公开(公告)号：US20230332539A1

公开(公告)日：2023-10-19

申请号：US17827180

申请日：2022-05-27

Applicant: General Electric Company

Inventor： Sesha Subramanian ,  Ravikanth Avancha ,  Atanu Saha

IPC: F02C9/18 ,  F02C7/00

CPC classification number: F02C9/18 ,  F02C7/00 ,  F05D2240/127

Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.

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.