: January 1, 2009Inventors: Zhifeng Dong, John Joseph Rahaim