公开(公告)号：US09869473B2

公开(公告)日：2018-01-16

申请号：US14750543

申请日：2015-06-25

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ahmed Mostafa Elkady ,  Allen Michael Danis ,  Eric Matthew Roberson ,  Mark Anthony Mueller ,  George Moertle ,  Shui-chi Li

IPC: F23R3/50 ,  F23R3/00

CPC classification number: F23R3/005 ,  F23R3/002 ,  F23R3/50 ,  F23R2900/03041 ,  F23R2900/03042

Abstract: A gas turbine engine combustor conical-flat heat shield includes an annular conical section extending upstream from and being integral with a flat section with a flat downstream facing surface which may be generally perpendicular to or canted with respect to a centerline. The flat section includes radially outer and inner edges at least one of which is circular and circumscribed about a centerline and circumferentially spaced apart clockwise and counter-clockwise radial edges having an origin on the centerline. A gas turbine engine combustor includes conical-flat heat shields in one or more circular rows arranged in a non-symmetrical or asymmetrical pattern. Two or more groups (A, B, C) of the conical-flat heat shields in the circular rows may be mounted on a domeplate and one or more of the conical-flat heat shields is different in one or more of the groups (A, B, C).

公开(公告)号：US11221143B2

公开(公告)日：2022-01-11

申请号：US15883573

申请日：2018-01-30

Applicant: General Electric Company

Inventor： Eric John Stevens ,  Allen Michael Danis

IPC: F23R3/26 ,  F23R3/00 ,  F23R3/16 ,  F23R3/10

Abstract: A combustor assembly comprising a deflector wall in which a plurality of openings is defined through the deflector wall and around the fuel nozzle opening. The plurality of openings defines a first set of openings at a first radius, a second set of openings at or greater than a second radius greater than the first radius, and a third set of openings at one or more of a third radius between the first radius and the second radius. The first set of openings defines one or more of a first angle relative to the radial direction between approximately 60 degrees and approximately 100 degrees. The second set of openings defines one or more of a second angle between approximately zero and approximately 30 degrees. The third set of openings defines one or more of a third angle between the first angle and the second angle.

公开(公告)号：US11181274B2

公开(公告)日：2021-11-23

申请号：US15681875

申请日：2017-08-21

Applicant: General Electric Company

Inventor： Allen Michael Danis ,  Scott Matthew Bush ,  Arthur Wesley Johnson ,  Nicholas Ryan Overman ,  Kent Hamilton Lyle ,  Eric John Stevens

IPC: F23R3/36 ,  F02C9/40 ,  F23R3/28 ,  F02C7/22 ,  F02C3/20 ,  F02C3/06 ,  F02C7/228 ,  F23R3/34 ,  F02C9/28

Abstract: The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.

公开(公告)号：US20200041129A1

公开(公告)日：2020-02-06

申请号：US16055494

申请日：2018-08-06

Applicant: General Electric Company

Inventor： Sibtosh Pal ,  Clayton Stuart Cooper ,  Arthur Wesley Johnson ,  Steven Clayton Vise ,  Michael Anthony Benjamin ,  Allen Michael Danis

IPC: F23R3/28 ,  F23C7/00 ,  F23R3/14

Abstract: A mixer assembly for a turbine engine is generally provided. The mixer assembly includes a vane assembly including a plurality of vanes configured to direct a flow of oxidizer to mix with a flow of fuel. The vane assembly includes a fluid diode disposed within a vane flow path between each pair of vanes of the vane assembly.

公开(公告)号：US10337738B2

公开(公告)日：2019-07-02

申请号：US15189085

申请日：2016-06-22

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Allen Michael Danis

IPC: F23R3/06 ,  F02C7/18 ,  F23R3/14 ,  F23R3/28 ,  F23R3/00 ,  F23R3/04

Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. Additionally, the liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end and defines a forward section extending from the quench air jets to the dome. The dome and the forward section of the liner are configured to be cooled substantially by one or both of impingement cooling or convective cooling.

公开(公告)号：US20190085767A1

公开(公告)日：2019-03-21

申请号：US15705314

申请日：2017-09-15

Applicant: General Electric Company

Inventor： Steven Clayton Vise ,  Allen Michael Danis ,  Jayanth Sekar ,  Pradeep Naik ,  Perumallu Vukanti ,  Arthur Wesley Johnson ,  Clayton Stuart Cooper ,  Karthikeyan Sampath

IPC: F02C3/22 ,  F23R3/00 ,  F23R3/04

Abstract: An apparatus and method for a combustor, the combustor including combustor liner having a plurality of dilution openings. The combustor receives a flow of fuel that is ignited and mixed with dilution air to form a flow of combustion gases. The flow of combustion gases travels through the combustor to a turbine section of an engine.

公开(公告)号：US10197279B2

公开(公告)日：2019-02-05

申请号：US15189074

申请日：2016-06-22

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Allen Michael Danis

IPC: F23R3/06 ,  F01D25/24 ,  F02C3/04 ,  F23R3/00 ,  F23R3/14 ,  F23R3/28 ,  F23D11/38

Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. The liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end. The quench air jets include a plurality of primary stage air jets and a plurality of secondary stage air jets. The plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction and together provide the combustion chamber with a quench airflow.

公开(公告)号：US20170370588A1

公开(公告)日：2017-12-28

申请号：US15189061

申请日：2016-06-22

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Allen Michael Danis

IPC: F23R3/28 ,  F23R3/06 ,  F02C7/22 ,  F02C3/04 ,  F23R3/00 ,  F02C7/12

CPC classification number: F23R3/286 ,  F02C3/04 ,  F02C7/12 ,  F02C7/222 ,  F05D2220/32 ,  F05D2260/201 ,  F23R3/002 ,  F23R3/06 ,  F23R3/283 ,  F23R2900/03043 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.

公开(公告)号：US20170370584A1

公开(公告)日：2017-12-28

申请号：US15189074

申请日：2016-06-22

Applicant: General Electric Company

Inventor： Gregory Allen Boardman ,  Pradeep Naik ,  Allen Michael Danis

IPC: F23R3/06 ,  F01D25/24 ,  F23R3/28 ,  F23R3/14 ,  F23R3/00 ,  F02C3/04

CPC classification number: F23R3/06 ,  F01D25/24 ,  F02C3/04 ,  F05D2220/32 ,  F23D11/383 ,  F23R3/002 ,  F23R3/007 ,  F23R3/14 ,  F23R3/286 ,  F23R2900/03043 ,  F23R2900/03044 ,  Y02T50/675

Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. The liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end. The quench air jets include a plurality of primary stage air jets and a plurality of secondary stage air jets. The plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction and together provide the combustion chamber with a quench airflow.