公开(公告)号：US20230053389A1

公开(公告)日：2023-02-23

申请号：US17649128

申请日：2022-01-27

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Pradeep Naik ,  Sripathi Mohan ,  Karthikeyan Sampath ,  Steven C. Vise ,  Shai Birmaher ,  Saket Singh

IPC: F23R3/16 ,  F23R3/28

Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.

公开(公告)号：US11280495B2

公开(公告)日：2022-03-22

申请号：US16808443

申请日：2020-03-04

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Steven Clayton Vise ,  Perumallu Vukanti ,  Mayank Krisna Amble ,  Clayton Stuart Cooper ,  Nicholas Ryan Overman ,  Karthikeyan Sampath ,  Allen Michael Danis ,  Craig Douglas Young

IPC: F23R3/14 ,  F23R3/28 ,  F23R3/00 ,  F02C7/22

Abstract: A flow device for a combustor assembly defining a longitudinal axis around which the flow device is positioned is provided. The flow device includes a body extended around the longitudinal axis. The body includes a first wall and a second wall separated longitudinally from one another along the longitudinal axis. A fuel injector passage is defined through the body coaxial to the longitudinal axis. A plurality of vane walls is extended radially between the first wall and the second wall relative to the longitudinal axis. A radial flow passage is extended between the plurality of vane walls and the fuel injector passage.

公开(公告)号：US10890327B2

公开(公告)日：2021-01-12

申请号：US15896223

申请日：2018-02-14

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Hiranya Kumar Nath ,  Arvind Kumar Rao ,  Steven Clayton Vise ,  Perumallu Vukanti ,  Mayank Krisna Amble ,  Clayton Stuart Cooper

IPC: F23R3/00 ,  F23R3/16 ,  F23R3/06 ,  F23R3/14 ,  F23R3/08

Abstract: A gas turbine engine combustor includes a liner defining at least in part a combustion chamber, a first side exposed to the combustion chamber, a second side opposite the first side, and a dilution hole extending from the second side to the first side. The liner includes an airflow feature on the first side of the liner adjacent to the dilution hole and extending into the combustion chamber to increase a cooling of the liner.

公开(公告)号：US10816202B2

公开(公告)日：2020-10-27

申请号：US15823633

申请日：2017-11-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Mayank Krisna Amble ,  Perumallu Vukanti ,  Steven Clayton Vise ,  Michael Anthony Benjamin

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/26 ,  F02K1/82 ,  F02C7/18 ,  F02C3/04

Abstract: A combustor liner, a gas turbine engine including a combustor having the combustor liner, and a method for regulating jet wakes in the combustor are disclosed. The combustor liner includes a panel, at least one first through-hole, and a plurality of second through-holes including first and second set of through-holes. The at least one first through-hole is disposed on a section of the panel in a first row. The plurality of second through-holes is disposed on the section along axial and circumferential directions and arranged adjacent to the at least one first through-hole. The first set and the second set of through-holes are arranged in a second row and a third row respectively. The first, second, and third rows extend along the circumferential direction. The at least one first through-hole and the plurality of second through-holes collectively cover circumferential plane of the section along the first, second, and third rows.

公开(公告)号：US10801726B2

公开(公告)日：2020-10-13

申请号：US15710921

申请日：2017-09-21

Applicant: General Electric Company

Inventor： Eric John Stevens ,  Allen Michael Danis ,  Ravi Chandra ,  Jayanth Sekar ,  Perumallu Vukanti

IPC: F23R3/28 ,  F23R3/14 ,  F23D11/38 ,  F23D11/00 ,  F23R3/50 ,  F23R3/04

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a deflector wall, an annular axial wall, and an annular shroud. The deflector wall is extended at least partially along a radial direction and a circumferential direction relative to an axial centerline and adjacent to a combustion chamber. A fuel nozzle opening is defined through the deflector wall, and a nozzle centerline is extended through the fuel nozzle opening along a lengthwise direction. The annular axial wall is coupled to the deflector wall and extended through the fuel nozzle opening. The axial wall is defined around the nozzle centerline. The annular shroud is defined around the nozzle centerline and extended co-directional to the axial wall. The axial wall and the annular shroud are each coupled to a radial wall defined upstream of the deflector wall. The annular shroud, the axial wall, and the radial wall together define a cooling plenum therebetween. The axial wall defines a discrete inlet opening therethrough providing fluid communication from a diffuser cavity to the cooling plenum. The cooling plenum defines an exit opening providing fluid communication from the cooling plenum to the combustion chamber.

