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公开(公告)号：US20220349314A1
公开(公告)日：2022-11-03
申请号：US17246912
申请日：2021-05-03
Applicant: Raytheon Technologies Corporation
Inventor： Robert A. White, III , Bryan P. Dube , Wojciech Lipka
Abstract: A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.
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公开(公告)号：US12000288B2
公开(公告)日：2024-06-04
申请号：US17246912
申请日：2021-05-03
Applicant: Raytheon Technologies Corporation
Inventor： Robert A. White, III , Bryan P. Dube , Wojciech Lipka
CPC classification number: F01D11/005 , F01D11/003 , F01D25/005 , F01D25/246 , F05D2230/90 , F05D2240/11
Abstract: A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.
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公开(公告)号：US11719130B2
公开(公告)日：2023-08-08
申请号：US17313099
申请日：2021-05-06
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Robert A. White, III , Bryan P. Dube
CPC classification number: F01D25/246 , F01D5/18 , F01D9/041 , F01D9/042 , F02C3/04 , F01D5/284 , F05D2220/323 , F05D2230/642 , F05D2240/12 , F05D2300/6033
Abstract: A vane system includes a plurality of vane assemblies and a continuous support ring. The vane assemblies are arranged circumferentially about an axis and each include a hollow airfoil fairing and a spar. The spar has a spar flange and a spar leg extending radially inwardly from the spar flange and through the hollow airfoil fairing. The continuous support ring has radially inner and outer sides and defines a circumferential row of through-holes between the radially inner and outer sides. The spar legs extend through the through-holes and the spar flanges are affixed at the radially outer side of the continuous support ring.
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公开(公告)号：US20230243265A1
公开(公告)日：2023-08-03
申请号：US17587764
申请日：2022-01-28
Applicant: Raytheon Technologies Corporation
Inventor： Bryan P. Dube , David A. Litton
CPC classification number: F01D5/186 , F01D5/284 , F01D5/288 , F05D2230/90 , F05D2260/202 , F05D2260/232 , F05D2300/6033 , F05D2300/611
Abstract: A ceramic matrix composite component includes a ceramic matrix composite wall; a coating disposed on the wall; and a cooling hole formed in the wall. The cooling hole has a metering section defined along a first axis and a diffuser section defined along a second axis that is offset from the first axis. The cooling hole has a total length defined along the first axis, the total length being the sum of a length of the metering portion and a length of the diffuser portion. The length of the metering portion is between about 40 percent and about 85 percent of the total length. A ceramic matrix composite airfoil and a method of applying a coating to a ceramic matrix composite component are also disclosed.
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公开(公告)号：US20230235675A1
公开(公告)日：2023-07-27
申请号：US17581170
申请日：2022-01-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Howard J. Liles , Bryan P. Dube
CPC classification number: F01D9/041 , F01D9/042 , F01D5/284 , F05D2240/12 , F05D2240/80 , F05D2250/291 , F05D2300/6033 , F05D2260/30
Abstract: A gas turbine engine includes a turbine section disposed about an engine axis. The turbine section includes inner and outer diameter ceramic support rings that define a gaspath there between. Each of the inner and outer diameter ceramic support rings is monolithic and continuous. Ceramic vane arc segments are disposed in the gaspath and supported by the inner and outer diameter ceramic support rings. Each of the ceramic vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter ceramic support ring with the ceramic vane arc segments to retain the ceramic vane arc segments between the inner and outer diameter ceramic support rings.
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Patent Agency Ranking
公开(公告)号：US11668200B2
公开(公告)日：2023-06-06
申请号：US17149914
申请日：2021-01-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Howard J. Liles , Bryan P. Dube , Wojciech Lipka
CPC classification number: F01D9/042 , F01D5/18 , F01D9/041 , F01D5/284 , F05D2300/6033
Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.
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公开(公告)号：US20230043695A1
公开(公告)日：2023-02-09
申请号：US17972833
申请日：2022-10-25
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Alyson T. Burdette , Bryan P. Dube
IPC: F01D9/04
Abstract: A method of fabricating an airfoil fairing for a vane arc segment includes providing a mandrel that necks down through a mandrel neck portion, providing fiber plies around the mandrel to form a tube that defines at least a portion of an airfoil profile of an airfoil section of an airfoil fairing, the fiber plies following the mandrel neck portion such that the tube has a corresponding tube neck portion that necks down to a collar, and removing the mandrel from the tube.
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公开(公告)号：US11549385B2
公开(公告)日：2023-01-10
申请号：US17307074
申请日：2021-05-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Robert A. White, III , Bryan P. Dube
Abstract: An airfoil assembly includes an airfoil fairing, a spar, a seal plate, and a seal. The airfoil fairing has a fairing platform and a hollow airfoil section that extends from the fairing platform. The spar has a spar leg that extends in the hollow airfoil section. The spar leg defines a spar leg periphery. The seal plate is secured with the fairing platform. The seal plate has an opening, and the opening has an opening periphery that is complementary to the spar leg periphery. The spar leg extends through the opening. The seal is between the seal plate and the spar leg. The seal seals around the spar leg periphery.
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公开(公告)号：US11299995B1
公开(公告)日：2022-04-12
申请号：US17191121
申请日：2021-03-03
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Tyler G. Vincent , Bryan P. Dube
Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section. A spar has a spar platform adjacent the first fairing platform and a hollow spar leg that extends from the spar platform and through the hollow airfoil section. The hollow spar leg has an internal passage for receiving cool air there through, a clevis mount, and a pin fairing. The clevis mount is distal from the spar platform and protrudes from the second fairing platform. The clevis mount includes first and second prongs with aligned holes. A pin extends through the aligned holes. The pin fairing extends over the pin between the first and second prongs for guiding the cooling air around the pin. There is a support platform adjacent the second fairing platform. The pin locks the support platform to the spar leg.
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公开(公告)号：US11215059B1
公开(公告)日：2022-01-04
申请号：US17011171
申请日：2020-09-03
Applicant: Raytheon Technologies Corporation
Inventor： San Quach , Bryan P. Dube , Raymond Surace , Alex J. Schneider , Tyler G. Vincent
Abstract: An airfoil includes a ceramic airfoil section that defines leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The span of the airfoil section has first, second, and third radial span zones. There is a row of cooling holes in an aft 25% of the axial span. The row of cooling holes extends though the first, second, and third radial span zones. The cooling holes in the first radial span zone define a first pitch P1, the cooling holes in the second radial span zone define a second pitch P2, and the cooling holes in the third radial span zone define a third pitch P3, wherein P2
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