公开(公告)号：US20230137910A1

公开(公告)日：2023-05-04

申请号：US17649220

申请日：2022-01-28

Applicant: General Electric Company

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

IPC: F23R3/00

Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner having a plurality of outer liner segments, and an inner liner having a plurality of inner liner segments. Each segment of the inner liner and the outer liner includes at least one slotted dilution opening therethrough extending in a circumferential direction, and each slotted dilution opening includes a deflector wall extending radially from the respective liner into a dilution zone of a combustion chamber between the outer liner and the inner liner. The at least one slotted dilution opening may be a curved slot (either concave or convex) dilution opening, and the curved slot dilution openings for each segment of the outer liner and the inner liner may be connected so as to provide a wavy slotted dilution opening extending annularly through the outer liner and the inner liner.

公开(公告)号：US20230034004A1

公开(公告)日：2023-02-02

申请号：US17389022

申请日：2021-07-29

Applicant: General Electric Company

Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik ,  Neeraj Mishra

IPC: F23R3/14 ,  F02C7/22

Abstract: A gas turbine combustor includes a main mixer for providing an air flow to mix with a fuel flow in a combustor. The main mixer includes an annular mixer body, a plurality of mixer vanes located circumferentially around the annular mixer body, and a plurality of wedges extending radially outward from each of the plurality of mixer vanes. At least one of the wedges includes serrations. The air flow through the main mixer enters the main mixer at a leading edge of the mixer vane, flows over the plurality of wedges, and exits the mixer vanes at a trailing edge of the main mixer. The wedges create vortices in the air flow to provide a uniform fuel-air flow.

公开(公告)号：US11566789B1

公开(公告)日：2023-01-31

申请号：US17655453

申请日：2022-03-18

Applicant: General Electric Company

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

IPC: F23R3/28 ,  F23R3/14

Abstract: A ferrule in a fuel-air mixer assembly. The ferrule includes a body having (i) a plurality of channels having sidewalls, the plurality of channels leading to a corresponding plurality of exit openings, the plurality of channels configured to guide a first airflow therein and (ii) a plurality of cascade holes formed within the sidewalls of the plurality of channels and defining a plurality of passageways therein that are transverse to the plurality of channels. The ferrule also includes a plurality of airflow modifiers provided within the plurality of channels. The plurality airflow modifiers are configured to reduce a velocity of the first airflow when the first airflow exits through the plurality of exit openings and to generate low velocity vortex pairs to reduce interaction of the first airflow with a second airflow provided through primary vanes located downstream of the plurality of exit openings of the plurality of channels.

公开(公告)号：US20250129941A1

公开(公告)日：2025-04-24

申请号：US19005042

申请日：2024-12-30

Applicant: General Electric Company

Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik

IPC: F23R3/14 ,  F02C7/22

Abstract: A main mixer for an engine. The main mixer includes a plurality of mixer vanes located circumferentially around a mixer body. Each mixer vane includes a waveform profile. The waveform profile detaches or trips a boundary layer of an air flow across the mixer vane such that the waveform profile introduces turbulence into the air flow.

公开(公告)号：US12181151B2

公开(公告)日：2024-12-31

申请号：US17389030

申请日：2021-07-29

Applicant: General Electric Company

Inventor： Rimple Rangrej ,  Saket Singh ,  Pradeep Naik

IPC: F23R3/14 ,  F02C7/22

Abstract: A main mixer for an engine. The main mixer includes a plurality of mixer vanes located circumferentially around a mixer body. Each mixer vane includes a waveform profile. The waveform profile detaches or trips a boundary layer of an air flow across the mixer vane such that the waveform profile introduces turbulence into the air flow.

