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公开(公告)号：US20240150027A1
公开(公告)日：2024-05-09
申请号：US18450071
申请日：2023-08-15
发明人： Jonathan E. Coleman , Timothy L. Schelfaut , Anthony M. Metz , Thomas P. Joseph , Mahesh Khandeparker , Kudum Shinde , Donald L. Gardner
摘要： Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.
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公开(公告)号：US20210261262A1
公开(公告)日：2021-08-26
申请号：US16797078
申请日：2020-02-21
发明人： Timothy Leo Schelfaut , Anthony Michael Metz , Jonathan Edward Coleman , Thomas P. Joseph , Michael C. Borner , Mahesh Khandeparker , Kudum Shinde
IPC分类号： B64D27/26
摘要： Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle θ of at least one of the plurality of engine-mounting links.
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公开(公告)号：US20240067349A1
公开(公告)日：2024-02-29
申请号：US18062977
申请日：2022-12-07
发明人： Kudum Shinde , Mahesh Khandeparker
CPC分类号： B64D27/26 , B64D13/08 , B64D2013/0607 , B64D2027/262
摘要： Example engine apparatus and associated control methods are disclosed. An example engine apparatus includes: a frame; a lug to attach the frame to an aircraft; a mount cover positioned over the lug; and a heating mechanism to regulate a temperature of the lug under the mount cover.
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公开(公告)号：US20210300577A1
公开(公告)日：2021-09-30
申请号：US16836442
申请日：2020-03-31
发明人： Jonathan E. Coleman , Timothy L. Schelfaut , Anthony M. Metz , Thomas P. Joseph , Mahesh Khandeparker , Kudum Shinde , Donald L. Gardner
摘要： Methods, apparatus, systems and articles of manufacture are disclosed. A mechanical linkage for mounting a gas turbine engine to a pylon includes: a bending restraint having a first end and a second end; a first joint at the first end of the bending restraint to connect the first end of the bending restraint to a fan section of the gas turbine engine; and a second joint at the second end of the bending restraint to connect the second end of the bending restraint to the pylon.
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公开(公告)号：US12079735B2
公开(公告)日：2024-09-03
申请号：US17323667
申请日：2021-05-18
发明人： Kudum Shinde , Mahesh Khandeparker
CPC分类号： G06N5/00 , F01D5/12 , F01D11/14 , F01D11/22 , F01D11/24 , F02C7/20 , G06N20/00 , F05D2270/54 , F05D2270/70 , F05D2270/709
摘要： Systems and methods for optimizing clearances within an engine include an adjustable coupling configured to couple a thrust link to the aircraft engine, an actuator coupled to the adjustable coupling, where motion produced by the actuator adjusts a hinge point of the adjustable coupling, sensors configured to capture real time flight data, and an electronic control unit. The electronic control unit receives flight data from the sensors, implements a machine learning model trained to predict clearance values within the engine based on the received flight data, predicts, with the machine learning model, the clearance values within the engine based on the received flight data, determines an actuator position based on the clearance values, and causes the actuator to adjust to the determined actuator position.
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公开(公告)号：US12129767B1
公开(公告)日：2024-10-29
申请号：US18333328
申请日：2023-06-12
CPC分类号： F01D25/28 , F05D2220/323
摘要： Gas turbine mounting configurations for backbone bending mitigations are described herein. An example gas turbine engine disclosed herein includes a pylon, an inlet to be subjected to an inlet load along an inlet load axis, a case assembly including a first case portion and a second case portion, a forward mount coupling the first case portion to the pylon, the coupling of the forward mount to the pylon defining a first line of action, an aft mount, and a thrust link coupling the second case portion to the pylon, the thrust link defining a second line of action, an intersection of the first line of action and the second line of action disposed at least one of: (1) on the inlet load axis and the centerline, (2) downstream of the inlet load axis and beneath the centerline, and (3) upstream of the inlet load axis and above the centerline.
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公开(公告)号：US11939070B2
公开(公告)日：2024-03-26
申请号：US16797078
申请日：2020-02-21
发明人： Timothy Leo Schelfaut , Anthony Michael Metz , Jonathan Edward Coleman , Thomas P. Joseph , Michael C. Borner , Mahesh Khandeparker , Kudum Shinde
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/268
摘要： Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle θ of at least one of the plurality of engine-mounting links.
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公开(公告)号：US20220371738A1
公开(公告)日：2022-11-24
申请号：US17323667
申请日：2021-05-18
发明人： Kudum Shinde , Mahesh Khandeparker
摘要： Systems and methods for optimizing clearances within an engine include an adjustable coupling configured to couple a thrust link to the aircraft engine, an actuator coupled to the adjustable coupling, where motion produced by the actuator adjusts a hinge point of the adjustable coupling, sensors configured to capture real time flight data, and an electronic control unit. The electronic control unit receives flight data from the sensors, implements a machine learning model trained to predict clearance values within the engine based on the received flight data, predicts, with the machine learning model, the clearance values within the engine based on the received flight data, determines an actuator position based on the clearance values, and causes the actuator to adjust to the determined actuator position.
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