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公开(公告)号：US10677081B2
公开(公告)日：2020-06-09
申请号：US15688129
申请日：2017-08-28
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. Jones , Gareth J. Jones , Gary Eadon
Abstract: There is disclosed an axial flow machine (10) comprising an annular flow path (23); a stator ring (38) comprising a plurality of stators mounted at their radially outer ends and extending into the annular flow path (23); a non-rotating body (24) axially adjacent the stator ring (38); and an annular shroud (42) disposed between the radially inner end of the stator ring (38) and the body (24). The shroud (42) is supported on the stator ring (38) and moveable relative the body (24); and the shroud (42) cooperates with the body (24) to inhibit a flow through a clearance pathway (78) therebetween.
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公开(公告)号：US10605109B2
公开(公告)日：2020-03-31
申请号：US15959501
申请日：2018-04-23
Applicant: United Technologies Corporation
Inventor： Brad Powell
Abstract: A blade tip clearance control system for an engine case of a gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an air seal segment within the engine case. A drive link extends through the engine case, the drive link mounted to the air seal segment.
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公开(公告)号：US20190368615A1
公开(公告)日：2019-12-05
申请号：US16541898
申请日：2019-08-15
Applicant: United Technologies Corporation
Inventor： Conway Chuong , Ross Wilson
Abstract: An assembly for rotational equipment includes a plurality of seal shoes, a seal base, a plurality of spring elements and a frangible element. The seal shoes are arranged around an axis in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam extends longitudinally between and connects the first mount and the second mount. The frangible element is configured to restrict radial outward movement of the first of the seal shoes.
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公开(公告)号：US10458267B2
公开(公告)日：2019-10-29
申请号：US15709617
申请日：2017-09-20
Applicant: General Electric Company
Inventor： Nathan Evan McCurdy Gibson , Darek Tomasz Zatorski
IPC: F01D11/06 , F01D5/22 , F01D25/24 , F01D1/26 , F01D5/03 , F01D11/02 , F01D11/14 , F01D11/16 , F02K3/072 , F02C3/067 , F04D29/54 , F04D27/00
Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.
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公开(公告)号：US10443446B2
公开(公告)日：2019-10-15
申请号：US15908210
申请日：2018-02-28
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Richard Ivakitch , Czeslaw Wojtyczka , Andreas Eleftheriou
Abstract: A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell.
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Patent Agency Ranking
公开(公告)号：US10443423B2
公开(公告)日：2019-10-15
申请号：US14834918
申请日：2015-08-25
Applicant: Michael G. McCaffrey
Inventor： Michael G. McCaffrey
Abstract: A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades. Adjacent blade outer air seal segments provide a circumferential gap. Facing ends of the adjacent blade outer air seal segments include surfaces. A gap seal engages the surfaces and obstructs the circumferential gap. A biasing member is configured to urge the gap seal radially inward toward the surfaces.
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公开(公告)号：US10422431B2
公开(公告)日：2019-09-24
申请号：US15651081
申请日：2017-07-17
Applicant: United Technologies Corporation
Inventor： Conway Chuong , Ross Wilson
Abstract: An assembly for rotational equipment includes a plurality of seal shoes, a seal base, a plurality of spring elements and a frangible element. The seal shoes are arranged around an axis in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam extends longitudinally between and connects the first mount and the second mount. The frangible element is configured to restrict radial outward movement of the first of the seal shoes.
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公开(公告)号：US10415420B2
公开(公告)日：2019-09-17
申请号：US15093972
申请日：2016-04-08
Applicant: United Technologies Corporation
Inventor： David J. Wasserman , Scott D. Virkler , Eric A. Hudson , Ryan W. Brandt
Abstract: Thermal lifting members for blade outer air seal supports of gas turbine engines include a hollow body defining a thermal cavity therein, at least one inlet fluid connector fluidly connected to the thermal cavity configured to supply hot fluid to the thermal cavity from a fluid source, at least one outlet fluid connector fluidly connected to the thermal cavity configured to allow the hot fluid to exit the thermal cavity, and at least one lifting hook configured to engage with a blade outer air seal support, wherein the thermal lifting member is configured to thermally expand outward when hot fluid is passed through the thermal cavity such that during thermal expansion the at least one lifting hook forces the blade outer air seal support to move outward.
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公开(公告)号：US10301961B2
公开(公告)日：2019-05-28
申请号：US14913785
申请日：2014-07-23
Applicant: United Technologies Corporation
Inventor： Timothy M. Davis , Brian Duguay
Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.
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公开(公告)号：US10287906B2
公开(公告)日：2019-05-14
申请号：US15163079
申请日：2016-05-24
Inventor： Edward C. Rice , Daniel K. Vetters
Abstract: A gas turbine engine includes a blade track, a support assembly, and a seal system. The blade track is arranged around a central axis of the gas turbine engine to direct gasses through the gas turbine engine. The support assembly is arranged around the blade track to support the blade track relative to the central axis. The seal system is configured to block fluid communication between pressurized cavities formed in the support assembly.
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