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41.发明申请AEROELASTICALLY TAILORED PROPELLERS FOR NOISE REDUCTION AND IMPROVED EFFICIENCY IN A TURBOMACHINE 审中-公开用于减少噪音和提高涡轮发动机效率的全自动定制螺旋桨公开(公告)号：US20150344127A1
公开(公告)日：2015-12-03
申请号：US14292873
申请日：2014-05-31
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
IPC: B64C11/50
CPC classification number: B64C11/18 , B64D2027/005 , Y02T50/66
Abstract: Aeroelastically tailored propellers for noise reduction and improved efficiency in a turbomachine are provided including one or more upstream blades and one or more downstream blades disposed downstream relative to the one or more upstream blades. Each of the one or more upstream blades and the one or more downstream blades are aeroelastically tailored such that the one or more downstream blades include a greater degree of effective clipping during a second condition than at a first condition. Each blade among the one or more upstream blades comprises one or more geometric parameters. Each blade among the one or more downstream blades comprises one or more geometric parameters. In addition, an open rotor aircraft gas turbine engine assembly including the aeroelastically tailored propellers and a method of decreasing noise and improving efficiency in a turbomachine are disclosed.
Abstract translation: 提供用于噪声降低和提高涡轮机效率的气动弹性定制推进器，包括一个或多个上游叶片和相对于一个或多个上游叶片设置在下游的一个或多个下游叶片。 所述一个或多个上游叶片和所述一个或多个下游叶片中的每一个被气动地定制，使得所述一个或多个下游叶片在第二状态期间比在第一条件下包括更大程度的有效限幅。 一个或多个上游叶片中的每个叶片包括一个或多个几何参数。 一个或多个下游叶片中的每个叶片包括一个或多个几何参数。 另外，公开了一种包括气动定型螺旋桨的开放式转子飞机燃气涡轮发动机组件以及降低噪声并提高涡轮机效率的方法。
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公开(公告)号：US12286941B2
公开(公告)日：2025-04-29
申请号：US18299102
申请日：2023-04-12
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Thomas Malkus , Kishore Ramakrishnan
Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.
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公开(公告)号：US20240309769A1
公开(公告)日：2024-09-19
申请号：US18674010
申请日：2024-05-24
Applicant: General Electric Company
Inventor： Kishore Ramakrishnan , Ravish Karve , Sara Elizabeth Carle , Trevor Howard Wood
CPC classification number: F01D9/041 , F01D25/28 , F05D2220/323 , F05D2250/37 , F05D2260/961
Abstract: A turbofan engine defining a circumferential direction is provided. The turbofan engine includes: a turbomachine, the turbomachine defining a pylon attachment location along the circumferential direction; an unducted rotor assembly drivingly coupled to the turbomachine, the unducted rotor assembly including a plurality of unducted rotor blades; and a plurality of outlet guide vanes positioned downstream of the plurality of unducted rotor blades, the plurality of outlet guide vanes including NOGV number of outlet guide vanes, the plurality of outlet guide vanes including a first outlet guide vane and a second outlet guide vane adjacent the first outlet guide vane, the first and second outlet guide vanes defining a gap spacing greater than 360 degrees divided by NOGV, and the pylon attachment location positioned outside of between the first and second outlet guide vanes along the circumferential direction.
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公开(公告)号：US12092034B2
公开(公告)日：2024-09-17
申请号：US17958549
申请日：2022-10-03
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Ramakrishna Venkata Mallina , Giridhar Jothiprasad , Kishore Ramakrishnan , Thomas Malkus
CPC classification number: F02C7/24 , F01D11/08 , F02C3/06 , F02C7/045 , F05D2240/14 , F05D2250/184 , F05D2260/96
Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
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公开(公告)号：US12085023B2
公开(公告)日：2024-09-10
申请号：US17958536
申请日：2022-10-03
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
CPC classification number: F02C7/24 , F01D11/08 , F02C3/06 , F02C7/045 , B64D2033/0206 , F05D2240/14 , F05D2250/184 , F05D2260/96
Abstract: A rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along a central axis of the rotary component and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the rotary component. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Further, at least one feature of the plurality of features is a slot having an acoustic liner feature integrated therein to reduce operational noise of the rotary component.
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Patent Agency Ranking
公开(公告)号：US20240295224A1
公开(公告)日：2024-09-05
申请号：US18656056
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan blades include a composite blade including a composite airfoil section having an airfoil leading edge and an airfoil trailing edge, a root attached to the composite airfoil section, and a blade shank therebetween. A metallic leading edge shield covers an axially extending portion of the composite airfoil section including at least a portion of the airfoil leading edge and covers a radially and chordwise extending portion of the airfoil leading edge of the blade shank. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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公开(公告)号：US20240288002A1
公开(公告)日：2024-08-29
申请号：US18656067
申请日：2024-05-06
Applicant: General Electric Company
Inventor： Jixian Yao , Trevor Howard Wood , Kishore Ramakrishnan , William Joseph Solomon , Giridhar Jothiprasad , Nicholas Joseph Kray
CPC classification number: F04D29/384 , F04D19/002
Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The annular casing is formed at least partially of a composite material. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.
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公开(公告)号：US20240117768A1
公开(公告)日：2024-04-11
申请号：US17958549
申请日：2022-10-03
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Ramakrishna Venkata Mallina , Giridhar Jothiprasad , Kishore Ramakrishnan , Thomas Malkus
CPC classification number: F02C7/24 , F01D11/08 , F02C3/06 , F05D2240/14 , F05D2250/184 , F05D2260/96
Abstract: A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
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公开(公告)号：US20230383675A1
公开(公告)日：2023-11-30
申请号：US17828112
申请日：2022-05-31
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Kishore Ramakrishnan
CPC classification number: F01D5/18 , F01D9/041 , F05D2240/121 , F05D2260/961 , F05D2250/184
Abstract: An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
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公开(公告)号：US20230340927A1
公开(公告)日：2023-10-26
申请号：US18299102
申请日：2023-04-12
Applicant: General Electric Company
Inventor： Trevor Howard Wood , Thomas Malkus , Kishore Ramakrishnan
IPC: F02K1/66
CPC classification number: F02K1/66
Abstract: A turbofan engine may include a variable pitch fan rotatable about an axis and operable in a forward thrust mode by generating flow opposite a direction of travel and in a reverse thrust mode by generating flow in the direction of travel. In reverse thrust mode, a nacelle assembly defines an intermediate opening disposed aft of the variable pitch fan. A flow guide assembly is configured to guide a first fluid flow opposite the direction of travel within a bypass passage from a forward opening to an aft opening of the nacelle assembly in forward thrust mode, and to redirect a second fluid flow from outside the bypass passage opposite the direction of travel to inside the bypass passage in the direction of travel through the intermediate opening in reverse thrust mode. One or more flow channels are defined for generating at least one fluidic injection pressurized by a core.
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