公开(公告)号：US20240247802A1

公开(公告)日：2024-07-25

申请号：US18598467

申请日：2024-03-07

Applicant: General Electric Company

Inventor： Vijayaraj Sukumar ,  Perumallu Vukanti ,  Pradeep Naik ,  Ajoy Patra ,  Karthikeyan Sampath ,  Rimple Rangrej ,  Hiranya Nath ,  Krishnendu Chakraborty ,  Narasimhan S. Sahana ,  Saket Singh ,  Ravindra Shankar Ganiger

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/10 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R3/04 ,  F23R3/10 ,  F23R2900/00017 ,  F23R2900/03045

Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.

公开(公告)号：US20230408098A1

公开(公告)日：2023-12-21

申请号：US17664971

申请日：2022-05-25

Applicant: General Electric Company

Inventor： Saket Singh ,  Rimple Rangrej ,  Pradeep Naik ,  Michael A. Benjamin ,  Joseph Zelina

IPC: F23R3/34 ,  F23R3/06

CPC classification number: F23R3/346 ,  F23R3/06

Abstract: A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.

公开(公告)号：US20230324047A1

公开(公告)日：2023-10-12

申请号：US17812897

申请日：2022-07-15

Applicant: General Electric Company

Inventor： Vijayaraj Sukumar ,  Perumallu Vukanti ,  Pradeep Naik ,  Ajoy Patra ,  Karthikeyan Sampath ,  Rimple Rangrej ,  Hiranya Nath ,  Krishnendu Chakraborty ,  Narasimhan S. Sahana ,  Saket Singh ,  Ravindra Shankar Ganiger

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R2900/03045 ,  F23R2900/00017 ,  F23R3/60

Abstract: A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.

公开(公告)号：US20230266007A1

公开(公告)日：2023-08-24

申请号：US17809381

申请日：2022-06-28

Applicant: General Electric Company

Inventor： Ranganatha Narasimha Chiranthan ,  Karthikeyan Sampath ,  Perumallu Vukanti ,  Rimple Rangrej ,  Ravindra Shankar Ganiger ,  Hiranya Nath

IPC: F23R3/16 ,  F23R3/06

CPC classification number: F23R3/16 ,  F23R3/06 ,  F23R2900/00001 ,  F23R2900/03045 ,  F23R2900/03044

Abstract: A combustor liner for a gas turbine has a cold side liner segment, and a hot side liner segment, with a baffle cavity between the cold side liner segment and the hot side liner segment. At least one cooling airflow dispersing member is arranged within the baffle cavity. The at least one cooling airflow dispersing member includes a main cavity portion, and at least one peripheral cavity portion surrounding the main cavity portion. The main cavity portion includes a main cavity inlet side having a cooling airflow opening, a main cavity outlet side having plurality of hot side cooling airflow openings, and at least one peripheral cavity outlet flow passage providing fluid communication between the main cavity portion and the at least one peripheral cavity portion. The at least one peripheral cavity portion includes a peripheral cavity outlet side having a plurality of hot side cooling airflow openings.

公开(公告)号：US11703225B2

公开(公告)日：2023-07-18

申请号：US17663311

申请日：2022-05-13

Applicant: General Electric Company

Inventor： Saket Singh ,  Pradeep Naik ,  Rimple Rangrej ,  Shai Birmaher ,  Ranganatha Narasimha Chiranthan ,  Ajoy Patra ,  Ravindra Shankar Ganiger ,  Hiranya Nath

IPC: F23R3/06 ,  F23R3/16

CPC classification number: F23R3/06 ,  F23R3/16

Abstract: A combustor liner for a combustor of a gas turbine includes an outer liner extending circumferentially about a combustor centerline, and an inner liner extending circumferentially about the combustor centerline, where the outer liner and the inner liner define a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution flow assembly comprising, (a) an annular slot dilution opening, and (b) a dilution fence extending between an upstream side of the annular slot dilution opening to a downstream side of the annular slot dilution opening, and extending into the combustion chamber, the dilution fence including a plurality of dilution openings therethrough for providing a flow of an oxidizer through the dilution fence into the combustion chamber.