公开(公告)号：US10563512B2

公开(公告)日：2020-02-18

申请号：US15793415

申请日：2017-10-25

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Carey Clum

IPC: F01D5/14

Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of leading edge radius to maximum thickness is between 0.40 (r/Tmax) and 0.45 (r/Tmax) and a ratio of leading edge radius to axial chord length is between 0.17 (r/bx) and 0.27 (r/bx).

公开(公告)号：US20200024984A1

公开(公告)日：2020-01-23

申请号：US16225944

申请日：2018-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Andrew S. Aggarwala ,  Timothy Charles Nash ,  Eunice Allen-Bradley ,  Eric A. Grover

IPC: F01D9/02 ,  F01D5/14 ,  F04D29/68 ,  F04D29/54 ,  F04D29/32

Abstract: An airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.

公开(公告)号：US10508550B2

公开(公告)日：2019-12-17

申请号：US15793454

申请日：2017-10-25

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Loubriel Ramirez

IPC: F01D5/14 ,  F04D29/68 ,  F04D29/52 ,  F01D9/04

Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extends along an axially chord between a leading edge and a trailing edge. A first profiled region is recessed into the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil. A third profiled region is recessed into the endwall along adjacent the leading edge of the second side of the second airfoil. The third profiled region is at least partially axially aligned with the second profiled region.

公开(公告)号：US20190120058A1

公开(公告)日：2019-04-25

申请号：US15793415

申请日：2017-10-25

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Carey Clum

IPC: F01D5/14

Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of leading edge radius to maximum thickness is between 0.40 (r/Tmax) and 0.45 (r/Tmax) and a ratio of leading edge radius to axial chord length is between 0.17 (r/bx) and 0.27 (r/bx).

公开(公告)号：US20190106989A1

公开(公告)日：2019-04-11

申请号：US15727683

申请日：2017-10-09

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash

IPC: F01D5/14 ,  F01D5/16

Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner portion of the platform. An airfoil extends from the radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A bowed tip portion extends perpendicular to a mid-camber line of the airfoil.

公开(公告)号：US09938854B2

公开(公告)日：2018-04-10

申请号：US14712067

申请日：2015-05-14

Applicant: United Technologies Corporation

Inventor： Alex J. Simpson ,  Timothy Charles Nash

IPC: F01D25/06 ,  F01D9/04 ,  F01D5/14 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F01D5/10 ,  F01D1/02 ,  F01D5/02

CPC classification number: F01D25/06 ,  F01D1/02 ,  F01D5/02 ,  F01D5/10 ,  F01D5/141 ,  F01D5/143 ,  F01D5/145 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F01D9/04 ,  F01D9/041 ,  F01D9/047 ,  F05D2220/32 ,  F05D2260/96 ,  Y02T50/673

Abstract: A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.