公开(公告)号：US20190128131A1

公开(公告)日：2019-05-02

申请号：US15796942

申请日：2017-10-30

Applicant: General Electric Company

Inventor： Alexander Martin Sener ,  Brian David Keith ,  David Alan Frey ,  Jamil Darnell Grant

IPC: F01D11/00 ,  F02C9/22

Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

公开(公告)号：US20190063246A1

公开(公告)日：2019-02-28

申请号：US15690346

申请日：2017-08-30

Applicant: General Electric Company

Inventor： David Alan Frey ,  Kirk Douglas Gallier ,  Daniel Patrick Kerns ,  Brandon ALlanson Reynolds

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/00 ,  F01D25/24

CPC classification number: F01D9/044 ,  C04B35/571 ,  C04B35/573 ,  C04B35/806 ,  C04B37/001 ,  C04B2235/48 ,  C04B2237/38 ,  C04B2237/61 ,  C04B2237/84 ,  F01D9/041 ,  F01D11/003 ,  F01D11/005 ,  F01D25/005 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/23 ,  F05D2230/31 ,  F05D2230/60 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2260/36 ,  F05D2300/603 ,  F05D2300/6033

Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a method for assembling an airfoil with a boundary structure to form a flow path assembly is provided. The method includes machining an opening into the boundary structure. The opening is sized to receive an airfoil or other component. The method also includes machining a cutout into the boundary structure proximate the opening. A locking feature is inserted into the cutout. When the airfoil is inserted into the opening, the locking feature interlocks the airfoil with the boundary structure. To seal the airfoil with the boundary structure, the airfoil is pressed against or into the boundary structure. When the airfoil is pressed, the locking feature is compressed such that a seal is formed between the airfoil and the boundary structure to seal the flow path assembly.

公开(公告)号：US20170328235A1

公开(公告)日：2017-11-16

申请号：US15155110

申请日：2016-05-16

Applicant: General Electric Company

Inventor： Michael Anthony Ruthemeyer ,  David Alan Frey

IPC: F01D25/12 ,  F02C3/04 ,  F01D5/12 ,  F01D9/04

CPC classification number: F01D9/041 ,  F01D9/065 ,  F05D2300/6033

Abstract: A turbine nozzle assembly includes an outer band and an inner band positioned radially inward from the outer band, wherein a gas flow path is defined between the outer and inner band. The turbine nozzle assembly further includes a stator vane extending radially inward from the outer band to the inner band through the gas flow path. In addition, the outer band of the turbine nozzle assembly defines a cavity and a first conduit extending from an inlet to the cavity. The outer band further defines a second conduit extending from the cavity to an outlet such that the cavity is in fluid communication with the gas flow path through the second conduit.