公开(公告)号：US20190284946A1

公开(公告)日：2019-09-19

申请号：US16293751

申请日：2019-03-06

Applicant: General Electric Company

Inventor： Tomasz Edward Berdowski ,  Artur Miroslaw Malek ,  Marcin Piotr Rykala ,  Adam Kiciak ,  Mahendran Manoharan ,  Zbigniew Michal Schabowski ,  Marcin Kawalkowski

IPC: F01D11/00 ,  F01D5/18

Abstract: An inter-stage seal assembly includes annular seal land mounted inwardly of and to seal support ring and pre-swirlers in purge duct extending through land. Purge duct may be bounded by spaced apart duct walls and pre-swirlers include turning vanes in outer exhaust section. Purge duct may include plurality of enclosed purge passages circumferentially disposed around engine centerline and pre-swirlers include curved section in passages. Seal land may be bifurcated having forward and aft seal land sections and purge duct may include purge duct inlet located therebetween. Seal support ring may include flange attached to or integrally and monolithically formed with inner platform attached to nozzle vanes extending across turbine flowpath and exhaust section may be flush with platform. Labyrinth seal teeth mounted to turbine rotor may engage land, purge duct may extend between annular inlets and outlets, inlet may be between adjacent couple of seal teeth.

公开(公告)号：US20180283203A1

公开(公告)日：2018-10-04

申请号：US15478321

申请日：2017-04-04

Applicant: General Electric Company

Inventor： Sanjeev Sai Kumar Manepalli ,  Monty Lee Shelton ,  Ganesh Seshadri ,  Mahendran Manoharan

IPC: F01D21/02 ,  F01D21/04 ,  F01D25/24 ,  F01D5/02 ,  F01D5/12

CPC classification number: F01D21/02 ,  F01D5/02 ,  F01D5/12 ,  F01D9/042 ,  F01D21/045 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/323 ,  F05D2260/311 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.

公开(公告)号：US10815811B2

公开(公告)日：2020-10-27

申请号：US15824151

申请日：2017-11-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ganesh Seshadri ,  Mahendran Manoharan

IPC: F01D11/12 ,  F04D29/16 ,  F04D29/32 ,  F01D5/22 ,  F01D11/08 ,  F04D29/52

Abstract: A rotatable component for a turbomachine and a method for regulating a circumferential ingress of a fluid at a trailing edge of the rotatable component are disclosed. The rotatable component includes an airfoil and a mechanical component. The airfoil includes a pressure side and a suction side. The mechanical component is coupled to the airfoil and includes a forward overhanging portion, and an aft overhanging portion. The forward overhanging portion is disposed at a leading edge of the airfoil and extends longitudinally beyond the leading edge. The aft overhanging portion is disposed at a trailing edge of the airfoil and extends longitudinally beyond the trailing edge, where both the forward and aft overhanging portions further extend circumferentially along the pressure side and the suction side of the airfoil. The aft overhanging portion includes a non-axisymmetric profile for regulating the circumferential ingress of the fluid from the pressure to suction sides.

公开(公告)号：US20180347403A1

公开(公告)日：2018-12-06

申请号：US15609368

申请日：2017-05-31

Applicant: General Electric Company

Inventor： Mahendran Manoharan ,  Ganesh Seshadri ,  Robert J. Beacock ,  Lyle Douglas Dailey ,  Ravikanth Avancha

IPC: F01D25/26 ,  F02C3/04 ,  F01D9/04 ,  F01D5/02

Abstract: An apparatus and method for a turbine engine comprising an outer casing having a first surface and defining an axial centerline and an inner casing located within the outer casing and having a second surface spaced. The first and second surfaces are spaced from each other and define an annular channel between where a combustion air flows in a fore to aft direction along a profile.

公开(公告)号：US20180156124A1

公开(公告)日：2018-06-07

申请号：US15366841

申请日：2016-12-01

Applicant: General Electric Company

Inventor： Jeffrey Donald Clements ,  Ganesh Seshadri ,  Mahendran Manoharan ,  Ravikanth Avancha ,  Aspi Rustom Wadia

IPC: F02C7/20 ,  F01D25/28 ,  F02C3/06 ,  F01D5/02 ,  F01D9/04 ,  F04D29/32 ,  F04D29/54 ,  F04D29/52 ,  F01D25/24

CPC classification number: F04D29/542 ,  F01D5/143 ,  F01D5/146 ,  F01D9/02 ,  Y02T50/673

Abstract: A frame apparatus for a turbine engine includes: a turbomachinery stage discharging into a downstream flowpath, the stage including a rotor carrying an array of axial-flow rotor airfoils; and a frame disposed downstream of the turbomachinery stage, the frame including: a support structure comprising at least one of a hub and an annular casing; an annular array of stationary struts carried by the support structure, each strut having an airfoil shape with spaced-apart pressure and suction sides extending between a leading edge and a trailing edge thereof, the stationary struts defining spaces therebetween; and the stationary struts defining spaces therebetween; and a plurality of splitters carried by the support structure, the splitters positioned in the spaces between the stationary struts, wherein at least one of a chord dimension of the splitters and a span dimension of the splitters is less than the corresponding dimension of the stationary struts.