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公开(公告)号：US11473434B2
公开(公告)日：2022-10-18
申请号：US16654380
申请日：2019-10-16
Applicant: United Technologies Corporation
Inventor： Timothy Charles Nash , Gary A. Zess , Eric A. Grover , Jin Hu
Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.
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公开(公告)号：US11466588B2
公开(公告)日：2022-10-11
申请号：US16668786
申请日：2019-10-30
Applicant: United Technologies Corporation
Inventor： David C. Kiely , Todd A. Davis , Russell B. Witlicki , Christopher M. Valva , Andrew Newton
Abstract: A gas turbine engine component includes an inner support structure surrounding an engine center axis and fixed to an engine static structure, an outer support structure spaced radially outward of the inner support structure, and a curved beam comprised of a plurality of curved beam spring segments that are positioned adjacent to each other to form a ring. The inner and outer support structures are coupled together around the curved beam to enclose the curved beam therebetween and form an assembly. A bearing is spaced radially inward of the assembly.
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公开(公告)号：US11459946B2
公开(公告)日：2022-10-04
申请号：US16536526
申请日：2019-08-09
Applicant: United Technologies Corporation
Inventor： Matthew R. Feulner , Gary Collopy
Abstract: A system includes a gas turbine engine having a low speed spool and a high speed spool. The system also includes a spool coupling system configured to mechanically link the low speed spool and the high speed spool. A controller is operable to determine a mode of operation of the gas turbine engine, monitor for a spool coupling activation condition associated with the mode of operation, and activate the spool coupling system based on the controller detecting the spool coupling activation condition. Engagement and power transfer between the low speed spool and the high speed spool occurs based on activation of the spool coupling system and reaching an engagement condition of the spool coupling system.
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公开(公告)号：US11459899B2
公开(公告)日：2022-10-04
申请号：US15934332
申请日：2018-03-23
Applicant: United Technologies Corporation
Inventor： Dilip M. Shah , Alan D. Cetel , Venkatarama K. Seetharaman , Raymond Surace
IPC: F01D5/18
Abstract: A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.
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公开(公告)号：US11459895B2
公开(公告)日：2022-10-04
申请号：US16848180
申请日：2020-04-14
Applicant: United Technologies Corporation
Inventor： Pedro David Laureano , John A. Lucena
Abstract: A turbine blade includes an airfoil including a pressure side and a suction side. A platform includes a pressure side wall and a suction side wall, and has a leading edge end wall and a trailing edge end wall. A pocket is positioned under the platform on the pressure side. A hole has a first end communicating with the pocket and having a second end communicating with the pressure side wall. A gas turbine engine is also disclosed.
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Patent Agency Ranking
公开(公告)号：US11454124B2
公开(公告)日：2022-09-27
申请号：US16686696
申请日：2019-11-18
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a first side, and a second side. Radially-extending ribs partition the interior cavity of the airfoil into first and second cooling channels and a radial cooling passage that is situated between the first and second cooling channels. The cooling channels extend to respective first and second channel ends. A turn channel connects the first and second channel ends. The turn channel splits at the first channel end into first and second channel legs such that there is a region between the first and second channel legs. The channels legs merge at the second channel end. The radial cooling passage extends through the region between the first and second channel legs.
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公开(公告)号：US11448233B2
公开(公告)日：2022-09-20
申请号：US15602754
申请日：2017-05-23
Applicant: United Technologies Corporation
Inventor： Eric W. Malmborg
Abstract: A fan blade assembly for a gas turbine engine includes a blade extending from a blade root to a blade tip, and from a blade leading edge to a blade trailing edge. The blade includes a plurality of ribs defining a plurality of blade cavities. A pressure surface cover is affixed to the blade and at least partially defines a pressure surface of the fan blade. At least one rib of the plurality of ribs extends along a predicted impact path of a foreign object at the fan blade assembly, thereby supporting impact loads on the pressure surface cover.
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公开(公告)号：US11448128B2
公开(公告)日：2022-09-20
申请号：US16785853
申请日：2020-02-10
Applicant: United Technologies Corporation
Inventor： Nigel David Sawyers-Abbott , Kenneth N. Baker
Abstract: A lubrication system for a gas turbine engine includes a primary fluid tank to receive a primary fluid, at least one secondary fluid tank to receive at least one fluid additive, and a mixer. The mixer has at least a first inlet in fluid communication with the primary fluid tank and a second inlet in fluid communication with the at least one secondary fluid tank. The mixer has at least one outlet that delivers a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine component.
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公开(公告)号：US11447271B2
公开(公告)日：2022-09-20
申请号：US16376324
申请日：2019-04-05
Applicant: United Technologies Corporation
Inventor： Nagendra Somanath , Kurt R. Heinemann , Evan Selin , Glenn Levasseur
Abstract: A maintenance scheduling system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters. Each of the gas turbine engine components is a single route component and has been utilized in a substantially identical single route. The computer system includes at least one simulated engine model. The simulated engine model is configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components. A correlation system is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A maintenance schedule module is configured determine a predictive model operable to determine a predicted wear pattern of a second single route component that is substantially identical to the gas turbine engine components.
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公开(公告)号：US11441489B2
公开(公告)日：2022-09-13
申请号：US16839111
申请日：2020-04-03
Applicant: United Technologies Corporation
Inventor： William C. Lamberti , Paul Raymond Scheid , Jason E. Posniak
Abstract: A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine. The communication adapter also includes a memory system and processing circuitry configured to receive an engine control update request from the offboard system, confirm an authentication between the communication adapter and the engine control, transfer one or more configuration items received at the communication adapter from the offboard system to the engine control based on the authentication, and transmit an update completion confirmation of the engine control from the communication adapter to the offboard system based on a confirmation message from the engine control.
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