公开(公告)号：US11959397B2

公开(公告)日：2024-04-16

申请号：US17857337

申请日：2022-07-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18

CPC classification number: F01D5/187

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

公开(公告)号：US20220349311A1

公开(公告)日：2022-11-03

申请号：US17857337

申请日：2022-07-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

公开(公告)号：US11486257B2

公开(公告)日：2022-11-01

申请号：US16856558

申请日：2020-04-23

Applicant: Raytheon Technologies Corporation

Inventor： Allan N. Arisi ,  Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18

Abstract: A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.

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：US11203981B1

公开(公告)日：2021-12-21

申请号：US16986493

申请日：2020-08-06

Applicant: Raytheon Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Allan N. Arisi

IPC: F02C7/28 ,  F02C3/04 ,  F01D5/18

Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body having a pressure and suction side walls and an internal rib and defining a cavity between, at least, the pressure side wall, the suction side wall, and the internal rib. A baffle insert is arranged within the cavity and includes a sealing portion arranged adjacent to the internal rib of the airfoil body with a gap therebetween. A seal element is arranged within the cavity and located in the gap. The seal element is free to move relative to each of the baffle insert and the airfoil body within the gap. When a pressure differential exists across the seal element, the seal element will sealingly engage between sealing portion of the baffle insert and the internal rib of the airfoil body to block a flow through the gap.

公开(公告)号：US10968752B2

公开(公告)日：2021-04-06

申请号：US16373008

申请日：2019-04-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： James Tilsley Auxier ,  Tracy A. Propheter-Hinckley ,  Allan N. Arisi

IPC: F01D5/18

Abstract: A turbine airfoil includes an airfoil outer wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. At least one cooling passage is embedded in the airfoil outer wall and has a radially-elongated entrance manifold, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice. The radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold.