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：US11242758B2

公开(公告)日：2022-02-08

申请号：US16679229

申请日：2019-11-10

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Adam P. Generale ,  Dominic J. Mongillo

IPC: F01D5/18 ,  F01D25/12

Abstract: An example airfoil vane according to the present disclosure includes an airfoil section including an outer wall that defines an internal cavity, and an insert situated in the internal cavity. A space is defined between the insert and the airfoil outer wall, the insert including an insert wall. A plurality of standoff features extend from the insert wall into the space and contact the airfoil outer wall at a contact area, whereby the standoff features are configured to block airflow in the space at the contact area and redirect the airflow to gaps between the standoff features. A gas turbine engine with the example airfoil vane and a method of assembling an airfoil vane are also disclosed.

公开(公告)号：US12044146B2

公开(公告)日：2024-07-23

申请号：US18123526

申请日：2023-03-20

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Richard Wesley Jackson ,  Adam P. Generale ,  Xuan Liu ,  Mark F. Zelesky

IPC: F01D5/28

CPC classification number: F01D5/288 ,  F01D5/284 ,  F05D2220/32 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2300/15 ,  F05D2300/21 ,  F05D2300/222 ,  F05D2300/30 ,  F05D2300/6033 ,  F05D2300/611 ,  F05D2300/6111

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

公开(公告)号：US20210054754A1

公开(公告)日：2021-02-25

申请号：US16868781

申请日：2020-05-07

Applicant: Raytheon Technologies Corporation

Inventor： Adam P. Generale ,  Dominic J. Mongillo, JR.

IPC: F01D9/06

Abstract: Airfoil assemblies for gas turbine engines are described. The airfoil assemblies include an airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, the airfoil body extending in a radial direction between a first end and a second end, wherein the airfoil defines an internal cavity bounded by interior surfaces of the airfoil body, the airfoil body formed from a high-temperature-material material and a metallic insert member installed within the internal cavity. One or more radially extending ribs are arranged on an exterior surface of the metallic insert member and defining one or more radially extending passages between the exterior surface of the metallic insert member and the interior surface of the airfoil body.

公开(公告)号：US20230250727A1

公开(公告)日：2023-08-10

申请号：US18123526

申请日：2023-03-20

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Richard Wesley Jackson ,  Adam P. Generale ,  Xuan Liu ,  Mark F. Zelesky

IPC: F01D5/28

CPC classification number: F01D5/288 ,  F01D5/284 ,  F05D2300/6033 ,  F05D2300/611 ,  F05D2300/30 ,  F05D2300/6111 ,  F05D2300/21 ,  F05D2240/306 ,  F05D2240/305 ,  F05D2300/222 ,  F05D2300/15 ,  F05D2220/32

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.

公开(公告)号：US11261749B2

公开(公告)日：2022-03-01

申请号：US16868781

申请日：2020-05-07

Applicant: Raytheon Technologies Corporation

Inventor： Adam P. Generale ,  Dominic J. Mongillo, Jr.

IPC: F01D9/06 ,  F01D5/18

Abstract: Airfoil assemblies for gas turbine engines are described. The airfoil assemblies include an airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, the airfoil body extending in a radial direction between a first end and a second end, wherein the airfoil defines an internal cavity bounded by interior surfaces of the airfoil body, the airfoil body formed from a high-temperature-material material and a metallic insert member installed within the internal cavity. One or more radially extending ribs are arranged on an exterior surface of the metallic insert member and defining one or more radially extending passages between the exterior surface of the metallic insert member and the interior surface of the airfoil body.

公开(公告)号：US11492914B1

公开(公告)日：2022-11-08

申请号：US17080969

申请日：2020-10-27

Applicant: Raytheon Technologies Corporation

Inventor： San Quach ,  Adam P. Generale ,  Raymond Surace ,  Lucas Dvorozniak

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/12 ,  F01D25/12

Abstract: A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.