公开(公告)号：US20210079799A1

公开(公告)日：2021-03-18

申请号：US16568730

申请日：2019-09-12

Applicant: General Electric Company

Inventor： Paul Hadley Vitt ,  Wilson Frost ,  Mark Broomer

IPC: F01D9/04

Abstract: An apparatus for a nozzle assembly for a turbine engine and a method of forming the nozzle assembly are described herein. The nozzle assembly can include a set of nozzles including an inner band and an outer band, with one or more airfoils extending between the inner and outer bands. The nozzles can be coupled to adjacent nozzles at the inner and outer bands to form the nozzle assembly. A throat can be defined at the minimum cross-sectional area between adjacent airfoils in the nozzle assembly. A formed portion can be formed on either of or both of the inner or outer band at the throat.

公开(公告)号：US11473437B2

公开(公告)日：2022-10-18

申请号：US16576933

申请日：2019-09-20

Applicant: General Electric Company

Inventor： Mark Broomer ,  Tyler Frederick Hooper ,  Jason Michael Ulberg

IPC: F01D11/00 ,  F01D25/24 ,  F02C7/28 ,  F01D9/04 ,  F01D11/08 ,  F16J15/08

Abstract: In one aspect, a sealing assembly for a turbine of a gas turbine engine includes a first turbine component having a first surface and a second surface positioned aft of the first surface. The first turbine component, in turn, defines a slot positioned between the first surface and the second surface. Furthermore, the sealing assembly includes a second turbine component positioned aft of the first turbine component such that the first component and the second component define a gap therebetween. Additionally, the sealing assembly includes a seal configured to seal the gap defined between the first turbine component and the second turbine component. The seal includes a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first component. Moreover, the seal further includes a second portion that exerts a sealing force on the second component.

公开(公告)号：US20170089211A1

公开(公告)日：2017-03-30

申请号：US14864221

申请日：2015-09-24

Applicant: General Electric Company

Inventor： Mark Broomer ,  Edip Sevincer ,  Anthony Christopher Marin

IPC: F01D11/00 ,  F16J15/04

CPC classification number: F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2300/501 ,  F16J15/04 ,  F16J15/0887

Abstract: Snap in annular spring seal including continuous or split full 360 degree ring having radially outer second seal end spaced outwardly of a radially inner first end of the ring and axial biasing means urging first and second seal ends apart. Biasing means may include an axially aftwardly opening conical section connecting first and second seal ends and second seal end having outer aftwardly opening V-shaped cross-sectional bend or circular cross-sectional bend. Spring seal may extend radially and circumferentially between and in sealing engagement with first and second annular turbine components. First end may be spring-loaded and removably secured in U-shaped or V-shaped slot of turbine component. Slot may include symmetrical inner U-shaped bent first seal end including annular substantially parallel or non-parallel forward and aft legs connected by semi-circular cross-sectional bend. Seal may include bowed section connecting circular seal ends.

公开(公告)号：US10392950B2

公开(公告)日：2019-08-27

申请号：US14706003

申请日：2015-05-07

Applicant: General Electric Company

Inventor： Victor Hugo Silva Correia ,  Brian Kenneth Corsetti ,  Mark Broomer

IPC: F01D9/04 ,  F01D25/24 ,  F01D25/00 ,  F01D25/10

Abstract: A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.

公开(公告)号：US20190024513A1

公开(公告)日：2019-01-24

申请号：US15653789

申请日：2017-07-19

Applicant: General Electric Company

Inventor： Robert Francis Manning ,  Mark Broomer ,  Brian Kenneth Corsetti

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D5/14 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58

Abstract: An airfoil for a turbine engine can include a body having an outer wall defining a pressure side and a suction side, and the body can extend axially between a truncated nose and a trailing edge. A shield can be positioned upstream of the nose to define a leading edge for the airfoil.