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公开(公告)号：US10815792B2
公开(公告)日：2020-10-27
申请号：US16239949
申请日：2019-01-04
Applicant: United Technologies Corporation
Inventor： James Tilsley Auxier , Jeffrey T. Morton , Matthew S. Gleiner , Parth Jariwala , Charles Thistle , Megan J. Kwolek
Abstract: A component for a gas turbine engine includes a body portion that extends between a leading edge and a trailing edge of the component. The trailing edge includes a flared region and a non-flared region. At least one discharge slot is disposed at least partially within the flared region of the component.
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公开(公告)号：US20190055848A1
公开(公告)日：2019-02-21
申请号：US15680807
申请日：2017-08-18
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Mohamed Hassan
Abstract: A gas turbine engine, having: a disk; a plurality of blades secured to the disk, each of the plurality of blades having a platform located between a root portion and an airfoil portion of the blade, wherein the platform of one of the plurality of blades is configured to define a cavity with a platform of an adjacent blade that is secured to the disk; a damper seal located in the cavity and positioned adjacent to a gap defined by edges of the platforms of the blades; and a damper restraint located on an interior surface of each platform, wherein the damper restraint extends into the cavity and is a raised feature configured to contact a peripheral edge portion of a damper seal when it is adjacent to the gap defined by the platforms of the blades.
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公开(公告)号：US20180187562A1
公开(公告)日：2018-07-05
申请号：US15397557
申请日：2017-01-03
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Mohamed Hassan
Abstract: A blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint retaining a lateral edge of a damper seal received in the cavity, wherein the lateral edge of the damper seal extends between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion extend towards the root when the damper seal is located in the cavity and wherein the damper restraint extends along and adjacent to a portion of the lateral edge of the damper seal.
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公开(公告)号：US20180187558A1
公开(公告)日：2018-07-05
申请号：US15397501
申请日：2017-01-03
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Mohamed Hassan
CPC classification number: F01D5/225 , F01D5/02 , F01D5/22 , F01D5/3007 , F01D11/006 , F01D11/008 , F04D29/083 , F04D29/322 , F04D29/324 , F04D29/668 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2230/60 , F05D2240/80 , F05D2260/36 , Y02T50/673
Abstract: A blade for a gas turbine engine is provided. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; and a chamfer located on opposing peripheral edges of the platform.
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公开(公告)号：US20180149025A1
公开(公告)日：2018-05-31
申请号：US15362779
申请日：2016-11-28
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Mohamed Hassan
Abstract: A blade for a gas turbine engine. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper seal received in the cavity, the damper seal having a main body portion that extends along a major axis of the damper seal between a first end portion and an opposing second end portion of the damper seal, the first end portion and the second end portion each extend towards the root when the damper seal is located in the cavity and wherein the damper seal has a variable thickness along at least a portion of a minor axis of the damper seal that extends between opposite peripheral edges of the main body portion.
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Patent Agency Ranking
公开(公告)号：US10570749B2
公开(公告)日：2020-02-25
申请号：US15004498
申请日：2016-01-22
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Yongxiang D. Xue
Abstract: A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.
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公开(公告)号：US10519782B2
公开(公告)日：2019-12-31
申请号：US15613255
申请日：2017-06-04
Applicant: United Technologies Corporation
Inventor： Carey Clum , Evan P. Molony , Charles Thistle , Dominic J. Mongillo
Abstract: Airfoils having a body with leading and trailing edges and a first serpentine cavity within the body enabling a cooling flow in a first direction within the airfoil body, a second serpentine cavity fluidly connected to the first serpentine cavity enabling a cooling flow in a second direction, and a third serpentine cavity fluidly connected to the second serpentine cavity enabling a cooling flow in at least one of the first direction or a third direction. A resupply cavity is fluidly connected to the third serpentine cavity to supply a resupply air to the third serpentine cavity, a junction at the location of the second serpentine cavity, the resupply cavity and the third serpentine cavity, and a flow control feature arranged to turn the serpentine cooling air from the second direction and/or prevent resupply air backflow.
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公开(公告)号：US20190024514A1
公开(公告)日：2019-01-24
申请号：US15656020
申请日：2017-07-21
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Evan P. Molony , Carey Clum
Abstract: Airfoils and airfoil cores for airfoils of gas turbine engines are provided. The airfoils include an airfoil body having a leading edge and a trailing edge, at least two serpentine flow cavities formed within the airfoil body, a resupply cavity fluidly connected to one serpentine flow cavity of the at least two serpentine flow cavities and arranged to supply a resupply air to the one serpentine flow cavity through a resupply bypass hole, a junction defined at a location where the resupply cavity fluidly connect to the one serpentine flow cavity, a separator rib within the airfoil body and fluidly separating part of the at least two serpentine flow cavities, at least one crossover rib located between the resupply bypass hole and the separator rib, and at least one crossover aperture located between the at least one crossover rib and the separator rib.
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公开(公告)号：US10047611B2
公开(公告)日：2018-08-14
申请号：US15009366
申请日：2016-01-28
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Mohamed Hassan
Abstract: The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.
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公开(公告)号：US20170211394A1
公开(公告)日：2017-07-27
申请号：US15004498
申请日：2016-01-22
Applicant: United Technologies Corporation
Inventor： Charles Thistle , Yongxiang D. Xue
Abstract: A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.
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