公开(公告)号：US20190186739A1

公开(公告)日：2019-06-20

申请号：US16210434

申请日：2018-12-05

Applicant: United Technologies Corporation

Inventor： Dennis M. Moura ,  Carey Clum

IPC: F23R3/00 ,  F23M5/08

CPC classification number: F23R3/002 ,  F01D5/189 ,  F01D9/065 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/607 ,  F23M5/08 ,  F23R3/005 ,  F23R2900/00004 ,  F23R2900/03042 ,  F23R2900/03044

Abstract: A gas turbine engine component assembly comprising: a first component having a first surface, a second surface opposite the first surface, a first cooling hole located in a first section of the first component extending from the second surface to first surface, and a second cooling hole located in a second section of the first component extending from the second surface to first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; wherein the first cooling hole is configured to direct at least one of the airflow and the particulate to impinge upon the second surface of the second component at first directional flow angle.

公开(公告)号：US20190048729A1

公开(公告)日：2019-02-14

申请号：US15671351

申请日：2017-08-08

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D5/14 ,  F01D9/02 ,  F01D25/12

Abstract: Airfoils including an airfoil body having leading and trailing edges and root and tip regions, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from the root region to the tip region, a forward-flowing serpentine flow path within the airfoil body defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity, a flag tip cavity extending aftward from proximate the leading edge to the trailing edge along the tip region, and a hybrid trailing edge cavity, wherein the first serpentine cavity is part of the hybrid trailing edge cavity and cooling air is supplied into the forward-flowing serpentine flow path from a hybrid trailing edge feed cavity inlet.

公开(公告)号：US10196902B2

公开(公告)日：2019-02-05

申请号：US14854606

申请日：2015-09-15

Applicant: United Technologies Corporation

Inventor： Sasha M. Moore ,  Timothy J. Jennings ,  Thomas N. Slavens ,  Clifford J. Musto ,  Nicholas M. LoRicco ,  Carey Clum ,  John McBrien ,  Christopher Whitfield ,  San Quach

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F04D29/32 ,  F01D9/06

Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.

公开(公告)号：US20190024514A1

公开(公告)日：2019-01-24

申请号：US15656020

申请日：2017-07-21

Applicant: United Technologies Corporation

Inventor： Charles Thistle ,  Evan P. Molony ,  Carey Clum

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

Abstract: Airfoils and airfoil cores for airfoils of gas turbine engines are provided. The airfoils include an airfoil body having a leading edge and a trailing edge, at least two serpentine flow cavities formed within the airfoil body, a resupply cavity fluidly connected to one serpentine flow cavity of the at least two serpentine flow cavities and arranged to supply a resupply air to the one serpentine flow cavity through a resupply bypass hole, a junction defined at a location where the resupply cavity fluidly connect to the one serpentine flow cavity, a separator rib within the airfoil body and fluidly separating part of the at least two serpentine flow cavities, at least one crossover rib located between the resupply bypass hole and the separator rib, and at least one crossover aperture located between the at least one crossover rib and the separator rib.

公开(公告)号：US20180347381A1

公开(公告)日：2018-12-06

申请号：US15607998

申请日：2017-05-30

Applicant: United Technologies Corporation

Inventor： Evan P. Molony ,  Carey Clum ,  Wolfgang Balzer

IPC: F01D5/30 ,  F01D9/04 ,  F01D5/14

CPC classification number: F01D5/3015 ,  F01D5/141 ,  F01D5/143 ,  F01D5/145 ,  F01D5/147 ,  F01D9/041 ,  F01D9/042 ,  F01D11/006 ,  F05B2240/301 ,  F05B2240/80 ,  F05D2240/11 ,  F05D2240/80

Abstract: A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.

公开(公告)号：US20180320525A1

公开(公告)日：2018-11-08

申请号：US15584119

申请日：2017-05-02

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo

IPC: F01D5/14 ,  F01D5/18

Abstract: Airfoils having a leading edge, a trailing edge, a first end, and a second end with a leading edge hybrid skin core cavity formed within the airfoil extending from the first end to the second end proximate the leading edge, the cavity having a hot wall and a cold wall. The cavity has a variable height-to-width ratio in a direction from the first end to the second end, with a first aspect ratio proximate the first end and a second aspect ratio proximate the second end with the height defined as a maximum distance between the hot wall and the cold wall and the width is defined as an arc length of the cold wall.

公开(公告)号：US20180156049A1

公开(公告)日：2018-06-07

申请号：US15368829

申请日：2016-12-05

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/187 ,  F01D5/20 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/125 ,  F05D2240/126 ,  Y02T50/673

Abstract: An airfoil includes an airfoil body having a first wall, a second wall, a third wall, a tip surface, and a rib. The first wall radially extends between a root region and a tip region and axially extends between a leading edge and a trailing edge. The second wall radially extends from the tip region towards the root region and axially extends between the leading edge and the trailing edge. The third wall radially extends between the root region and the tip region and axially extends between the leading edge and the trailing edge. The tip surface circumferentially extends between the second wall and the third wall. The rib is radially spaced apart from the tip surface and circumferentially extends between the first wall and the third wall.

公开(公告)号：US20180156045A1

公开(公告)日：2018-06-07

申请号：US15368746

申请日：2016-12-05

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D5/14

Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom having an aft flowing serpentine hybrid skin core positioned relative to a plurality of core bodies and configured to define at least one serpentine cavity within the manufactured airfoil. The aft flowing serpentine hybrid skin core extends from a root region toward a tip region in a radial direction of the manufactured airfoil and the plurality of core bodies are positioned about the aft flowing serpentine hybrid skin core to form a shielding structure to thermally shield the aft flowing serpentine hybrid skin core in the manufactured airfoil.

公开(公告)号：US20180156043A1

公开(公告)日：2018-06-07

申请号：US15368737

申请日：2016-12-05

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Dominic J. Mongillo, JR.

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  B22C9/04 ,  B22C9/10

Abstract: Core assemblies for manufacturing airfoils and airfoils made therefrom, the core assemblies having a leading edge hybrid skin core positioned relative to a plurality of core bodies and configured to define a leading edge cavity at a leading edge of the manufactured airfoil. The leading edge hybrid skin core extends from a root region toward a tip region in a radial direction, the leading edge hybrid skin core extends above at least one of the plurality of core bodies to define an exit in a tip region of the manufactured airfoil, and the leading edge hybrid skin core has a height-to-width ratio of about 0.8 or less.

公开(公告)号：US20170159447A1

公开(公告)日：2017-06-08

申请号：US14961221

申请日：2015-12-07

Applicant: United Technologies Corporation

Inventor： Carey Clum ,  Timothy J. Jennings

IPC: F01D5/14 ,  F01D25/30 ,  F01D11/08 ,  F02C7/18 ,  B23K15/00 ,  F01D9/02 ,  F01D25/12 ,  B22C9/10 ,  B22D25/02 ,  B22F3/105 ,  F01D5/18 ,  F23R3/00

CPC classification number: F01D5/147 ,  B22C9/108 ,  B22D25/02 ,  B22F3/1055 ,  B23K15/0086 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/186 ,  F01D5/187 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F01D25/30 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2260/202 ,  F05D2260/204 ,  F23R3/002 ,  Y02T50/673 ,  Y02T50/676

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 includes a plurality of nodes, a plurality of branches that extend between the plurality of nodes, and a plurality of passages extending between the plurality of nodes and the plurality of passages. Further, at least one of the branches is non-circular in cross-section.