公开(公告)号：US20220213798A1

公开(公告)日：2022-07-07

申请号：US17706761

申请日：2022-03-29

Applicant: General Electric Company

Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

IPC: F01D9/04 ,  F04D29/54 ,  F01D11/00 ,  F01D9/02

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

公开(公告)号：US20200025002A1

公开(公告)日：2020-01-23

申请号：US16377398

申请日：2019-04-08

Applicant: General Electric Company

Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

IPC: F01D9/04 ,  F04D29/54 ,  F01D11/00 ,  F01D9/02

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

公开(公告)号：US11286799B2

公开(公告)日：2022-03-29

申请号：US16377398

申请日：2019-04-08

Applicant: General Electric Company

Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

IPC: F01D9/04 ,  F04D29/54 ,  F01D11/00 ,  F01D9/02

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

公开(公告)号：US20180238185A1

公开(公告)日：2018-08-23

申请号：US15440294

申请日：2017-02-23

Applicant: General Electric Company

Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

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

CPC classification number: F01D9/044 ,  F01D9/023 ,  F01D11/005 ,  F04D29/54 ,  F05D2240/12 ,  Y02T50/672

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

公开(公告)号：US11828199B2

公开(公告)日：2023-11-28

申请号：US17706761

申请日：2022-03-29

Applicant: General Electric Company

Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

IPC: F01D9/04 ,  F04D29/54 ,  F01D11/00 ,  F01D9/02

CPC classification number: F01D9/044 ,  F01D9/023 ,  F01D11/005 ,  F04D29/54 ,  F05D2240/12 ,  Y02T50/60

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

公开(公告)号：US10253641B2

公开(公告)日：2019-04-09

申请号：US15440294

申请日：2017-02-23

Applicant: General Electric Company

Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

IPC: F01D9/04 ,  F04D29/54 ,  F01D11/00 ,  F01D9/02

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

公开(公告)号：US20180230839A1

公开(公告)日：2018-08-16

申请号：US15432269

申请日：2017-02-14

Applicant: General Electric Company

Inventor： Kirk D. Gallier ,  Edward Charles Vickers

IPC: F01D11/02 ,  F02K3/06

CPC classification number: F01D11/02 ,  F01D11/003 ,  F01D11/005 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/11 ,  F05D2240/56 ,  Y02T50/672

Abstract: A shroud assembly for a turbine engine comprises a plurality of circumferentially arranged shroud segments, each terminating in circumferentially spaced first and second shiplap elements, where the first shiplap element of one shroud segment can overlap the second shiplap element of an adjacent shroud segment.