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公开(公告)号：US11261748B2
公开(公告)日：2022-03-01
申请号：US16678549
申请日：2019-11-08
发明人： Robert White, III
摘要： An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.
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公开(公告)号：US11261741B2
公开(公告)日：2022-03-01
申请号：US16678927
申请日：2019-11-08
摘要： An airfoil includes an airfoil body that has a trailing edge region. The trailing edge region includes first and second monolithic ceramic exterior walls, a flow discharge passage between the first and second monolithic ceramic exterior walls, a ceramic matrix composite (CMC) liner at least a portion of which is disposed in the flow discharge passage between the first and second monolithic ceramic exterior walls, and an array of pedestals disposed in the flow discharge passage. Each of the flow guides bridges the CMC liner and at least one of the first and second monolithic ceramic exterior walls.
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公开(公告)号：US11255432B2
公开(公告)日：2022-02-22
申请号：US16375954
申请日：2019-04-05
IPC分类号： F16J9/26
摘要： A piston seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a metal alloy binder phase and a hard particle phase distributed through the binder phase.
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公开(公告)号：US11255197B2
公开(公告)日：2022-02-22
申请号：US16734464
申请日：2020-01-06
摘要： An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.
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公开(公告)号：US11255026B2
公开(公告)日：2022-02-22
申请号：US16415466
申请日：2019-05-17
发明人： Bart A. van Hassel
IPC分类号： D01D10/02 , D01F9/08 , D02J13/00 , C04B41/00 , C04B41/80 , D01D5/00 , D01F9/10 , D06M10/00 , C04B37/00 , C04B35/622
摘要： A method for forming an ultra-high temperature (UHT) composite structure includes dispensing a polymeric precursor with a spinneret biased at a first DC voltage; forming a plurality of nanofibers from the polymeric precursor; receiving the plurality of nanofibers with a collector biased at a second DC voltage different than the first DC voltage; and changing a direction of movement of the plurality of nanofibers between the spinneret and the collector with a plurality of magnets having a magnetic field by adjusting the magnetic field.
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公开(公告)号：US11248989B2
公开(公告)日：2022-02-15
申请号：US16448365
申请日：2019-06-21
摘要： A system for providing real time aircraft engine sensor analysis includes a computer system configured to receive an engine operation data set in real time. The computer system includes a machine learning based analysis tool and a user interface configured to display a real time analysis of the engine operation data set. The user interface includes at least one portion configured to identify a plurality of anomalies in the engine operation data set.
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公开(公告)号：US11248791B2
公开(公告)日：2022-02-15
申请号：US15889764
申请日：2018-02-06
发明人： Steven D Porter , Jon E Sobanski
IPC分类号： F23R3/06 , B22C7/02 , F01D25/12 , F23R3/00 , B22D25/02 , F23R3/50 , F02K1/82 , F02C7/24 , F02K3/06
摘要： A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface and a plurality of holes, each hole including a central axis having vector components defined by a common vector.
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公开(公告)号：US11248523B2
公开(公告)日：2022-02-15
申请号：US16676112
申请日：2019-11-06
发明人： Nicholas D. Leque , Joseph H. Polly
摘要： A power extraction system for a gas turbine engine may comprise a low spool transmission and a low spool accessory gearbox. The low spool accessory gearbox may comprise a generator and a dual clutch transmission. The dual clutch transmission may be coupled between the low spool transmission and the generator.
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公开(公告)号：US11248470B2
公开(公告)日：2022-02-15
申请号：US16594402
申请日：2019-10-07
摘要： An airfoil includes an airfoil section that has an airfoil wall that define leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. The airfoil section extends form a platform. The platform defines a shelf that extends forward from the first end at the leading end of the airfoil section to a platform leading edge, aft from the first end at the trailing end of the airfoil section to a platform trailing edge, laterally from the first end at the first side of the airfoil section to a first platform side edge, and laterally from the first end at the second side of the airfoil section to a second platform side edge. The internal core cavity extends from the airfoil section into the shelf.
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公开(公告)号：US11242769B2
公开(公告)日：2022-02-08
申请号：US16221991
申请日：2018-12-17
发明人： Vijay Narayan Jagdale , Jesse R. Boyer , Om P. Sharma , Evan Butcher , Lawrence Binek , Bryan G. Dods
摘要： A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.
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