公开(公告)号：US20190234222A1

公开(公告)日：2019-08-01

申请号：US15883959

申请日：2018-01-30

Applicant: United Technologies Corporation

Inventor： Colin G. Amadon ,  Nicholas Hunnewell

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D9/042 ,  F01D25/246 ,  F05D2220/321 ,  F05D2240/12 ,  F05D2250/38

Abstract: A stator vane arrangement may comprise a first shroud comprising a first side surface and a second side surface, a slot disposed in the first shroud, the slot at least partially defined by the first side surface and the second side surface, a stator vane extending at least partially through the slot, wherein the first side surface and the second side surface are disposed on opposite sides of the slot, and the first side surface is oriented at a first non-zero angle with respect to a radial direction.

公开(公告)号：US20180010470A1

公开(公告)日：2018-01-11

申请号：US15202795

申请日：2016-07-06

Applicant: United Technologies Corporation

Inventor： Paul W. Baumann ,  Colin G. Amadon ,  Steven J. Ford

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/3023 ,  F01D9/042 ,  F01D25/06 ,  F04D29/542 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2260/96 ,  F05D2300/43 ,  F05D2300/603

Abstract: A stator assembly for a gas turbine engine includes an annular outer shroud, an annular inner shroud radially spaced from the outer shroud and a plurality of stator vanes extending from the outer shroud to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat. A stator and case assembly for a gas turbine engine includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly located at the case. The stator assembly includes an annular outer shroud secured to the case, an annular inner shroud secured to the case and a plurality of stator vanes extending from the outer to the inner shroud. A volume of potting is located at the inner shroud and at the outer shroud to retain the plurality of stator vanes thereat.

公开(公告)号：US20190234241A1

公开(公告)日：2019-08-01

申请号：US15881069

申请日：2018-01-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Colin G. Amadon ,  Thomas Freeman

IPC: F01D25/24

CPC classification number: F01D25/24 ,  F01D9/04 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/14 ,  F05D2250/36 ,  F05D2260/30 ,  F05D2300/431 ,  F05D2300/50211 ,  F05D2300/6012 ,  F05D2300/603

Abstract: A gas turbine engine includes an annular structure disposed around an engine central longitudinal axis of the gas turbine engine. The annular structure defines an annular channel and comprises a first density, according to various embodiments. The gas turbine engine may further include a weight-saving filler disposed within the annular channel. The weight-saving filler may have a second density that is less than the first density. The gas turbine engine may further include an annular retention strap disposed around the engine central longitudinal axis of the gas turbine engine. The annular retention strap is at least partially embedded in the weight-saving filler, according to various embodiments.

公开(公告)号：US20190232472A1

公开(公告)日：2019-08-01

申请号：US15884879

申请日：2018-01-31

Applicant: United Technologies Corporation

Inventor： Thomas Freeman ,  Colin G. Amadon

IPC: B25B27/00

CPC classification number: B25B27/0092 ,  F01D11/005 ,  F01D25/24 ,  F01D25/246 ,  F01D25/285 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2240/57

Abstract: A tool for seating a wear liner into a first groove of a fan case of a gas turbine engine includes a body, a handle, and a first guide foot. The body includes a first end and a second end. The handle is connected to and extends from the body. The first guide foot is connected to and extends from the first end of the body. The first guide foot includes a first end connected to the body and a second end opposite from the first end of the first guide foot. The second end of the first guide foot is rounded and includes a chamfered portion.

公开(公告)号：US10344622B2

公开(公告)日：2019-07-09

申请号：US15216802

申请日：2016-07-22

Applicant: United Technologies Corporation

Inventor： Colin G. Amadon

IPC: F01D25/24 ,  F01D9/04 ,  F01D25/28 ,  F04D29/52 ,  F04D29/54 ,  F04D29/64

Abstract: An assembly for rotational equipment with an axial centerline. The assembly includes a first component and a second component. Each of the components extends circumferentially around and axially along the centerline. The first component includes a flange and a lug aperture extending axially through the flange. The second component includes a mount base and a bayoneted lug on the mount base. The mount base is configured to axially engage the flange where the bayoneted lug extends through the lug aperture. A fastener secures the components together. The fastener projects axially into a fastener aperture in the mount base for an axial length that is less than or equal to an axial length of the bayoneted lug.

