-
1.发明公开公开(公告)号：US20230192562A1
公开(公告)日：2023-06-22
申请号：US18083983
申请日：2022-12-19
Applicant: Raytheon Technologies Corporation
Inventor： Kathryn S. Read , Bryan H. Farrar , Andrew J. Lazur , Steven R. Clarke , Aaron Tomich
IPC: C04B35/80 , D03D15/283 , D03D15/242
CPC classification number: C04B35/80 , D03D15/283 , D03D15/242 , C04B2235/5216 , C04B2235/616 , C04B2235/5212 , D10B2321/06 , D10B2321/08 , D10B2505/02
Abstract: Disclosed herein is a composite ply comprising fill and warp tows; or optional axial and bias tows; wherein one or more of the fill tows and/or the warp tows or wherein one or more of the optional axial and/or bias tows comprise a polymer yarn while the remaining portion of the fill tows and/or the warp tows or the remaining portion of the bias and/or optional axial tows comprise the polymer yarn; and wherein the polymer yarn is melted to bond to the fill or warp tows to prevent removal from the ply.
-
公开(公告)号：US20230053047A1
公开(公告)日：2023-02-16
申请号：US17971999
申请日：2022-10-24
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Bryan H. Farrar , Jon E. Sobanski
Abstract: An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.
-
公开(公告)号：US11549380B2
公开(公告)日：2023-01-10
申请号：US17076043
申请日：2020-10-21
Applicant: Raytheon Technologies Corporation
Inventor： Bryan H. Farrar , Howard J. Liles
Abstract: A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.
-
公开(公告)号：US20210156266A1
公开(公告)日：2021-05-27
申请号：US17076043
申请日：2020-10-21
Applicant: Raytheon Technologies Corporation
Inventor： Bryan H. Farrar , Howard J. Liles
Abstract: A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.
-
Patent Agency Ranking
公开(公告)号：US12044143B2
公开(公告)日：2024-07-23
申请号：US17553928
申请日：2021-12-17
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Howard J. Liles , Tyler G. Vincent , Bryan H. Farrar
CPC classification number: F01D5/187 , F01D5/282 , F01D5/284 , F05D2240/304 , F05D2260/202 , F05D2260/2214 , F05D2300/6033
Abstract: A gas turbine engine component includes a supply cavity and a manifold cavity that shares a common divider wall with the supply cavity. The common divider wall includes inlet metering holes that connect the supply cavity and the manifold cavity. An exterior wall has an exterior surface and an opposed interior surface that bounds portions of the supply cavity and of the manifold cavity. Outlet cooling holes extend through the exterior wall and connect the manifold cavity with the exterior surface. The number of the inlet metering holes is equal to or less than the number of the outlet cooling holes, and at least one of the inlet holes is coaxial with at least one of the outlet holes.
-
公开(公告)号：US20230193764A1
公开(公告)日：2023-06-22
申请号：US17553928
申请日：2021-12-17
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Howard J. Liles , Tyler G. Vincent , Bryan H. Farrar
CPC classification number: F01D5/187 , F01D5/282 , F01D5/284 , F05D2240/304 , F05D2260/202 , F05D2300/6033 , F05D2260/2214
Abstract: A gas turbine engine component includes a supply cavity and a manifold cavity that shares a common divider wall with the supply cavity. The common divider wall includes inlet metering holes that connect the supply cavity and the manifold cavity. An exterior wall has an exterior surface and an opposed interior surface that bounds portions of the supply cavity and of the manifold cavity. Outlet cooling holes extend through the exterior wall and connect the manifold cavity with the exterior surface. The number of the inlet metering holes is equal to or less than the number of the outlet cooling holes, and at least one of the inlet holes is coaxial with at least one of the outlet holes.
-
公开(公告)号：US11905854B2
公开(公告)日：2024-02-20
申请号：US17971999
申请日：2022-10-24
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Bryan H. Farrar , Jon E. Sobanski
CPC classification number: F01D9/065 , B22F10/28 , B23P15/04 , B33Y80/00 , F01D5/18 , F01D5/189 , F05D2220/32 , F05D2230/50 , F05D2230/60 , F05D2300/6033
Abstract: An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.
-
公开(公告)号：US11415009B2
公开(公告)日：2022-08-16
申请号：US17150184
申请日：2021-01-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Bryan H. Farrar
Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section extending there between. There is a spar having 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 with a clevis mount that that protrudes from the second fairing platform. A support platform adjacent the second fairing platform has first and second through-holes. The end portion of the spar leg extends through the first through-hole and a pin extends though the clevis mount to lock the support platform to the spar leg. A stabilizer rod extends through the second through-hole of the support platform and limits rotation of the support platform about the pin.
-
公开(公告)号：US20220228499A1
公开(公告)日：2022-07-21
申请号：US17150184
申请日：2021-01-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Bryan H. Farrar
Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section extending there between. There is a spar having 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 with a clevis mount that that protrudes from the second fairing platform. A support platform adjacent the second fairing platform has first and second through-holes. The end portion of the spar leg extends through the first through-hole and a pin extends though the clevis mount to lock the support platform to the spar leg. A stabilizer rod extends through the second through-hole of the support platform and limits rotation of the support platform about the pin.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.011 seconds)
