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：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.

公开(公告)号：US12038176B2

公开(公告)日：2024-07-16

申请号：US17651644

申请日：2022-02-18

Applicant: General Electric Company

Inventor： Pradeep Naik ,  Shai Birmaher ,  Kwanwoo Kim ,  Saket Singh ,  Perumallu Vukanti ,  Karthikeyan Sampath ,  Steven C. Vise ,  Nicholas R. Overman ,  Michael A. Benjamin

IPC: F23R3/14 ,  F23R3/28 ,  F23D11/38

CPC classification number: F23R3/14 ,  F23R3/286 ,  F23D11/383

Abstract: A swirler assembly includes a swirler having a primary swirler with a primary swirler venturi, a swirler ferrule plate connected upstream to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an annular pressure drop cavity with oxidizer inlet orifices in fluid communication with the swirler, and at least one outlet orifice in fluid communication with the primary swirler venturi. A second flow of oxidizer to the swirler incurs a first pressure drop, a third flow of the oxidizer from the swirler to the annular pressure drop cavity incurs a second pressure drop, and a fourth flow of the oxidizer from the annular pressure drop cavity to the primary swirler venturi incurs a third pressure drop.

公开(公告)号：US20240230088A9

公开(公告)日：2024-07-11

申请号：US18314418

申请日：2023-05-09

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Rimple Rangrej ,  Pradeep Naik ,  Saket Singh ,  Deepak Ghiya ,  Perumallu Vukanti

IPC: F23R3/00 ,  F23R3/60

CPC classification number: F23R3/002 ,  F23R3/60 ,  F23R2900/00014

Abstract: In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.

公开(公告)号：US11927349B2

公开(公告)日：2024-03-12

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 ,  F23R3/04 ,  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：US20230341125A1

公开(公告)日：2023-10-26

申请号：US17820373

申请日：2022-08-17

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Karthikeyan Sampath ,  Perumallu Vukanti ,  Ravindra Shankar Ganiger ,  Pradeep Naik

IPC: F23R3/06

CPC classification number: F23R3/06

Abstract: A combustor liner for a gas turbine includes a liner at least partially defining a combustion chamber. The liner includes a plurality of dilution openings therethrough, at least one dilution opening of the plurality of dilution openings defined by (a) a main dilution opening portion defining a main dilution opening perimeter, and (b) a plurality of secondary dilution opening portions arranged about the main dilution opening perimeter and extending outward from the main dilution opening portion.

公开(公告)号：US20220390112A1

公开(公告)日：2022-12-08

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 ,  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 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.

公开(公告)号：US20220390111A1

公开(公告)日：2022-12-08

申请号：US17340654

申请日：2021-06-07

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

IPC: F23R3/00 ,  F23R3/60 ,  F02C7/18

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 further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.

公开(公告)号：US11384937B1

公开(公告)日：2022-07-12

申请号：US17318801

申请日：2021-05-12

Applicant: General Electric Company

Inventor： Karthikeyan Sampath ,  Ugandhar K. Reddy ,  Steven C. Vise ,  Allen M. Danis ,  Kwanwoo Kim ,  Ranganatha Narasimha Chiranthan

IPC: F23R3/14 ,  F23R3/26

Abstract: A swirler with integrated damper may include a primary swirler vane having a primary air passage, a secondary swirler vane having a secondary air passage, and a damper within the primary swirler vane, the secondary swirler vane, or both the primary swirler vane and the secondary swirler vane. The damper may include a series of cavities. The damper is configured to absorb one or more frequencies present in an air flow through the primary air passage, the secondary air passage, or both the primary air passage and the secondary air passage.

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.