公开(公告)号：US10151204B2

公开(公告)日：2018-12-11

申请号：US15042840

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： David P. Houston ,  Tracy A. Propheter-Hinckley ,  Benjamin T. Fisk ,  Anita L. Tracy

IPC: F01D5/16 ,  B22F3/105 ,  B22F5/04 ,  F01D9/04 ,  F01D25/04 ,  F04D29/38 ,  F04D29/54 ,  F04D29/66 ,  B22F5/10

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.

公开(公告)号：US20180347373A1

公开(公告)日：2018-12-06

申请号：US16000239

申请日：2018-06-05

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo

IPC: F01D5/18 ,  F01D9/04 ,  F04D29/58 ,  F01D25/12 ,  F01D9/02 ,  F04D29/52 ,  F01D11/08

CPC classification number: F01D5/186 ,  F01D9/02 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  F04D29/526 ,  F04D29/5846 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/30 ,  F05D2250/28 ,  F05D2260/202 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  Y02T50/673 ,  Y02T50/676

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.

公开(公告)号：US10099275B2

公开(公告)日：2018-10-16

申请号：US14670566

申请日：2015-03-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley

IPC: B22C9/10 ,  F01D25/12 ,  F01D5/18 ,  B22C9/04 ,  B22C21/14 ,  B22C9/24 ,  F01D5/16

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a first cavity, a second cavity and a rib between the first cavity and the second cavity, the rib including a first rib surface that is substantially flat and a second rib surface that is tapered.

公开(公告)号：US20180274373A1

公开(公告)日：2018-09-27

申请号：US15995884

申请日：2018-06-01

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D5/20 ,  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 for a gas turbine engine 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 extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.

公开(公告)号：US20180258772A1

公开(公告)日：2018-09-13

申请号：US15979997

申请日：2018-05-15

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Stephanie Santoro

IPC: F01D5/18 ,  B22C9/10 ,  B22C9/24 ,  B22D25/02 ,  F01D9/04

CPC classification number: F01D5/18 ,  B22C9/103 ,  B22C9/24 ,  B22D25/02 ,  F01D5/186 ,  F01D9/041 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/204 ,  Y10T29/49337

Abstract: A process for providing cooling fluid holes in an airfoil portion of a turbine engine component comprising: positioning a first core with metering/tripping features that form a row of protrusions, and teardrop features that form a fluid passageways, the teardrop features including a central teardrop feature having a trailing edge, a first teardrop feature located on a first side of and spaced from the central teardrop feature, the first teardrop feature having a longitudinal axis and being non-symmetrical about the longitudinal axis, and a second teardrop feature located on a second side of and spaced from the central teardrop feature, the second teardrop feature having a longitudinal axis and non-symmetrical about the longitudinal axis; joining the core to a ceramic core; forming the turbine engine component; removing the core, forming a cooling microcircuit with fluid outlets; and drilling a central portion of the cooling microcircuit forming a converging/diverging outlet.

公开(公告)号：US10047629B2

公开(公告)日：2018-08-14

申请号：US14763719

申请日：2013-01-28

Applicant: United Technologies Corporation

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

IPC: F01D17/16 ,  F01D9/04 ,  F02C9/22 ,  F01D5/14 ,  F01D9/06

Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is 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 at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.

公开(公告)号：US10041358B2

公开(公告)日：2018-08-07

申请号：US14696601

申请日：2015-04-27

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  San Quach

IPC: F01D5/18 ,  F01D5/20

Abstract: A blade for a gas turbine engine includes an airfoil having a tip with a terminal end surface and multiple squealer pockets recessed into the terminal end surface. A method of cooling a blade includes the steps of providing cooling fluid to a first squealer pocket in an airfoil tip, and providing cooling fluid to a second squealer pocket in the airfoil tip in an amount that is different than that provided to the first squealer pocket.

公开(公告)号：US20180135459A1

公开(公告)日：2018-05-17

申请号：US15354132

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D25/12 ,  F02C3/04 ,  F01D5/18 ,  F01D9/02 ,  F01D11/00 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F04D29/08

Abstract: An airfoil includes a supply passage to provide a coolant, an airfoil section that has walls that define an internal cavity, a baffle seated in the internal cavity, and a seal proximate the edge of the baffle. The baffle is seated such that there is a gap between the baffle and at least one of the walls. The baffle includes a baffle wall that has cooling holes and that defines an interior baffle region. The seal seals off the gap such that the coolant that exits the supply passage will be directed to flow into the interior baffle region.

公开(公告)号：US20180135442A1

公开(公告)日：2018-05-17

申请号：US15354150

申请日：2016-11-17

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

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

CPC classification number: F01D9/02 ,  F01D5/18 ,  F01D5/284 ,  F01D5/3084 ,  F01D5/3092 ,  F01D9/041 ,  F01D9/042 ,  F01D9/044 ,  F01D11/003 ,  F01D25/246 ,  F04D29/083 ,  F04D29/324 ,  F04D29/542 ,  F05D2220/32 ,  F05D2230/51 ,  F05D2230/60 ,  F05D2240/10 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/80 ,  F05D2260/52 ,  F05D2300/10 ,  F05D2300/20 ,  F05D2300/21 ,  Y02T50/672

Abstract: An airfoil includes an airfoil section that has an internal cavity and first and second endwall sections between which the airfoil section is disposed. The first endwall section includes a guide portion that has a guide opening flanked by first and second bearing lands. The first bearing land is between the guide opening and a first port in the first endwall section that opens to the internal cavity of the airfoil section. The second bearing land is between the guide opening and a second port in the first endwall section that also opens to the internal cavity. A tie member extends through the internal cavity and secures the first and second endwall sections together to trap the airfoil section. The tie member extends through the guide opening in the first endwall section. A spring member on the first and second bearing lands tensions the tie member.

公开(公告)号：US20180135437A1

公开(公告)日：2018-05-17

申请号：US15354055

申请日：2016-11-17

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/28 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F04D29/38 ,  F04D29/54 ,  B23P15/04

CPC classification number: F01D5/284 ,  B23P15/04 ,  B32B18/00 ,  C04B2235/6028 ,  C04B2237/38 ,  C04B2237/62 ,  C04B2237/84 ,  F01D5/147 ,  F01D5/187 ,  F01D5/282 ,  F01D9/041 ,  F01D9/042 ,  F01D9/065 ,  F01D25/12 ,  F04D29/388 ,  F04D29/542 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.