公开(公告)号：US20190162413A1

公开(公告)日：2019-05-30

申请号：US15823633

申请日：2017-11-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Mayank Krisna Amble ,  Perumallu Vukanti ,  Steven Clayton Vise ,  Michael Anthony Benjamin

IPC: F23R3/06 ,  F23R3/00

CPC classification number: F23R3/06 ,  F02C3/04 ,  F02C7/18 ,  F02K1/822 ,  F05D2220/32 ,  F05D2240/35 ,  F23R3/002 ,  F23R3/26

Abstract: A combustor liner, a gas turbine engine including a combustor having the combustor liner, and a method for regulating jet wakes in the combustor are disclosed. The combustor liner includes a panel, at least one first through-hole, and a plurality of second through-holes including first and second set of through-holes. The at least one first through-hole is disposed on a section of the panel in a first row. The plurality of second through-holes is disposed on the section along axial and circumferential directions and arranged adjacent to the at least one first through-hole. The first set and the second set of through-holes are arranged in a second row and a third row respectively. The first, second, and third rows extend along the circumferential direction. The at least one first through-hole and the plurality of second through-holes collectively cover circumferential plane of the section along the first, second, and third rows.

公开(公告)号：US20250116402A1

公开(公告)日：2025-04-10

申请号：US18768665

申请日：2024-07-10

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aritra Chakraborty ,  Perumallu Vukanti ,  Pradeep Naik ,  Arijit Sinha Roy ,  Bhavya Naidu Panduri ,  R. Narasimha Chiranthan ,  Ajoy Patra ,  Michael T. Bucaro ,  Sibtosh Pal ,  Pabitra Badhuk

IPC: F23R3/06

Abstract: A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.

公开(公告)号：US20250109853A1

公开(公告)日：2025-04-03

申请号：US18476595

申请日：2023-09-28

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Perumallu Vukanti ,  Ravindra Shankar Ganiger ,  Sahana Narasimhan Suresh ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan ,  Hiranya Kumar Nath

IPC: F23R3/00 ,  F23R3/28 ,  F23R3/60

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section includes a primary combustor liner including an inner liner and an outer liner. A dome wall and a primary dome inlet are located in the dome wall. The outer liner defines at least one opening downstream from the primary dome inlet. A primary combustion chamber and a set of secondary combustors are fluidly coupled to the primary combustion chamber at the at least one opening.

公开(公告)号：US12158270B2

公开(公告)日：2024-12-03

申请号：US18104408

申请日：2023-02-01

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Pradeep Naik ,  R Narasimha Chiranthan ,  Ajoy Patra ,  Arijit Sinha Roy ,  Pabitra Badhuk ,  Aritra Chakraborty ,  Bhavya Naidu Panduri ,  Michael T. Bucaro ,  Sibtosh Pal

IPC: F23R3/46 ,  F23R3/04 ,  F23R3/18

Abstract: A combustor comprising a dome wall, an annular liner, a combustion chamber, a set of fuel cups, and a set of dilution passages for each fuel cup of the set of fuel cups. The set of fuel cups circumferentially spaced along the dome wall relative to the combustor centerline. The set of dilution passages terminating in a plurality of slots spaced about the corresponding fuel cup in the set of fuel cups.

公开(公告)号：US12152777B2

公开(公告)日：2024-11-26

申请号：US17340703

申请日：2021-06-07

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Perumallu Vukanti ,  Daniel J. Kirtley ,  Karthikeyan Sampath ,  Shai Birmaher ,  Pradeep Naik ,  Rajendra Mahadeorao Wankhade ,  Michael Anthony Benjamin ,  Veeraraju Vanapalli ,  Deepak Ghiya

IPC: F23R3/00 ,  F23R3/08 ,  F01D9/02

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner including a dilution slot in fluid communication with the combustion chamber; and one or more guides configured to redirect cooling medium into the dilution slot.