公开(公告)号：US20230094199A1

公开(公告)日：2023-03-30

申请号：US17649218

申请日：2022-01-28

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Shai Birmaher ,  Saket Singh ,  Rimple Rangrej ,  Krishnendu Chakraborty

IPC: F23R3/26

Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner and an inner liner. The outer liner has an annular outer liner slot dilution opening, with a plurality of outer liner swirl vanes disposed within the annular outer liner slot dilution opening. The inner liner of the combustor liner includes an annular inner liner slot dilution opening, and also includes a plurality of inner liner swirl vanes disposed within the annular inner liner slot dilution opening.

公开(公告)号：US20220412560A1

公开(公告)日：2022-12-29

申请号：US17355689

申请日：2021-06-23

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Gregory A. Boardman

IPC: F23R3/06

Abstract: A combustor for a gas turbine engine has a combustor liner that has a cold surface side and a hot surface side, the liner defining an upstream end and a downstream end, and a dilution opening through the combustor liner. The dilution opening includes a main dilution hole portion having an upstream edge and a downstream edge, a notched portion disposed at the upstream edge and extending upstream from the upstream edge, the notched portion being in fluid communication with the main dilution hole portion, and a slotted portion disposed at the downstream edge and extending downstream of the downstream edge, the slotted portion being in fluid communication with the main dilution hole portion.

公开(公告)号：US20220333526A1

公开(公告)日：2022-10-20

申请号：US17233728

申请日：2021-04-19

Applicant: General Electric Company

Inventor： Saket Singh ,  Rimple Rangrej

IPC: F02C3/14 ,  F23R3/00

Abstract: A gas turbine engine that includes a combustor configured for efficient combustion of fuel for the generation of combustion gases. The engine includes an annular combustor that includes an annular wall that defines a channel configured to conduct hot combustion gases along a flow-path of combustion gases. The annular wall has an exterior first surface and an interior second surface. A plurality of dilution holes is defined through the wall. Each dilution hole is defined by a dilution hole surface that extends between an entry end and an exit end. The entry end is defined by the first surface and the exit end is defined by the second surface such that the dilution hole has a convergent and then divergent cross-sectional profile. The entry end has a first geometric shape and the exit end has a second geometric shape that is different than the second geometric shape.

公开(公告)号：US20220290861A1

公开(公告)日：2022-09-15

申请号：US17201846

申请日：2021-03-15

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Rimple Rangrej ,  Saket Singh ,  Pradeep Naik

IPC: F23R3/00 ,  F23R3/06

Abstract: A liner for a combustor in a gas turbine engine. The liner may include a liner body having a cold side and a hot side. The liner may include a dilution opening and a passage extending through the liner body. The passage may be positioned adjacent the dilution opening. The passage may be angled with respect to an interior surface of the liner body. A dilution flow may flow through the dilution opening from the cold side to the hot side and a secondary flow may flow through the passage from the cold side to the hot side. The secondary flow may exit into the hot side behind the dilution flow and may suppresses wakes formed behind the dilution flow on the hot side of the liner.