公开(公告)号：US20160201492A1

公开(公告)日：2016-07-14

申请号：US14955808

申请日：2015-12-01

Applicant: United Technologies Corporation

Inventor： Jin Hu

IPC: F01D9/06 ,  F01D25/12 ,  F01D9/04

CPC classification number: F01D9/041 ,  F01D5/081 ,  F05D2240/126 ,  F05D2240/129 ,  F05D2250/74 ,  F05D2260/14 ,  Y02T50/673 ,  Y02T50/676

Abstract: A tangential on-board injection (TOBI) system for gas turbine engines includes a first endwall and a second endwall radially spaced apart from the first endwall. A plurality of airfoils extend radially from the first endwall to the second endwall. Each airfoil has a leading edge and a trailing edge. Each airfoil includes a first fillet portion transitioning between the airfoil and the first endwall and a second fillet portion transitioning between the airfoil and the second endwall. The radius of curvature of the first and second fillet portions proximate to the leading edge of the airfoil is larger than the radius of curvature of the first and second fillet portions proximate to the trailing edge.

Abstract translation: 用于燃气涡轮发动机的切向机载喷射（TOBI）系统包括第一端壁和与第一端壁径向间隔开的第二端壁。 多个翼型件从第一端壁径向延伸到第二端壁。 每个翼型件具有前缘和后缘。 每个翼型件包括在翼型件和第一端壁之间过渡的第一圆角部分和在翼型件和第二端壁之间转换的第二圆角部分。 靠近翼型的前缘的第一和第二圆角部分的曲率半径大于靠近后缘的第一和第二圆角部分的曲率半径。

公开(公告)号：US20160007474A1

公开(公告)日：2016-01-07

申请号：US14790886

申请日：2015-07-02

Applicant: United Technologies Corporation ,  Goodrich Corporation

Inventor： Sameh Dardona ,  Michael P. Humbert ,  John P. Wesson ,  Wayde R. Schmidt ,  Daniel V. Viens ,  Jin Hu

IPC: H05K3/00 ,  H05B3/06 ,  H05B3/02 ,  H05K3/30 ,  H05B3/12 ,  H05B3/26 ,  H05K3/12 ,  H05B3/00 ,  H05B3/16

CPC classification number: H05K3/0014 ,  B33Y80/00 ,  H05B3/0014 ,  H05B3/06 ,  H05B3/12 ,  H05B3/145 ,  H05B3/16 ,  H05B3/265 ,  H05B3/267 ,  H05B3/34 ,  H05B3/84 ,  H05B2203/003 ,  H05B2203/013 ,  H05B2203/017 ,  H05B2214/02 ,  H05B2214/04 ,  H05K3/12 ,  H05K3/30

Abstract: A heating circuit assembly and method of manufacture includes an electrically conductive heating element having a pattern. An electrically non-conductive substrate is additive manufactured and secured to the element for structural support. The substrate has a topology that generally aligns with the pattern of the element thereby reducing the assembly weight and minimizing substrate material waste.

Abstract translation: 加热电路组件及其制造方法包括具有图案的导电加热元件。 非导电基材是制造并固定到用于结构支撑的元件的添加剂。 衬底具有通常与元件的图案对准的拓扑，从而减少组件重量并使衬底材料浪费最小化。

公开(公告)号：US11473434B2

公开(公告)日：2022-10-18

申请号：US16654380

申请日：2019-10-16

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Gary A. Zess ,  Eric A. Grover ,  Jin Hu

IPC: F01D5/14 ,  F01D9/02

Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.

