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公开(公告)号：US11021995B2
公开(公告)日：2021-06-01
申请号：US16055704
申请日：2018-08-06
Applicant: United Technologies Corporation
Inventor： Robert J. Morris
Abstract: A gas turbine engine includes a fan rotating with a fan shaft, a compressor and a turbine section. The turbine section includes a fan drive rotor driving the fan through the fan shaft. At least one bearing is between an inner static case and the fan shaft. The inner static case is cantilever mounted to static structure, and has a forward end spaced in a forward direction toward the fan rotor from a cantilever mount. A damping assembly is associated with the inner static case.
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公开(公告)号：US10697375B2
公开(公告)日：2020-06-30
申请号：US15874033
申请日：2018-01-18
Applicant: United Technologies Corporation
Inventor： William E. Rosenkrans , Robert J. Morris
Abstract: A method of operation for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, reducing a rotational speed of a fan relative to a shaft through a gear train, driving the shaft with a first turbine, driving a compressor with a second turbine, communicating airflow from the fan through a bypass passage defined by a nacelle, the nacelle extending along an engine axis and surrounding the fan, and having a bypass ratio of greater than 10, discharging the airflow through a variable area fan nozzle defining a discharge airflow area, detecting an airfoil flutter condition associated with adjacent airfoils of the fan, and moving the variable area fan nozzle to vary the discharge airflow area and mitigate the airfoil flutter condition.
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公开(公告)号：US10544741B2
公开(公告)日：2020-01-28
申请号：US15725748
申请日：2017-10-05
Applicant: United Technologies Corporation
Inventor： William E. Rosenkrans , Robert J. Morris
Abstract: A gas turbine engine includes a fan section that has a fan with a plurality of airfoils, a compressor section, a gear train that reduces a rotational speed of the fan relative to a shaft in operation, a turbine section that has a first turbine and a second turbine, and a bypass ratio of greater than 10. The first turbine drives the shaft. A nacelle extends along an engine axis and surrounds the fan. A variable area fan nozzle defines a discharge airflow area. A fan airfoil flutter sensing system has a first sensor that actively and selectively detects a fan airfoil flutter condition in operation, and communicates with a controller programmed to move the variable area fan nozzle and vary the discharge airflow area to mitigate the flutter condition.
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公开(公告)号：US10077713B2
公开(公告)日：2018-09-18
申请号：US15161871
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： Daniel L. Gysling , Gregory M. Savela , Robert J. Morris
CPC classification number: F02C7/06 , F01D25/164 , F01D25/183 , F02K3/025 , F05D2260/96 , F16C19/06 , F16C27/045 , F16C2360/23 , F16F15/0237 , F16F2230/30
Abstract: A film damper for a gas turbine engine includes an annular inner member and an annular outer member located radially outboard of the annular inner member, the annular outer member and the annular inner member defining a damper annulus therebetween. A fluid supply passage delivers a flow of fluid into the damper annulus from the annular outer member, and a backflow prevention device is located at the fluid supply passage to prevent backflow of the flow of fluid from the damper annulus into the fluid supply passage.
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公开(公告)号：US20180156137A1
公开(公告)日：2018-06-07
申请号：US15874033
申请日：2018-01-18
Applicant: United Technologies Corporation
Inventor： William E. Rosenkrans , Robert J. Morris
Abstract: A method of operation for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, reducing a rotational speed of a fan relative to a shaft through a gear train, driving the shaft with a first turbine, driving a compressor with a second turbine, communicating airflow from the fan through a bypass passage defined by a nacelle, the nacelle extending along an engine axis and surrounding the fan, and having a bypass ratio of greater than 10, discharging the airflow through a variable area fan nozzle defining a discharge airflow area, detecting an airfoil flutter condition associated with adjacent airfoils of the fan, and moving the variable area fan nozzle to vary the discharge airflow area and mitigate the airfoil flutter condition.
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Patent Agency Ranking
公开(公告)号：US09470263B2
公开(公告)日：2016-10-18
申请号：US14626286
申请日：2015-02-19
Applicant: United Technologies Corporation
Inventor： Gregory M. Savela , Robert J. Morris
CPC classification number: F16C27/045 , F02C7/06 , F16C19/06 , F16C2240/54 , F16C2360/23
Abstract: A bearing for a gas turbine engine may comprise a squeeze film damper. A bearing housing may comprise a roughened surface. The roughened surface may increase friction between the bearing housing and the oil in the squeeze film damper. The increased friction may increase the damping force in the squeeze film damper. The increased damping force may prevent oil inertia, and prevent resonant vibrations.
Abstract translation: 用于燃气涡轮发动机的轴承可以包括挤压膜阻尼器。 轴承座可包括粗糙表面。 粗糙表面可能增加轴承壳体与挤压薄膜阻尼器中的油之间的摩擦。 增加的摩擦力可能增加挤压薄膜阻尼器中的阻尼力。 增加的阻尼力可以防止油惯性，并防止共振。
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公开(公告)号：US10808543B2
公开(公告)日：2020-10-20
申请号：US14783152
申请日：2014-04-09
Applicant: United Technologies Corporation
Inventor： Robert A. Grelotti , Robert J. Morris
Abstract: A rotor assembly for a gas turbine engine includes a rotor defining an outer periphery; and a plurality of blades attached to the outer periphery. The plurality of blades includes a material property different than the other of the plurality of blades to provide mistuning of the rotor.
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公开(公告)号：US10711703B2
公开(公告)日：2020-07-14
申请号：US15725720
申请日：2017-10-05
Applicant: United Technologies Corporation
Inventor： William E. Rosenkrans , Robert J. Morris
Abstract: A gas turbine engine includes a fan section that has a fan. A fan casing surrounds the fan section. A compressor section defines an engine axis. A gear train reduces a rotational speed of the fan relative to a shaft. A low pressure turbine is coupled to the shaft. A nacelle extends along the engine axis and surrounds the fan casing, a bypass ratio of greater than 10. A variable area fan nozzle defines a discharge airflow area. A flutter sensing system includes a controller programmed to move the variable area fan nozzle to vary the discharge airflow area in response to detecting an airfoil flutter condition associated with adjacent airfoils of the fan.
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公开(公告)号：US09915174B1
公开(公告)日：2018-03-13
申请号：US15420308
申请日：2017-01-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Robert J. Morris , Gregory M. Savela , Daniel L. Gysling , Richard A. Lomenzo
CPC classification number: F01D25/164 , F16C27/045 , F16C33/72 , F16C2360/23 , F16F9/02 , F16F2222/126 , F16F2230/30
Abstract: A bearing assembly is provided. The bearing assembly may include an inner race configured to couple to a shaft, an outer race disposed around the inner race, a bearing support structure coupled to the outer race, and a housing disposed around the bearing support structure. The housing and the bearing support structure may define a squeeze-film damper annulus configured to receive an aerated damping fluid. The aerated damping fluid may be provided from a fluid pump and an air supply port.
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公开(公告)号：US20170335767A1
公开(公告)日：2017-11-23
申请号：US15161871
申请日：2016-05-23
Applicant: United Technologies Corporation
Inventor： Daniel L. Gysling , Gregory M. Savela , Robert J. Morris
CPC classification number: F02C7/06 , F01D25/164 , F01D25/183 , F02K3/025 , F05D2260/96 , F16C19/06 , F16C27/045 , F16C2360/23 , F16F15/0237 , F16F2230/30
Abstract: A film damper for a gas turbine engine includes an annular inner member and an annular outer member located radially outboard of the annular inner member, the annular outer member and the annular inner member defining a damper annulus therebetween. A fluid supply passage delivers a flow of fluid into the damper annulus from the annular outer member, and a backflow prevention device is located at the fluid supply passage to prevent backflow of the flow of fluid from the damper annulus into the fluid supply passage.
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