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公开(公告)号：US20240360795A1
公开(公告)日：2024-10-31
申请号：US18306644
申请日：2023-04-25
IPC分类号： F02C7/277
CPC分类号： F02C7/277 , F05D2260/96
摘要： An air turbine starter for starting an engine includes a starter housing having an inlet, an outlet, and a flow path extending between the inlet and the outlet. The air turbine starter includes a rotatable turbine member having a central hub defining a platform and a set of blades extending radially from the platform. The air turbine starter also includes a damping member.
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公开(公告)号：US20240360767A1
公开(公告)日：2024-10-31
申请号：US18687378
申请日：2022-08-31
发明人： Jean-Hilaire LEXILUS
IPC分类号： F01D5/22
CPC分类号： F01D5/22 , F05D2220/323 , F05D2230/60 , F05D2240/30 , F05D2260/96
摘要： A damper for an impeller of an aircraft turbomachine includes an elastic member housed in two metallic half-shells so as to allow a relative movement of the half-shells relative to one another.
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公开(公告)号：US12129815B2
公开(公告)日：2024-10-29
申请号：US17816556
申请日：2022-08-01
申请人： IHI Corporation
发明人： Yasuhiro Ishikawa , Shinji Ishihara , Hatsuo Mori
CPC分类号： F02K9/972 , F02K9/52 , F05D2240/35 , F05D2260/2214 , F05D2260/232 , F05D2260/96
摘要： The combustor for a rocket engine includes a combustion room configured to cause a combustion reaction between a fuel and an oxidant, an injector configured to inject the fuel and the oxidant into the combustion room, and a nozzle skirt configured to inject combustion gas generated by the combustion reaction to an outside, and an inertance increasing portion configured to increase an equivalent inertance in a vibration equivalent circuit of the combustor for the rocket engine.
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公开(公告)号：US12110844B2
公开(公告)日：2024-10-08
申请号：US17987671
申请日：2022-11-15
申请人： ROHR, INC.
IPC分类号： F02K1/82
CPC分类号： F02K1/827 , F05D2220/323 , F05D2260/96
摘要： A center plug for attenuating noise in a gas turbine engine includes an inner skin, a forward bulkhead, and aft bulkhead, and a noise attenuation panel. The inner skin has a substantially cylindrical shape and extending along an axial centerline. The forward bulkhead is disposed proximate a forward end of the inner skin. The forward bulkhead is connected to and extends radially outward from the inner skin. The aft bulkhead is disposed proximate an aft end of the inner skin. The aft bulkhead is connected to and extending radially outward from the inner skin. The noise attenuation panel is positioned intermediate the inner skin and partially divides a region bounded by the inner skin, the forward bulkhead and the aft bulkhead into.
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公开(公告)号：US12104536B2
公开(公告)日：2024-10-01
申请号：US17318898
申请日：2021-05-12
申请人： Rohr, Inc.
CPC分类号： F02C7/24 , F02C7/045 , F02K1/827 , G10K11/161 , G10K11/172 , B64D2033/0206 , F05D2260/96
摘要： An acoustic attenuation structure for a gas turbine engine includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first axial tube, each of the first axial tube and the second axial tube being in fluid communication with one another through the first central body.
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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
发明人： Trevor Howard Wood , Ramakrishna Venkata Mallina , Giridhar Jothiprasad , Kishore Ramakrishnan , Thomas Malkus
CPC分类号： F02C7/24 , F01D11/08 , F02C3/06 , F02C7/045 , F05D2240/14 , F05D2250/184 , F05D2260/96
摘要： 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
CPC分类号： F02C7/24 , F01D11/08 , F02C3/06 , F02C7/045 , B64D2033/0206 , F05D2240/14 , F05D2250/184 , F05D2260/96
摘要： 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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公开(公告)号：US12085018B2
公开(公告)日：2024-09-10
申请号：US18337763
申请日：2023-06-20
发明人： Jeffrey G. Morris , Brett Vann
CPC分类号： F02C7/05 , F02C7/20 , F02C7/24 , H02K7/1823 , E21B41/0085 , F01D15/00 , F05D2220/76 , F05D2230/644 , F05D2240/90 , F05D2260/30 , F05D2260/607 , F05D2260/608 , F05D2260/96
摘要： A system for providing mobile electric power includes a first transport including a generator, a second transport including a gas turbine, and a third transport including an air inlet filter housing. The first transport, the second transport, and the third transport are separate transports that are independently movable in a transportation mode. In an operation mode, the first transport and the second transport are connected end-to-end such that a first end side of the first transport faces a first end side of the second transport. In the operation mode, the third transport is positioned relative to the end-to-end connected first and second transports such that a first longitudinal side of the third transport faces a first longitudinal side of the first transport and a first longitudinal side of the second transport.
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公开(公告)号：US12065947B2
公开(公告)日：2024-08-20
申请号：US18090197
申请日：2022-12-28
发明人： Ravindra Shankar Ganiger , Sam J. Stoughton , Kevin Lee Kirkeng , Jacob P. Miller , Reddi Hari Prasad Reddy Mylapalli , Paul Trimby , Jaeyong Kim
CPC分类号： F01D5/225 , F02C7/28 , F05D2240/55 , F05D2250/283 , F05D2260/31 , F05D2260/96
摘要： Methods, apparatus, systems and articles of manufacture are disclosed. An inner shroud damper for a gas turbine engine includes: at least one carrier including a joint to couple to an inner shroud, the at least one carrier having a first side and a second side, and at least one mass damper coupled to the at least one carrier.
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公开(公告)号：US12060808B2
公开(公告)日：2024-08-13
申请号：US18457491
申请日：2023-08-29
发明人： Michael Ericson Friedman , Gang Liu
CPC分类号： F01D5/027 , B23B29/043 , B23C3/18 , B23C5/00 , B23C5/12 , F05D2220/32 , F05D2230/10 , F05D2240/24 , F05D2260/96
摘要： A turbine rotor includes a rotor body and a balancing weight slot defined in an exterior circumference of the body. The balancing weight slot has a first axial width and a first radially outward facing surface at a first radial distance from a rotor axis. The rotor also includes a balancing weight entry port defined in a portion of the exterior circumference of the rotor body and aligned with the balancing weight slot. The balancing weight entry port has a second axial width greater than the first axial width and a second radially outward facing surface at a second radial distance from the axis of the rotor body that is smaller than the first radial distance. A method may include machining the entry port into the rotor with a tool. The method may be applied to a new rotor, or to remove cracks initiating from a previous entry port.
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