公开(公告)号：US11333036B2

公开(公告)日：2022-05-17

申请号：US16557046

申请日：2019-08-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley

IPC: B32B18/00 ,  F01D5/28 ,  F01D25/00 ,  F01D9/04 ,  F02C3/04 ,  C04B35/80

Abstract: An article includes a ceramic matrix composite wall that defines at least a side of a passage. The ceramic wall includes a ceramic matrix composite flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. The ceramic matric composite of the wall comprises woven fibers that are dispersed in a ceramic body matrix. An airfoil and a gas turbine engine are also disclosed.

公开(公告)号：US11319817B2

公开(公告)日：2022-05-03

申请号：US16821169

申请日：2020-03-17

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D5/18 ,  F01D9/04 ,  F04D29/54 ,  F04D29/38 ,  F04D29/58 ,  F02C7/18

Abstract: An airfoil includes a core structure that defines a cooling passage and first and second panels that are attached with the core structure. Each of the first and second panels includes an exterior gas path side, an opposed interior side, and a side edge. The side edge has a bearing portion that defines a bearing surface. The bearing surface of the first panel abuts the bearing surface of the second panel at a bearing interface. There are channels in the bearing portion of the first panel. Each of the channels has a first end that opens to the cooling passage and a second end that opens to the exterior gas path side at one of the side edges. Each of the channels is defined on a side by the bearing surface of the second panel.

公开(公告)号：US11268387B2

公开(公告)日：2022-03-08

申请号：US16239689

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr. ,  Steven Bruce Gautschi

IPC: F01D5/18 ,  F01D5/14 ,  B22C9/10 ,  F01D5/28

Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.

公开(公告)号：US11149573B2

公开(公告)日：2021-10-19

申请号：US16665339

申请日：2019-10-28

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D11/00 ,  F02C3/04 ,  F01D5/14 ,  F01D9/02 ,  F04D29/32 ,  F04D29/54 ,  F04D29/08 ,  F01D5/30 ,  F01D9/04 ,  F01D5/18 ,  F01D5/28

Abstract: An airfoil includes an endwall section and an airfoil section that defines, at least in part, an airfoil profile. The airfoil section includes an internal passage and a rib that sub-divides the internal passage. At least one of the rib or the endwall section includes a seal cavity. A seal is disposed in the seal cavity.

公开(公告)号：US11149556B2

公开(公告)日：2021-10-19

申请号：US16667949

申请日：2019-10-30

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D25/12

Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.

公开(公告)号：US20210285336A1

公开(公告)日：2021-09-16

申请号：US16815042

申请日：2020-03-11

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D25/12 ,  F01D25/14 ,  F01D25/24

Abstract: A gas turbine engine article includes an article wall that defines a cavity, a cooling passage network embedded between inner and outer portions of the article wall, and at least one conical passage through at least a portion of the inner portion of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, an outlet orifice through the outer portion of the article wall, and an intermediate region of passages that connects the inlet orifice to the outlet orifice. The conical passage has a first end that is proximate the cavity and a second end that opens at the intermediate region of passages.

公开(公告)号：US11092016B2

公开(公告)日：2021-08-17

申请号：US16589306

申请日：2019-10-01

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D9/02 ,  F01D5/14 ,  F01D9/06 ,  F02C3/04 ,  F01D25/00 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04

Abstract: An airfoil includes first and second endwalls and an airfoil section having a dual airfoil profile. The airfoil section includes a double wall that has an outer wall that defines a primary leading end of the dual airfoil profile and an inner wall spaced from the outer wall. The outer wall is trapped between the first and second endwalls in mortise and tenon joints, and the inner wall defines a secondary leading end of the dual airfoil profile.

公开(公告)号：US11041395B2

公开(公告)日：2021-06-22

申请号：US16453101

申请日：2019-06-26

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Emma J. Place ,  Timothy J. Jennings ,  Jeremy B. Fredette

IPC: F01D9/06 ,  F01D25/08 ,  F04D29/64

Abstract: Methods for forming airfoils, core assemblies, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly configured to define one or more internal cavities of the airfoil body, the core assembly comprising at least core structure having a purge slot protrusion extending from a portion of the core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket.

公开(公告)号：US10968753B1

公开(公告)日：2021-04-06

申请号：US16552450

申请日：2019-08-27

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Carey Clum ,  Timothy J. Jennings

IPC: F01D5/18 ,  F01D5/14

Abstract: Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.

公开(公告)号：US20200347738A1

公开(公告)日：2020-11-05

申请号：US16400618

申请日：2019-05-01

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Egon Salimusaj

IPC: F01D11/00

Abstract: A component for a gas turbine engine includes a first platform that has a first pair of circumferential surfaces and a first axially aft surface. A first axially extending seal slot is located in each of the first pair of circumferential surfaces and the first axially aft surface. A first cover plate is attached to the first axially aft surface and encloses at least a portion of the first axially extending seal slots.