公开(公告)号：US20180023420A1

公开(公告)日：2018-01-25

申请号：US15216802

申请日：2016-07-22

Applicant: United Technologies Corporation

Inventor： Colin G. Amadon

IPC: F01D25/24 ,  F04D29/64 ,  F04D29/54 ,  F04D29/52 ,  F01D9/04 ,  F01D25/28

CPC classification number: F01D25/246 ,  F01D9/041 ,  F01D25/243 ,  F01D25/28 ,  F04D29/522 ,  F04D29/542 ,  F04D29/644 ,  F05D2220/30 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2260/33 ,  F05D2260/36

Abstract: An assembly for rotational equipment with an axial centerline. The assembly includes a first component and a second component. Each of the components extends circumferentially around and axially along the centerline. The first component includes a flange and a lug aperture extending axially through the flange. The second component includes a mount base and a bayoneted lug on the mount base. The mount base is configured to axially engage the flange where the bayoneted lug extends through the lug aperture. A fastener secures the components together. The fastener projects axially into a fastener aperture in the mount base for an axial length that is less than or equal to an axial length of the bayoneted lug.

公开(公告)号：US20170306796A1

公开(公告)日：2017-10-26

申请号：US15136130

申请日：2016-04-22

Applicant: United Technologies Corporation

Inventor： Colin G. Amadon

IPC: F01D25/24 ,  F01D9/04

Abstract: A stator includes a plurality of stator vanes and a shroud operably connected to the stator vanes. The shroud includes one or more positioning tabs configured to engage one or more corresponding alignment features of a mating component to radially position the shroud at the mating component, the one or more shroud positioning tabs position the outer shroud to define a radial tip clearance between an outer shroud and an adjacent rotor of the gas turbine engine. A gas turbine engine includes a stator and case assembly in fluid communication with a combustor. The stator and case assembly includes a stator located at a case. The stator has a plurality of stator vanes and a shroud including one or more positioning tabs configured to engage one or more corresponding case alignment features to radially position the shroud at the case.

公开(公告)号：US10648479B2

公开(公告)日：2020-05-12

申请号：US15797577

申请日：2017-10-30

Applicant: United Technologies Corporation

Inventor： Colin G. Amadon ,  Anthony R. Bifulco

IPC: F04D29/08 ,  F01D9/04 ,  F01D11/00 ,  F04D29/54

Abstract: A vane assembly for a gas turbine includes a first shroud segment, a second shroud segment, a first inner air seal, and a seal assembly. The first shroud segment has a first end face. The second shroud segment is disposed adjacent to the first shroud segment and has a second end face that faces towards and is spaced apart from the first end face by a gap. The first inner air seal extends into the first shroud segment and defines a first trench. The seal assembly at least partially received within the first trench.

公开(公告)号：US10472979B2

公开(公告)日：2019-11-12

申请号：US15239921

申请日：2016-08-18

Applicant: United Technologies Corporation

Inventor： Dene A. Montgomery ,  Colin G. Amadon

IPC: F01D9/04 ,  F01D25/06 ,  F01D25/24

Abstract: A stator assembly for a gas turbine engine includes an arcuate shroud including a shroud pocket, the shroud pocket having a shroud slot extending therethrough. A stator vane is insertable into the shroud pocket and includes a vane slot extending therethrough. A strap extends through the shroud slot and the vane slot to retain the vane to the shroud. A gas turbine engine includes a combustor and a stator and case assembly in in fluid communication with the combustor. The stator and case assembly includes a case defining a working fluid flowpath for the gas turbine engine and a stator assembly secured at the case.

公开(公告)号：US20190128274A1

公开(公告)日：2019-05-02

申请号：US15797577

申请日：2017-10-30

Applicant: United Technologies Corporation

Inventor： Colin G. Amadon ,  Anthony R. Bifulco

IPC: F04D29/08 ,  F04D29/54

Abstract: A vane assembly for a gas turbine includes a first shroud segment, a second shroud segment, a first inner air seal, and a seal assembly. The first shroud segment has a first end face. The second shroud segment is disposed adjacent to the first shroud segment and has a second end face that faces towards and is spaced apart from the first end face by a gap. The first inner air seal extends into the first shroud segment and defines a first trench. The seal assembly at least partially received within the first trench.