公开(公告)号：US12006837B2

公开(公告)日：2024-06-11

申请号：US17587764

申请日：2022-01-28

Applicant: Raytheon Technologies Corporation

Inventor： Bryan P. Dube ,  David A. Litton

IPC: F01D5/18 ,  F01D5/28

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.

公开(公告)号：US20240175372A1

公开(公告)日：2024-05-30

申请号：US18070978

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Raymond Surace ,  Howard J. Liles ,  Bryan P. Dube

IPC: F01D25/00 ,  F01D9/04

CPC classification number: F01D25/005 ,  F01D9/041 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.

公开(公告)号：US11988104B1

公开(公告)日：2024-05-21

申请号：US18070978

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Raymond Surace ,  Howard J. Liles ,  Bryan P. Dube

IPC: F01D25/00 ,  F01D9/04

CPC classification number: F01D25/005 ,  F01D9/041 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.

公开(公告)号：US20240018875A1

公开(公告)日：2024-01-18

申请号：US18187839

申请日：2023-03-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan P. Dube ,  Wojciech Lipka

IPC: F01D9/04 ,  F01D5/18

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D9/041 ,  F01D5/284

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 spar 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.

公开(公告)号：US20220389823A1

公开(公告)日：2022-12-08

申请号：US17339567

申请日：2021-06-04

Applicant: Raytheon Technologies Corporation

Inventor： Bryan P. Dube ,  Joshua S. Lieberman

IPC: F01D5/28 ,  F01D9/04

Abstract: A method of assembling a ceramic matrix composite (CMC) component is provided. The method includes assessing which portions of the CMC component require relatively high-temperature capability and which portions require at least one of strength, thickness and increased thermal conductivity, making the portions that require the relatively high temperature capability with chemical vapor infiltration (CVI), making the portions that require the at least one of strength, thickness and increased thermal conductivity with melt infiltration (MI) and combining the portions that require the relatively high temperature capability with the CVI and the portions that require the at least one of strength, thickness and increased thermal conductivity with the MI.

公开(公告)号：US20220356808A1

公开(公告)日：2022-11-10

申请号：US17307074

申请日：2021-05-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Robert A. White, III ,  Bryan P. Dube

IPC: F01D11/00 ,  F01D5/18 ,  F02C7/28

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.

公开(公告)号：US11459894B1

公开(公告)日：2022-10-04

申请号：US17197140

申请日：2021-03-10

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tyler G. Vincent ,  Chang Gao ,  Bryan P. Dube

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/28

Abstract: An airfoil fairing includes an airfoil section that is formed of a fiber-reinforced composite wall. The airfoil section has first and second radial ends, pressure and suction sides, leading and trailing ends that join the pressure and suction sides, an internal cavity, and a rib that extends radially in the internal cavity. The rib has a radial rib end at the first radial end of the airfoil section and extends across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side. The rib defines at the radial end first and second shoulders. The first and second shoulders define a radial notch there between.

公开(公告)号：US20220268165A1

公开(公告)日：2022-08-25

申请号：US17480511

申请日：2021-09-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Alyson T. Burdette ,  Bryan P. Dube

IPC: F01D9/04

Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and a hollow airfoil section that extends there from. The hollow airfoil section defines an airfoil profile and surrounds an internal cavity. The fairing platform defines a gaspath side and a non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite comprised of fiber plies. The fiber plies include at least one cavity fiber ply that is arranged as a tube that circumscribes the internal cavity. The at least one cavity fiber ply extends through the fairing platform and defines at least a portion of an upstanding collar on the non-gaspath side of the fairing platform. The upstanding collar defines a collar profile. The tube necks down through a neck portion such that at least a portion of the collar profile is narrower than the airfoil profile.

公开(公告)号：US11339667B2

公开(公告)日：2022-05-24

申请号：US16990420

申请日：2020-08-11

Applicant: Raytheon Technologies Corporation

Inventor： San Quach ,  Bryan P. Dube ,  Tracy A. Propheter-Hinckley ,  Allan N. Arisi ,  Adam P. Generale ,  Lucas Dvorozniak ,  Howard J. Liles

IPC: F01D5/18 ,  F01D5/28

Abstract: A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.

公开(公告)号：US12180857B2

公开(公告)日：2024-12-31

申请号：US18304922

申请日：2023-04-21

Applicant: Raytheon Technologies Corporation

Inventor： Emma J. Place ,  Bryan P. Dube ,  Pedro D. Laureano ,  Bernard Joseph Reilly, III ,  Mohamed Hassan ,  Edwin Otero ,  Andrew Correia ,  William R. Hackbarth, II ,  Jeffrey M. Jacques

IPC: F01D5/30 ,  F01D5/02

Abstract: An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.