公开(公告)号：US10440829B2

公开(公告)日：2019-10-08

申请号：US14790886

申请日：2015-07-02

Applicant: United Technologies Corporation ,  Goodrich Corporation

Inventor： Sameh Dardona ,  Michael P. Humbert ,  John P. Wesson ,  Wayde R. Schmidt ,  Daniel V. Viens ,  Jin Hu

IPC: H05K3/00 ,  H05B3/12 ,  H05B3/14 ,  H05B3/26 ,  H05B3/34 ,  H05B3/84 ,  H05B3/00 ,  H05B3/06 ,  H05B3/16 ,  H05K3/12 ,  H05K3/30 ,  B33Y80/00

Abstract: A heating circuit assembly and method of manufacture includes an electrically conductive heating element having a pattern. An electrically non-conductive substrate is additive manufactured and secured to the element for structural support. The substrate has a topology that generally aligns with the pattern of the element thereby reducing the assembly weight and minimizing substrate material waste.

公开(公告)号：US10221708B2

公开(公告)日：2019-03-05

申请号：US14955808

申请日：2015-12-01

Applicant: United Technologies Corporation

Inventor： Jin Hu

IPC: F01D9/04 ,  F01D5/08

Abstract: A tangential on-board injection (TOBI) system for gas turbine engines includes a first endwall and a second endwall radially spaced apart from the first endwall. A plurality of airfoils extend radially from the first endwall to the second endwall. Each airfoil has a leading edge and a trailing edge. Each airfoil includes a first fillet portion transitioning between the airfoil and the first endwall and a second fillet portion transitioning between the airfoil and the second endwall. The radius of curvature of the first and second fillet portions proximate to the leading edge of the airfoil is larger than the radius of curvature of the first and second fillet portions proximate to the trailing edge.

公开(公告)号：US20210115803A1

公开(公告)日：2021-04-22

申请号：US16654380

申请日：2019-10-16

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Gary A. Zess ,  Eric A. Grover ,  Jin Hu

IPC: F01D9/02

Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.

公开(公告)号：US10808540B2

公开(公告)日：2020-10-20

申请号：US15928133

申请日：2018-03-22

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Curtis L. Memory ,  Jin Hu ,  Thomas J. Praisner

IPC: F01D5/14 ,  F15D1/00 ,  F01D9/06 ,  F01D9/04 ,  F01D25/24 ,  F01D25/30

Abstract: A strut for a gas turbine engine includes an airfoil section extending in a spanwise direction between a first platform and a second platform, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width. Exterior surfaces of the airfoil section define a leading portion between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge. The exterior surfaces establish a respective exterior contour for each span position between a 0% span position and a 100% span position. The exterior surfaces define a plurality of dimples in the leading portion.

公开(公告)号：US20200248574A1

公开(公告)日：2020-08-06

申请号：US16267955

申请日：2019-02-05

Applicant: United Technologies Corporation

Inventor： Angela C. Reisch ,  Carson A. Roy Thill ,  Dairus Deylan McDowell ,  Jin Hu ,  Jeremy Drake ,  Gregory A. O'Connor ,  David M. Pons ,  Katelyn Kwoka

IPC: F01D9/04 ,  F01D9/02

Abstract: An on-board injector for delivering discharge air toward a turbine rotor of a gas turbine engine. The on-board injector having: a first wall; a second wall spaced from said first wall to define an annular inlet and an annular exit, wherein the first wall has a first length and the second wall has a second length; and a plurality of airfoils extending between the first wall and the second wall to segregate discharge air from the annular inlet, wherein each of the plurality of airfoils extend from the annular inlet and the annular exit and completely across the first length and the second length.

公开(公告)号：US20190292915A1

公开(公告)日：2019-09-26

申请号：US15928133

申请日：2018-03-22

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Curtis L. Memory ,  Jin Hu ,  Thomas J. Praisner

IPC: F01D5/14 ,  F01D25/24 ,  F01D9/04 ,  F15D1/00

Abstract: A strut for a gas turbine engine includes an airfoil section extending in a spanwise direction between a first platform and a second platform, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width. Exterior surfaces of the airfoil section define a leading portion between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge. The exterior surfaces establish a respective exterior contour for each span position between a 0% span position and a 100% span position. The exterior surfaces define a plurality of dimples in the leading portion.