Patents by Inventor Robert Joseph Orlando
Robert Joseph Orlando 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: 10215047Abstract: An actuator includes a pump including a first cavity and a diaphragm coupled in flow communication with the first cavity. The diaphragm is configured to pressurize a fluid contained in the first cavity. The pump further includes a first valve coupled in flow communication with the first cavity. The first valve is configured to release fluid from the first cavity when the first cavity is pressurized. The actuator also includes a piston assembly operatively coupled to the pump.Type: GrantFiled: December 28, 2015Date of Patent: February 26, 2019Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Joseph George Rose, Robert Joseph Orlando, Chenyu Jack Chou
-
Patent number: 9726113Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a core gas turbine engine including a first rotatable drive shaft, a first low-pressure turbine section in serial flow communication with the gas turbine engine, a gear assembly coupled to the first low-pressure turbine section through a second rotatable drive shaft, and a second low-pressure turbine section in serial flow communication with the core gas turbine engine. The first low-pressure turbine section is configured to rotate in a first rotational direction, and the second low-pressure turbine section is configured to rotate in a second rotational direction opposite the first rotational direction. The first and second low-pressure turbine sections are spaced axially apart from each other. The turbine engine assembly also includes a fan assembly coupled to the first low-pressure turbine section through the gear assembly, and coupled to the second low-pressure turbine section through a third rotatable drive shaft.Type: GrantFiled: January 7, 2014Date of Patent: August 8, 2017Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz, Alan Roy Stuart
-
Publication number: 20170183976Abstract: An actuator includes a pump including a first cavity and a diaphragm coupled in flow communication with the first cavity. The diaphragm is configured to pressurize a fluid contained in the first cavity. The pump further includes a first valve coupled in flow communication with the first cavity. The first valve is configured to release fluid from the first cavity when the first cavity is pressurized. The actuator also includes a piston assembly operatively coupled to the pump.Type: ApplicationFiled: December 28, 2015Publication date: June 29, 2017Inventors: Thomas Ory Moniz, Joseph George Rose, Robert Joseph Orlando, Chenyu Jack Chou
-
Publication number: 20140119885Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a core gas turbine engine including a first rotatable drive shaft, a first low-pressure turbine section in serial flow communication with the gas turbine engine, a gear assembly coupled to the first low-pressure turbine section through a second rotatable drive shaft, and a second low-pressure turbine section in serial flow communication with the core gas turbine engine. The first low-pressure turbine section is configured to rotate in a first rotational direction, and the second low-pressure turbine section is configured to rotate in a second rotational direction opposite the first rotational direction. The first and second low-pressure turbine sections are spaced axially apart from each other. The turbine engine assembly also includes a fan assembly coupled to the first low-pressure turbine section through the gear assembly, and coupled to the second low-pressure turbine section through a third rotatable drive shaft.Type: ApplicationFiled: January 7, 2014Publication date: May 1, 2014Applicant: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz, Alan Roy Stuart
-
Patent number: 8205458Abstract: A duplex turbine nozzle includes a row of different first and second vanes alternating circumferentially between radially outer and inner bands in vane doublets having axial splitlines therebetween. The vanes have opposite pressure and suction sides spaced apart in each doublet to define an inboard flow passage therebetween, and corresponding outboard flow passages between doublets. The vanes have different patterns of film cooling holes with larger cooling flow density along the outboard passages than along the inboard passages.Type: GrantFiled: December 31, 2007Date of Patent: June 26, 2012Assignee: General Electric CompanyInventors: Ching-Pang Lee, Robert Joseph Orlando
-
Patent number: 8104292Abstract: A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of second cooling holes extending therethrough. The corresponding patterns have different collective flowrate capabilities.Type: GrantFiled: December 17, 2007Date of Patent: January 31, 2012Assignee: General Electric CompanyInventors: Ching-Pang Lee, Geoffrey Douglas Robinson, Robert Joseph Orlando
-
Patent number: 8091334Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: GrantFiled: January 26, 2011Date of Patent: January 10, 2012Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
-
Patent number: 8015828Abstract: A power take-off system for a gas turbine engine includes a starter coupled to a second spool, and a clutch assembly coupled between the starter and a first spool, the clutch assembly configured to couple the first spool to the starter when starting the gas turbine engine assembly. A method of assembling a gas turbine engine assembly that includes the power take-off system, and a gas turbine engine assembly including the power take-off system are also described.Type: GrantFiled: April 3, 2007Date of Patent: September 13, 2011Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jan Christopher Schilling, Robert Joseph Orlando, Raymond Felix Patt
-
Patent number: 7997085Abstract: A method for assembling a gas turbine engine including a core gas turbine engine, a low-pressure turbine, a starter, and a generator is provided. The method includes coupling a starter to the core gas turbine engine, and coupling a generator to the low-pressure turbine.Type: GrantFiled: September 27, 2006Date of Patent: August 16, 2011Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Paul Cooker, Robert Joseph Orlando
-
Patent number: 7966806Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a low-pressure turbine coupled to said core gas turbine engine, a counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction, and a gearbox comprising an input and an output, said gearbox output coupled to at least one of said first and second rotor sections, said gearbox input coupled to said low-pressure turbine. A method of assembling the turbofan engine assembly described herein is also provided.Type: GrantFiled: October 31, 2006Date of Patent: June 28, 2011Assignee: General Electric CompanyInventors: John Leslie Henry, Robert Joseph Orlando, Thomas Ory Moniz
-
Publication number: 20110120136Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: ApplicationFiled: January 26, 2011Publication date: May 26, 2011Inventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
-
Patent number: 7926259Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a first fan assembly coupled to a low-pressure turbine, a second fan assembly disposed downstream from the first fan assembly, and a gearbox coupled between the second fan assembly and the low-pressure turbine. A method of assembling the above turbofan engine assembly is also described herein.Type: GrantFiled: October 31, 2006Date of Patent: April 19, 2011Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz
-
Patent number: 7926289Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.Type: GrantFiled: November 10, 2006Date of Patent: April 19, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
-
Patent number: 7921634Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a counter-rotating fan assembly disposed upstream from the booster compressor, the counter-rotating fan assembly comprising a first fan configured to rotate in a first direction and a second fan configured to rotate in an opposite second direction, and a low-pressure turbine disposed downstream from the intermediate-pressure turbine, the low-pressure turbine configured to drive the counter-rotating fan assembly. A method of assembling the above turbofan engine assembly is also described herein.Type: GrantFiled: October 31, 2006Date of Patent: April 12, 2011Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz
-
Patent number: 7905083Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a counter-rotating fan assembly disposed upstream from the booster compressor, the counter-rotating fan assembly comprising a first fan configured to rotate in a first direction and a second fan configured to rotate in an opposite second direction, and an intermediate-pressure turbine disposed downstream from the core gas turbine engine, wherein the intermediate-pressure turbine drives the booster compressor and the second fan assembly. A method of assembling the above turbofan engine assembly is also described herein.Type: GrantFiled: October 31, 2006Date of Patent: March 15, 2011Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz
-
Patent number: 7886518Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: GrantFiled: November 14, 2006Date of Patent: February 15, 2011Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
-
Patent number: 7883311Abstract: A rotor assembly for a gas turbine engine is provided. The rotor assembly includes a compressor rotor, a compressor stator coupled upstream from the compressor rotor, and a bearing assembly coupled between the compressor rotor and the compressor stator for supporting the compressor rotor. The bearing assembly includes a pair of foil thrust bearings coupled to a portion of the compressor stator and a pair of spring packs coupled substantially co-axially to the pair of foil thrust bearings. A method of assembling the same is also provided.Type: GrantFiled: December 20, 2006Date of Patent: February 8, 2011Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Robert Joseph Orlando
-
Patent number: 7870742Abstract: A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.Type: GrantFiled: November 10, 2006Date of Patent: January 18, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
-
Patent number: 7870743Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.Type: GrantFiled: November 10, 2006Date of Patent: January 18, 2011Assignee: General Electric CompanyInventors: Ching-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
-
Patent number: 7841165Abstract: A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor directly to the low-pressure turbine such that the booster compressor rotates in the first direction.Type: GrantFiled: October 31, 2006Date of Patent: November 30, 2010Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz