公开(公告)号：US20220364510A1

公开(公告)日：2022-11-17

申请号：US17317131

申请日：2021-05-11

Applicant: General Electric Company

Inventor： Gurunath Gandikota ,  Varun Lakshmanan ,  Perumallu Vukanti ,  Allen M. Danis ,  Michael A. Benjamin

IPC: F02C7/18 ,  F23R3/28 ,  F02C7/22 ,  F23R3/16 ,  F23R3/06

Abstract: A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.

公开(公告)号：US11415321B2

公开(公告)日：2022-08-16

申请号：US17029587

申请日：2020-09-23

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 method for regulating jet wakes in a combustor including: directing compressed fluid into a passageway between a casing and a combustor liner; directing a combustion gas along a combustion zone; discharging a first portion of compressed fluid from the passageway into the combustion zone via a first through-hole which is disposed on a section of a combustor panel in a first circumferential row; and discharging a second portion of the compressed fluid from the passageway into the combustion zone via second through-holes, wherein the second through-holes are disposed on a section of the panel, spaced apart axially and circumferentially, and adjacent to the first through-hole, wherein the second through-holes include a first set of through-holes and a second set of through-holes, the first set of through-holes in a second row and the second set of through-holes in a third row, wherein the second and third rows extend circumferentially.

公开(公告)号：US11255543B2

公开(公告)日：2022-02-22

申请号：US16057249

申请日：2018-08-07

Applicant: General Electric Company

Inventor： Mayank Krisna Amble ,  Gurunath Gandikota ,  Perumallu Vukanti ,  Ravi Chandra ,  Karthikeyan Sampath

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/28 ,  F23R3/04 ,  F23R3/50

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening and includes a walled chute disposed at least partially through the opening. A plurality of flow openings is defined through the walled chute.

公开(公告)号：US20190249874A1

公开(公告)日：2019-08-15

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

CPC classification number: F23R3/002 ,  F23R3/08 ,  F23R3/14 ,  F23R3/16 ,  F23R2900/03042

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：US20250075911A1

公开(公告)日：2025-03-06

申请号：US18949096

申请日：2024-11-15

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Clayton S. Cooper ,  Perumallu Vukanti ,  Michael A. Benjamin ,  Steven C. Vise ,  Sripathi Mohan

IPC: F23R3/16 ,  F23L7/00

Abstract: A combustor having a main chamber and a trapped vortex cavity. The main chamber includes an outer liner and an inner liner. The trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the trapped vortex cavity to produce combustion gases. The trapped vortex cavity injects the combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system operably injecting steam into the main chamber such that the steam flows downstream of the trapped vortex cavity.

公开(公告)号：US20250075910A1

公开(公告)日：2025-03-06

申请号：US18952330

申请日：2024-11-19

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Pradeep Naik ,  Joseph Zelina ,  Sripathi Mohan ,  Perumallu Vukanti ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Karthikeyan Sampath

IPC: F23R3/00 ,  F23R3/42

Abstract: A turbine engine with a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. A combustion section for the turbine engine, having a primary combustor liner including an inner liner and an outer liner annular about an engine centerline. A dome wall extending between the inner liner and the outer liner. A set of primary dome inlets located in the dome wall and circumferentially arranged about the engine centerline. A set of secondary combustors fluidly coupled to a primary combustion chamber, the set of secondary combustors including a first mini combustor and a second mini combustor.

公开(公告)号：US20250067214A1

公开(公告)日：2025-02-27

申请号：US18501484

申请日：2023-11-03

Applicant: General Electric Company

Inventor： Perumallu Vukanti ,  Pradeep Naik ,  Saket Singh ,  Michael A. Benjamin ,  Sripathi Mohan ,  Clayton S. Cooper ,  Rajendra Wankhade ,  Hiranya Nath ,  Nicholas R. Overman ,  Steven C. Vise

IPC: F02C3/30 ,  F23R3/04

Abstract: A combustor includes a combustion chamber and an annular dome. The combustion chamber includes an outer liner and an inner liner and has a combustion zone. The annular dome is coupled to the outer liner and the inner liner. A plurality of mixing assemblies operably injects a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases. A combustor steam system is in fluid communication with the combustion chamber. The combustor steam system includes a steam path defined by at least one of the outer liner, the inner liner, or the annular dome. The combustor steam system operably directs steam through the steam path from the at least one of the outer liner, the inner liner, or the annular dome and into the combustion chamber.

公开(公告)号：US20250020325A1

公开(公告)日：2025-01-16

申请号：US18901941

申请日：2024-09-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Ajoy Patra ,  Pradeep Naik ,  R Narasimha Chiranthan ,  Perumallu Vukanti ,  Michael T. Bucaro

IPC: F23R3/28

Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.

公开(公告)号：US20250020324A1

公开(公告)日：2025-01-16

申请号：US18435282

申请日：2024-02-07

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Manampathy G. Giridharan ,  Clayton S. Cooper ,  Michael A. Benjamin ,  Steven C. Vise ,  Michael T. Bucaro ,  Ajoy Patra ,  Pradeep Naik ,  Perumallu Vukanti ,  R Narasimha Chiranthan

IPC: F23R3/06 ,  F23R3/28

Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.

公开(公告)号：US20240410586A1

公开(公告)日：2024-12-12

申请号：US18808558

申请日：2024-08-19

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Daniel J. Kirtley ,  Shai Birmaher ,  Veeraraju Vanapalli ,  Karthikeyan Sampath ,  Deepak Ghiya ,  Perumallu Vukanti ,  Rajendra Mahadeorao Wankhade ,  Pradeep Naik ,  Rimple Rakeshkumar Rangrej ,  Saket Singh

IPC: F23R3/42 ,  F02C3/02 ,  F02C3/14

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 forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.