公开(公告)号：US11933193B2

公开(公告)日：2024-03-19

申请号：US17529685

申请日：2021-11-18

Applicant: GE Avio S.r.l. ,  GENERAL ELECTRIC COMPANY

Inventor： Pratish Patil ,  Amit Goyal ,  Mahendran Manoharan ,  Francesco Bertini ,  Jaikumar Loganathan

IPC: F01D5/14

CPC classification number: F01D5/145 ,  F05D2240/31

Abstract: A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.

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：US20200049014A1

公开(公告)日：2020-02-13

申请号：US16490416

申请日：2018-03-06

Applicant: General Electric Company ,  GE Avio S.r.l.

Inventor： Jeffrey Donald Clements ,  Paul Hadley Vitt ,  Francesco Bertini ,  Aspi Rustom Wadia ,  Ganesh Seshadri ,  Mahendran Manoharan ,  Ravikanth Avancha

IPC: F01D5/14 ,  F01D5/28

Abstract: A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.

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.