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公开(公告)号：US10196980B2
公开(公告)日：2019-02-05
申请号：US15017805
申请日：2016-02-08
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Bruce Alan Carter , Charles Andrew Corman
Abstract: A retention housing for the outer race of a bearing of a gas turbine engine includes a spring finger housing connected to and overlying a bearing housing that is connected to the outer race of the bearing. The spring finger housing includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. A plurality of edge recesses are defined in the bearing housing and a plurality of lug tabs extending radially from the engine's interface shell limit are disposed in the edge recess to limit the deflection and self-arrest the distortion of the retention housing. A gas turbine engine includes the retention housing described above.
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公开(公告)号：US20180112672A1
公开(公告)日：2018-04-26
申请号：US15331121
申请日：2016-10-21
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Shuvajyoti Ghosh , Shivaram AC , Akash Joshi , Vidya Lokammanahalli Shivashankar
IPC: F04D29/056 , F02K3/06 , F04D29/32 , F04D29/053 , F16C35/073 , F16C39/02
CPC classification number: F16C39/02 , F01D21/045 , F01D25/162 , F01D25/164 , F02C7/06 , F02K3/06 , F04D29/321 , F04D29/662 , F05D2220/36 , F05D2260/311 , F05D2300/505 , F16C19/06 , F16C19/225 , F16C25/083 , F16C35/073 , F16C2202/06 , F16C2202/08 , F16C2360/23 , Y02T50/671
Abstract: A method of reducing loads in a rotor assembly during an imbalance condition, a shape memory alloy recoupler device, and a hybrid bearing support system are provided. The hybrid bearing support system includes a shaft extension fixedly coupled to a rotatable member at a radially inner end of the shaft extension, a radially outer end of said shaft extension fixedly coupled to a rotatable race of a bearing supporting the rotatable member, and a recoupler device formed of a shape memory alloy (SMA) material coupled in parallel with at least a portion of said shaft extension between the radially inner end and the radially outer end.
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公开(公告)号：US09869205B2
公开(公告)日：2018-01-16
申请号：US14948917
申请日：2015-11-23
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Bruce Alan Carter , Nitin Deepak Rupnar , Charles Andrew Corman
IPC: F01D25/16 , F16C35/04 , F16C35/067 , F16C27/04
CPC classification number: F01D25/162 , F01D25/164 , F05D2220/32 , F05D2240/54 , F16C19/06 , F16C27/045 , F16C35/042 , F16C35/067 , F16C2360/23 , Y02T50/671
Abstract: A housing for retention of the outer race of a bearing of a gas turbine engine includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. Controlled circumferential gaps on both sides of each spring finger limit the deflection and self-arrest the distortion of the housing. An axial gap is created on the aft end by a portion of the spring finger beam structure that opposes an axial face of the housing and limits the axial distortion. A radial gap created between interface hardware of the housing and the inner retention housing also acts to retain the spring finger housing under load in a radial direction.
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公开(公告)号：US12281618B2
公开(公告)日：2025-04-22
申请号：US18910905
申请日：2024-10-09
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Bugra H. Ertas , Ravindra Shankar Ganiger , Andrea Piazza , Arthur W. Sibbach
Abstract: A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.
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公开(公告)号：US20250116199A1
公开(公告)日：2025-04-10
申请号：US18984554
申请日：2024-12-17
Applicant: General Electric Company
IPC: F01D11/00
Abstract: Seals for a gas turbine engine are disclosed herein. An example sealing apparatus for a gas turbine engine includes a first end having a first contact surface to contact a first component of a rotating machine, a second end having a second contact surface to contact a second component of the rotating machine, the second component positioned in proximity to the first component such that a cavity is formed therebetween, the apparatus dividing the cavity into a first cavity portion and a second cavity portion, and a central portion extending the first end from the second end, the central portion defining a first chamber and a second chamber, the first chamber in fluid communication with the first cavity portion, the second chamber in fluid communication with the second cavity portion, the first chamber is fluidly isolated from the second chamber.
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Patent Agency Ranking
公开(公告)号：US12270308B2
公开(公告)日：2025-04-08
申请号：US18493508
申请日：2023-10-24
Applicant: General Electric Company
Inventor： Naveena K P , Ravindra Shankar Ganiger , Domala Uma Maheshwar , Kishore Budumuru , Kudum Shinde , Abhishek Goverdhan
Abstract: Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate including a first surface and a second surface that is radially inward relative to the first surface; an actuator structure coupled to the second surface of the annular substrate; and a smart structure cantilevered from the second surface of the annular substrate, the smart structure including: a support structure, a first region of the support structure coupled to the second surface of the annular substrate, a second region of the support structure coupled to the actuator structure; and a radially inward surface defining a variable surface, the support structure to move the variable surface in a radial direction.
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公开(公告)号：US12221892B2
公开(公告)日：2025-02-11
申请号：US18463970
申请日：2023-09-08
Applicant: General Electric Company
Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.
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公开(公告)号：US20250027537A1
公开(公告)日：2025-01-23
申请号：US18456244
申请日：2023-08-25
Applicant: General Electric Company
Inventor： Paul Mathew , Ravindra Shankar Ganiger , David Raju Yamarthi
IPC: F16C33/24
Abstract: Bearings with grooves and methods of producing the same are disclosed. Examples disclosed herein include a bearing having a bearing surface with a groove, the bearing positioned adjacent to a shaft, the groove facing the shaft, and a negative thermal expansion (NTE) material positioned in the groove, the NTE material at least partially filling the groove.
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公开(公告)号：US12180890B1
公开(公告)日：2024-12-31
申请号：US18454531
申请日：2023-08-23
Applicant: General Electric Company
Inventor： Nageswar Rao Ganji , Ravindra Shankar Ganiger , Ambika Shivamurthy , Hiranya Kumar Nath , Trevor H. Wood
Abstract: Example variable bleed valve assemblies for a gas turbine engine are disclosed herein, including a port extending radially outward from a compressor section of the gas turbine engine, the port defining a variable bleed valve cavity, the port to resonate at a resonant frequency based on an operating condition of the gas turbine engine, and an acoustic suppressor positioned on a wall of the port, the acoustic suppressor extending circumferentially along the wall by a length greater than a cross-sectional width of the acoustic suppressor, the acoustic suppressor defining a resonant cavity based on the length and the cross-sectional width, the acoustic suppressor including a perforated portion, the acoustic suppressor tuned to resonate at the resonant frequency based on the length and the perforated portion.
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公开(公告)号：US20240426222A1
公开(公告)日：2024-12-26
申请号：US18751022
申请日：2024-06-21
Applicant: General Electric Company
Inventor： Deepak Trivedi , Rahul Anil Bidkar , Bugra H. Ertas , Narendra Anand Hardikar , Ravindra Shankar Ganiger
Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include one or more paired rotors and stators and at least one interface between the rotors and the stators. The components of the stator may be axially and radially movable by vibrations and other mechanical interference. The stators comprise a sealing element, a seal housing, and a stator interface connected to the engine housing. In some examples, seal assembly includes a damping element to isolate one or more of the rotating components from vibrations mechanical interference that might misalign the rotating components from the stationary components while the turbomachine is operational. In some examples, the damping element is positioned between the seal housing and the stator interface. In other examples, the damping element is positioned between the stator interface and the engine housing.
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