公开(公告)号：US11286550B2

公开(公告)日：2022-03-29

申请号：US15470949

申请日：2017-03-28

Applicant: United Technologies Corporation

Inventor： Michael N. Task ,  Xuan Liu

IPC: C23C10/26 ,  C23C10/54 ,  C23C10/56 ,  C23C10/52 ,  C23C10/30 ,  C23C10/60

Abstract: A process includes applying a slurry to a surface of a metallic article to produce a slurry film on the surface. The slurry is composed of a liquid carrier, chromium and aluminum, and an agent that is reactive with the chromium and aluminum to form intermediary compounds. The article and slurry film are then thermally treated at an activation temperature at which the agent reacts with the chromium and aluminum to form the intermediary compounds. The intermediary compounds deposit the chromium and aluminum on the surface. The thermal treating also diffuses the chromium and aluminum into a sub-surface region of the article such that the sub-surface region becomes enriched with chromium and aluminum.

公开(公告)号：US11280201B2

公开(公告)日：2022-03-22

申请号：US16600875

申请日：2019-10-14

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Adam P. Generale ,  Lucas Dvorozniak ,  San Quach ,  Bryan P. Dube

IPC: F01D5/18

Abstract: An airfoil vane includes an airfoil section including an outer wall that defines an internal cavity; and a baffle situated in the internal cavity, the baffle including a baffle wall that defines a central cavity having a leading end and a trailing end corresponding to a leading end and a trailing end of the airfoil section, and a tail extending from the baffle wall, the tail including at least one feature configured to disturb an airflow surrounding the tail. A baffle for the airfoil vane assembly and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

公开(公告)号：US11274828B2

公开(公告)日：2022-03-15

申请号：US16270645

申请日：2019-02-08

Applicant: United Technologies Corporation

Inventor： Zhongfen Ding

IPC: F23R3/00 ,  C04B35/10 ,  C04B35/48 ,  C04B35/622 ,  F02K3/04

Abstract: An article includes a substrate, a bond coat layer disposed on the substrate, and a layer of networked ceramic nanofibers disposed on the bond coat layer.

公开(公告)号：US11274559B2

公开(公告)日：2022-03-15

申请号：US16743435

申请日：2020-01-15

Applicant: United Technologies Corporation

Inventor： Robin Prenter ,  Timothy J. Jennings ,  Carey Clum

IPC: F01D5/18 ,  F02C7/30

Abstract: A gaspath component for a gas turbine engine includes a platform. A body extends outward from the platform and includes at least one internal cooling passage. The internal cooling passage includes at least one particulate redirection feature defined at an end of the body opposite the platform. The at least one particulate redirection feature includes a first face oblique to and facing an expected flow of fluid through the internal cooling passage and defines at least one corresponding opening.

公开(公告)号：US11268696B2

公开(公告)日：2022-03-08

申请号：US16165172

申请日：2018-10-19

Applicant: United Technologies Corporation

Inventor： Gary J. Dillard ,  Assaf Farah

IPC: F23R3/00 ,  F02C7/18 ,  F23R3/06 ,  F02K3/06

Abstract: A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.

公开(公告)号：US11268444B2

公开(公告)日：2022-03-08

申请号：US15599149

申请日：2017-05-18

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  Jonathan Ortiz

IPC: F02C6/08 ,  F02C7/18 ,  F02C3/04 ,  F02C9/18 ,  F01D9/02 ,  F01D5/08 ,  F02K3/06

Abstract: A cooling system for a component of a gas turbine engine includes a first airflow passage configured to direct a first airflow to a mixing chamber and a second airflow passage to configured direct a second airflow to the mixing chamber, the second airflow having a higher temperature than the first airflow, and a cooling airflow passage to direct a cooling airflow from the mixing chamber to the component, the cooling airflow comprising the first airflow and the second airflow. The airflow passages are configured and sized to allow an amount of cooling airflow for unrestricted engine operation. When the first airflow passage is disabled, the second airflow passage and cooling airflow passage are configured and sized to allow an amount of cooling airflow which is adequate to permit continued safe engine operation restricted to within only a portion of its normal parameters and operating envelope.

公开(公告)号：US11262071B2

公开(公告)日：2022-03-01

申请号：US16520853

申请日：2019-07-24

Applicant: United Technologies Corporation

Inventor： Robin Prenter ,  Ryan Lundgreen

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/42

Abstract: A gas turbine engine, including: a diffuser case defining an inner shroud and an outer shroud; and a combustor housed within the diffuser case between the inner shroud and the outer shroud, the combustor including: a shell; a forward dome attached to the shell at a forward end of the combustor; and a deflector attached to the forward dome and extending away from the forward dome.

公开(公告)号：US11261748B2

公开(公告)日：2022-03-01

申请号：US16678549

申请日：2019-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Robert White, III

IPC: F01D9/04 ,  F01D5/18 ,  F01D5/28 ,  F01D11/00

Abstract: An airfoil vane assembly includes a vane piece defining a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform. The first vane platform defines a collar projection therefrom. A spar piece defines a spar platform and a spar extends from the spar platform into the hollow airfoil section. The spar platform includes a radial opening defined by first and second axial faces. The radial opening is configured to receive the collar projection, and a groove in the first axial face. A seal is situated in the groove. The seal seals against the collar projection and a biasing member is configured to bias the seal towards the collar projection. A method of assembling a vane is also disclosed.

公开(公告)号：US11261741B2

公开(公告)日：2022-03-01

申请号：US16678927

申请日：2019-11-08

Applicant: United Technologies Corporation

Inventor： Matthew B. Kennedy ,  Paul F. Croteau ,  John E. Holowczak ,  Thomas J. Martin

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/18

Abstract: An airfoil includes an airfoil body that has a trailing edge region. The trailing edge region includes first and second monolithic ceramic exterior walls, a flow discharge passage between the first and second monolithic ceramic exterior walls, a ceramic matrix composite (CMC) liner at least a portion of which is disposed in the flow discharge passage between the first and second monolithic ceramic exterior walls, and an array of pedestals disposed in the flow discharge passage. Each of the flow guides bridges the CMC liner and at least one of the first and second monolithic ceramic exterior walls.

公开(公告)号：US11255432B2

公开(公告)日：2022-02-22

申请号：US16375954

申请日：2019-04-05

Applicant: United Technologies Corporation

Inventor： Pantcho P. Stoyanov ,  Kelly M. Harrington

IPC: F16J9/26

Abstract: A piston seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a metal alloy binder phase and a hard particle phase distributed through the binder phase.