公开(公告)号：US20190091759A1

公开(公告)日：2019-03-28

申请号：US16106294

申请日：2018-08-21

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  James T. Auxier ,  Eric A. Hudson

IPC: B22C9/10 ,  B22C21/14

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

公开(公告)号：US10215048B2

公开(公告)日：2019-02-26

申请号：US14762302

申请日：2013-01-21

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Raymond Surace ,  Tracy A. Propheter-Hinckley

IPC: F01D17/16 ,  F01D5/14 ,  F01D5/18

Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.

公开(公告)号：US20190024530A1

公开(公告)日：2019-01-24

申请号：US15653064

申请日：2017-07-18

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Raymond Surace ,  Robert L. Hazzard ,  Mark Borja

IPC: F01D17/16

CPC classification number: F01D17/162 ,  F05D2230/60 ,  F05D2240/128 ,  F05D2260/30 ,  F05D2260/50

Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.

公开(公告)号：US20190003333A1

公开(公告)日：2019-01-03

申请号：US16112451

申请日：2018-08-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Lane M. Thornton

IPC: F01D17/12 ,  F16K15/16 ,  F01D5/18 ,  F01D17/10 ,  F01D25/12 ,  F01D9/02 ,  F16K31/00

Abstract: A thermally driven spring valve for turbine gas path parts is disclosed herein. A thermally driven spring valve includes a bimetallic sheet comprising a base, a first finger portion extending from the base and a second finger portion extending from the base, the first finger portion having a first curvature vector and the second finger portion have a second curvature vector, wherein an exterior surface extends from the base through the first finger portion and the second finger portion and an interior surface extends from the base through the first finger portion and the second finger portion, wherein the exterior surface of the first finger portion is disposed proximate the interior surface of the base wherein the exterior surface of the second finger portion is disposed proximate the interior surface of the base. A thermally driven spring valve may include perforations through a finger portion.

公开(公告)号：US20180334909A1

公开(公告)日：2018-11-22

申请号：US16048466

申请日：2018-07-30

Applicant: United Technologies Corporation

Inventor： Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky ,  Joel H. Wagner ,  Thomas N. Slavens

IPC: F01D5/18 ,  F23R3/00 ,  B22F3/105 ,  B23P15/26 ,  F01D5/14 ,  F02C7/18 ,  F01D25/24 ,  F01D25/12 ,  F01D25/08 ,  F01D11/08 ,  F01D9/02 ,  B33Y80/00 ,  B33Y70/00 ,  B33Y10/00

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.

公开(公告)号：US20180320548A1

公开(公告)日：2018-11-08

申请号：US16033356

申请日：2018-07-12

Applicant: United Technologies Corporation

Inventor： Michael F. Blair ,  Tracy A. Propheter-Hinckley ,  Mark F. Zelesky

IPC: F01D25/12 ,  F28F7/02 ,  F28F1/40 ,  F01D25/10 ,  F28D15/00 ,  F02C7/14 ,  F28F1/12

CPC classification number: F01D25/12 ,  F01D25/10 ,  F02C7/14 ,  F05D2260/205 ,  F05D2260/213 ,  F05D2260/232 ,  F28D15/00 ,  F28F1/124 ,  F28F1/40 ,  F28F7/02 ,  F28F2255/18 ,  Y02T50/676

Abstract: A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.

公开(公告)号：US20180283195A1

公开(公告)日：2018-10-04

申请号：US15475656

申请日：2017-03-31

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Raymond Surace ,  Renee J. Jurek ,  Tracy A. Propheter-Hinckley

IPC: F01D11/20 ,  F02C3/04 ,  F01D5/02 ,  F02C9/18 ,  F04D29/54

CPC classification number: F01D11/20 ,  F01D5/02 ,  F01D9/065 ,  F01D11/24 ,  F02C3/04 ,  F02C9/18 ,  F04D29/542 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213 ,  F05D2300/50212 ,  Y02T50/676

Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.

公开(公告)号：US10036264B2

公开(公告)日：2018-07-31

申请号：US14896738

申请日：2014-06-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey ,  Tracy A. Propheter-Hinckley ,  Raymond Surace

IPC: F01D5/14 ,  F01D9/02 ,  F01D17/16 ,  F04D29/38 ,  F02C7/20 ,  F01D5/30 ,  F01D5/18

CPC classification number: F01D9/02 ,  F01D5/18 ,  F01D17/162 ,  F05D2230/60 ,  F05D2260/201 ,  F05D2300/20

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a shell defining an interior, a spar extending into the interior and a first flange attached to the spar. The spar is configured to pivot to change a positioning of the shell.

公开(公告)号：US10012089B2

公开(公告)日：2018-07-03

申请号：US14704022

申请日：2015-05-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Steven Bruce Gautschi

IPC: F01D5/20 ,  F01D5/18 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/186 ,  F01D5/20 ,  F05D2220/32 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge. The airfoil extends to a tip. A tip pocket is formed in the tip and terminates prior to the trailing edge. A heat transfer augmentation device is formed in the tip pocket.

公开(公告)号：US20180135452A1

公开(公告)日：2018-05-17

申请号：US15354243

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D11/00 ,  F01D5/12 ,  F01D9/02 ,  F04D29/32 ,  F04D29/54 ,  F04D29/08 ,  F02C3/04

Abstract: An airfoil includes an airfoil structure that defines a portion of an airfoil profile and a panel that defines a different portion of the airfoil profile. The panel has perimeter edges that meet the airfoil structure in a perimeter joint, and there is a perimeter seal disposed in the perimeter joint.