-
公开(公告)号：US20170101191A1
公开(公告)日：2017-04-13
申请号：US14879217
申请日：2015-10-09
Applicant: General Electric Company
IPC: B64D33/02 , F02C7/32 , F04D29/32 , F04D29/52 , B64D27/24 , F04D29/36 , F01D15/10 , B64D27/18 , B64D27/26 , F02K3/062 , F04D29/54
CPC classification number: B64D33/02 , B64C1/16 , B64C21/06 , B64D27/18 , B64D27/20 , B64D27/24 , B64D27/26 , B64D29/04 , B64D2027/026 , B64D2033/0226 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/325 , F04D29/36 , F04D29/522 , F04D29/542 , F05D2220/323 , Y02T50/166
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades attached to a fan shaft. The aft engine also includes a nacelle encircling the plurality of fan blades and a structural support system for mounting the aft engine to the aircraft. The structural support system extends from the fuselage of the aircraft, through the fan shaft, and to the nacelle when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
-
公开(公告)号：US12215633B2
公开(公告)日：2025-02-04
申请号：US18486523
申请日：2023-10-13
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
-
公开(公告)号：US20210062728A1
公开(公告)日：2021-03-04
申请号：US16560089
申请日：2019-09-04
Applicant: General Electric Company
Inventor： Mark Frisch , Mark Joseph Mielke , Thomas Lee Becker
Abstract: An actuation assembly for concentric variable stator vanes of a rotary component of a gas turbine engine. The actuation assembly includes an inner casing and an intermediate casing defining a first concentric flowpath extending between the inner casing and the intermediate casing. The actuation assembly includes an outer casing defining a second concentric flowpath extending between the intermediate casing and the outer casing. The actuation assembly includes a first variable stator vane extending radially inward from the intermediate casing into the first concentric flowpath. The actuation assembly includes a second variable stator vane extending radially within the second concentric flowpath between a distal end at the outer casing and proximate end at the inner casing and defining a cavity extending therebetween. A first trunnion extends radially inward from the outer casing through the cavity of the second variable stator vane and is drivingly coupled to the first variable stator vane.
-
公开(公告)号：US20190329896A1
公开(公告)日：2019-10-31
申请号：US16450131
申请日：2019-06-24
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.
-
公开(公告)号：US09938853B2
公开(公告)日：2018-04-10
申请号：US15018966
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Thomas Lee Becker , Tod Robert Steen
IPC: F02C7/36 , F01D25/04 , F01D15/10 , H02P21/05 , F02C3/04 , F02C7/04 , F02C7/22 , F16F15/14 , F16F15/16 , H02K5/24 , H02P9/00 , H02P23/04 , F16F15/00 , H02P23/26
CPC classification number: F01D25/04 , F01D15/10 , F02C3/04 , F02C7/04 , F02C7/22 , F02C7/36 , F05D2220/32 , F05D2240/35 , F05D2260/96 , F16F15/00 , F16F15/12 , F16F15/14 , F16F15/16 , F16F15/18 , H02K5/24 , H02P9/007 , H02P21/05 , H02P23/04 , H02P23/26 , Y02T50/671
Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
-
Patent Agency Ranking
公开(公告)号：US09821917B2
公开(公告)日：2017-11-21
申请号：US14859514
申请日：2015-09-21
Applicant: General Electric Company
CPC classification number: B64D27/14 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/00 , B64D29/04 , B64D2027/264 , B64D2033/0226
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
-
公开(公告)号：US09815560B2
公开(公告)日：2017-11-14
申请号：US14859566
申请日：2015-09-21
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64D29/04 , B64C1/16 , B64C21/06 , B64D27/20 , B64D33/02 , B64D2033/0226 , Y02T50/166
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.
-
公开(公告)号：US20170081036A1
公开(公告)日：2017-03-23
申请号：US14859556
申请日：2015-09-21
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64D27/14 , B64C1/16 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/04 , B64D33/02 , Y02T50/166
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine, the fan including a plurality of fan blades. The aft engine also includes a nacelle surrounding the plurality of fan blades and defining an inlet. The inlet defines a non-axis symmetric shape with respect to the central axis of the aft engine to, e.g., allow for a maximum amount of airflow into the aft engine.
-
公开(公告)号：US11603801B2
公开(公告)日：2023-03-14
申请号：US17328795
申请日：2021-05-24
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
-
公开(公告)号：US11447259B2
公开(公告)日：2022-09-20
申请号：US16450131
申请日：2019-06-24
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.
-
-
-
-
-
-
-
-
-
Search Results
36
records
(took 0.019 seconds)
