Gas turbine engine airfoil
    41.
    发明授权

    公开(公告)号:US11473434B2

    公开(公告)日:2022-10-18

    申请号:US16654380

    申请日:2019-10-16

    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.

    Gas turbine engine spool coupling
    43.
    发明授权

    公开(公告)号:US11459946B2

    公开(公告)日:2022-10-04

    申请号:US16536526

    申请日:2019-08-09

    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.

    Turbine blade cooling hole for side wall

    公开(公告)号:US11459895B2

    公开(公告)日:2022-10-04

    申请号:US16848180

    申请日:2020-04-14

    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.

    Airfoil turn channel with split and flow-through

    公开(公告)号:US11454124B2

    公开(公告)日:2022-09-27

    申请号:US16686696

    申请日:2019-11-18

    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.

    Following blade impact load support

    公开(公告)号:US11448233B2

    公开(公告)日:2022-09-20

    申请号:US15602754

    申请日:2017-05-23

    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.

    Fluid additive system
    48.
    发明授权

    公开(公告)号:US11448128B2

    公开(公告)日:2022-09-20

    申请号:US16785853

    申请日:2020-02-10

    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.

    Aircraft component repair scheduling system and process

    公开(公告)号:US11447271B2

    公开(公告)日:2022-09-20

    申请号:US16376324

    申请日:2019-04-05

    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.

    Remote updates of a gas turbine engine

    公开(公告)号:US11441489B2

    公开(公告)日:2022-09-13

    申请号:US16839111

    申请日:2020-04-03

    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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