公开(公告)号：US12012903B2

公开(公告)日：2024-06-18

申请号：US17719659

申请日：2022-04-13

Applicant: General Electric Company

Inventor： Hejie Li ,  Michael A. Benjamin ,  Nicholas Ryan Overman

IPC: F02C9/28 ,  F02C7/224

CPC classification number: F02C9/28 ,  F02C7/224 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2270/20 ,  F05D2270/301 ,  F05D2270/303

Abstract: A fuel temperature control system and a method of controlling a fuel temperature for a turbine engine including supplying an aviation fuel to a fuel nozzle fluidly coupled to a combustion chamber. A fuel temperature sensor for determining at least one input parameter to define an inlet fuel temperature of the aviation fuel in the fuel nozzle. A controller for receiving the at least one input parameter and for calculating a calculated flow number in the fuel nozzle. The controller capable of comparing the calculated flow number and a reference flow number associated with a threshold during a steady state condition to determine if the aviation fuel is boiling inside the fuel nozzle.

公开(公告)号：US11906165B2

公开(公告)日：2024-02-20

申请号：US17717739

申请日：2022-04-11

Applicant: General Electric Company

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

IPC: F23R3/14 ,  F23R3/28

CPC classification number: F23R3/14 ,  F23R3/286

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.

公开(公告)号：US11788724B1

公开(公告)日：2023-10-17

申请号：US17929360

申请日：2022-09-02

Applicant: General Electric Company

Inventor： Hiranya Nath ,  Ravindra Shankar Ganiger ,  Michael A. Benjamin

IPC: F23R3/00 ,  F23R3/04 ,  F02C7/045

CPC classification number: F23R3/002 ,  F02C7/045 ,  F23R3/04 ,  F05D2240/35 ,  F05D2260/96 ,  F23R2900/00014

Abstract: A combustor liner has an outer liner and an inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The outer liner and the inner liner each have a converging-diverging section extending into the dilution zone of the combustion chamber and form a throat between them. A bridge member extends across the converging-diverging sections to form a damper cavity therebetween. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat, and includes a damper inlet feed member on a downstream portion of the converging-diverging section, so that an acoustic damper is defined by the converting-diverging section, the bridge, and the damper inlet feed. The acoustic damper dampens acoustic characteristics of the combustor.

公开(公告)号：US11774100B2

公开(公告)日：2023-10-03

申请号：US17725895

申请日：2022-04-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nayan Vinod Patel ,  Michael A. Benjamin

IPC: F23R3/34 ,  F23R3/14 ,  F23R3/36 ,  F23R3/06 ,  F02C7/22 ,  F23R3/28

CPC classification number: F23R3/34 ,  F23R3/06 ,  F23R3/14 ,  F23R3/36 ,  F02C7/22 ,  F23R3/28 ,  F23R3/346

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.

公开(公告)号：US20230304665A1

公开(公告)日：2023-09-28

申请号：US18302346

申请日：2023-04-18

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F23R3/28 ,  F02C7/264 ,  F23R3/04 ,  F23R3/50 ,  F23D14/64

CPC classification number: F23R3/286 ,  F02C7/264 ,  F23D14/64 ,  F23R3/045 ,  F23R3/50 ,  F05D2240/35 ,  F05D2260/99 ,  F23D2207/00

Abstract: A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.

公开(公告)号：US20230296250A1

公开(公告)日：2023-09-21

申请号：US17740443

申请日：2022-05-10

Applicant: General Electric Company

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

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23R2900/03044

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.

公开(公告)号：US11754288B2

公开(公告)日：2023-09-12

申请号：US17115877

申请日：2020-12-09

Applicant: General Electric Company

Inventor： Hari Ravi Chandra ,  Arvind Kumar Rao ,  Shai Birmaher ,  Jayanth Sekar ,  Gurunath Gandikota ,  Michael A. Benjamin

IPC: F23R3/00 ,  F23R3/34 ,  F23R3/28 ,  F02C7/22 ,  F23D14/70 ,  F23D14/64

CPC classification number: F23R3/343 ,  F02C7/222 ,  F23D14/64 ,  F23D14/70 ,  F23R3/286 ,  F05D2240/35 ,  F23D2206/10

Abstract: A mixing assembly for a combustor, including: a pilot mixer and a pilot fuel nozzle; a main mixer including: a main housing surrounding the pilot mixer; a fuel manifold positioned between the pilot housing and the main housing; a mixer foot extending outward from a forward end of the main housing; a main swirler body surrounding the main housing such that an annular mixing channel is defined between the main housing and the main swirler body, and coupled to the mixer foot; and a main fuel ring in the mixing channel downstream of the mixer foot connected to the main housing by main fuel vanes, at least one of the main fuel ring and the main fuel vanes including fuel injection ports positioned to discharge fuel into a central portion of the mixing channel, wherein the mixer foot extends farther from the main housing than the main fuel ring.

公开(公告)号：US20230243311A1

公开(公告)日：2023-08-03

申请号：US17590472

申请日：2022-02-01

Applicant: GENERAL ELECTRIC COMPANY ,  GE Avio S.r.l.

Inventor： David Justin Brady ,  Mirko Gernone ,  Michael A. Benjamin ,  Steven C. Vise

IPC: F02C9/40 ,  F02C7/22 ,  F23R3/36 ,  F23R3/30

CPC classification number: F02C9/40 ,  F02C7/22 ,  F23R3/36 ,  F23R3/30 ,  F05D2220/32 ,  F05D2240/36

Abstract: A fuel supply system for a combustion section of a turbine engine. The turbine engine including a heat source. The fuel supply system comprising a first fuel supply having a liquid fuel, a second fuel supply having a first gaseous fuel, and a heat exchanger fluidly coupled to the first fuel supply and the heat source. The heat exchanger producing a heat sufficient to change the liquid fuel to a second gaseous fuel that is the same type of fuel as the first gaseous fuel.

公开(公告)号：US20230228424A1

公开(公告)日：2023-07-20

申请号：US17725895

申请日：2022-04-21

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Nayan Vinod Patel ,  Michael A. Benjamin

IPC: F02C7/22 ,  F02C3/04 ,  F23R3/14 ,  F23R3/28 ,  F23R3/36

CPC classification number: F02C7/22 ,  F02C3/04 ,  F23R3/14 ,  F23R3/28 ,  F23R3/36 ,  F05D2220/30 ,  F05D2240/35

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.

公开(公告)号：US20230194095A1

公开(公告)日：2023-06-22

申请号：US17700852

申请日：2022-03-22

Applicant: General Electric Company

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

IPC: F23R3/38 ,  F02C7/22

CPC classification number: F23R3/38 ,  F02C7/22

Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and emission needs require the use of alternative fuels, which combust at higher temperatures and faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.