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1. 发明授权

US11454396B1 Fuel injector and pre-mixer system for a burner array 有权
公开(公告)号：US11454396B1
公开(公告)日：2022-09-27
申请号：US17340614
申请日：2021-06-07
申请人： General Electric Company
发明人： Gregory A. Boardman , Vishal Sanjay Kediya , Pradeep Naik , Jeffrey M. Martini
IPC分类号： F23R3/14 , F23R3/28 , F23C7/00
摘要： A fuel injector and mini-mixer system includes a mixing element tube configured to mix air and fuel prior to injecting the air and fuel into a combustor, an injector positioned within the mixing element tube, the injector being configured to inject a fluid into the mixing element tube, one or more air inlet slots positioned on one or more sides of the injector, one or more fuel injection holes configured to inject fuel into the mixing element tube, and one or more delta wing vortex generators positioned within an internal wall of the mixing element tube, the one or more delta wing vortex generators configured to generate a vortex pair that accelerates the mixing of air and fuel injected into the mixing element tube. Additional air slots can be provided downstream of the delta wing vortex generators to energize the vortex pair or lift fuel away to prevent flameholding.

2. 发明申请

US20220290862A1 FUEL MIXER 有权
公开(公告)号：US20220290862A1
公开(公告)日：2022-09-15
申请号：US17199244
申请日：2021-03-11
申请人： General Electric Company
发明人： Vishal Sanjay Kediya , Pradeep Naik , Gregory A. Boardman , Manampathy G. Giridharan
IPC分类号： F23R3/28 , F02C7/22
摘要： A mixer for providing a fuel-air mixer to a combustor of an engine. The mixer may include a fuel flow and an air flow entering an interior passage of the mixer. The air flow may be comprised of three separate air flows. The first air flow may be parallel to a central axis of the mixer for pulling the fuel into the interior passage. The second air flow may be inclined with respect to the central axis of the mixer and the third air flow may be tangential to the mixer body. The second air flow and the third air flow may push the fuel flow toward the interior passage and away from the boundary layer flow.

3. 发明申请

US20220325891A1 DILUTION HORN PAIR FOR A GAS TURBINE ENGINE COMBUSTOR 有权
公开(公告)号：US20220325891A1
公开(公告)日：2022-10-13
申请号：US17228433
申请日：2021-04-12
申请人： General Electric Company
发明人： Vishal Sanjay Kediya , Pradeep Naik , Ajoy Patra , Narasimhan S. Sahana
IPC分类号： F23R3/10 , F02C3/00
摘要： A combustor for a gas turbine engine has an annular inner liner and an annular outer liner forming a combustion chamber therebetween. A dilution horn pair includes dilution horns that provide a flow of an oxidizer gas into the combustion chamber in a dilution zone. At least one of the dilution horns forming the dilution horn pair is arranged so as to provide a lateral flow component of the flow of oxidizer gas therethrough into the combustion chamber, the lateral flow component having a flow direction extending laterally across and non-orthogonal to an axial flow direction of combustion gases within the combustion chamber.

4. 发明申请

US20200263873A1 Fuel Nozzle Assembly 审中-公开
公开(公告)号：US20200263873A1
公开(公告)日：2020-08-20
申请号：US16278341
申请日：2019-02-18
申请人： General Electric Company
发明人： Gregory Allen Boardman , Michael Anthony Benjamin , Pradeep Naik , Vishal Sanjay Kediya
IPC分类号： F23R3/28 , F02C7/22
摘要： A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. A centerbody is positioned radially inward of the outer sleeve. The centerbody includes an outer annular wall extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve further includes a first radial wall extended from a downstream end of the outer annular wall. The centerbody defines a plenum radially inward thereof. The outer annular wall and the outer sleeve together define a first fuel air mixing passage extended along the longitudinal direction therebetween. A fuel injector is disposed in the plenum. The fuel injector includes a tubular outer wall extended co-directional to the fuel nozzle centerline. The outer wall defines a second fuel air mixing passage therewithin. The second fuel air mixing passage is extended through the first radial wall of the centerbody.

5. 发明申请

US20230003385A1 PREMIXER ARRAY 有权
公开(公告)号：US20230003385A1
公开(公告)日：2023-01-05
申请号：US17367036
申请日：2021-07-02
申请人： General Electric Company
发明人： Pradeep Naik , Gregory A. Boardman , Vishal Sanjay Kediya
IPC分类号： F23R3/28 , F23R3/50 , F23R3/04
摘要： A premixer array for a gas turbine engine includes a plurality of swirled premixer tubes and a plurality of non-swirled premixer tubes. The premixer array further includes a pilot tube for providing a pilot product. The plurality of swirled premixer tubes may guide and spread out the pilot product in a radial direction, in a circumferential direction, or both in a radial direction and a circumferential direction. The plurality of swirled premixer tubes may include clockwise swirled and counterclockwise swirled premixers. Also, included is a method of controlling the flow of pilot products.

6. 发明授权

US11506388B1 Furcating pilot pre-mixer for main mini-mixer array in a gas turbine engine 有权
公开(公告)号：US11506388B1
公开(公告)日：2022-11-22
申请号：US17315016
申请日：2021-05-07
申请人： General Electric Company
发明人： Gregory A. Boardman , Pradeep Naik , Bassam Sabry Mohammad Abdelnabi , Manampathy G. Giridharan , Vishal Sanjay Kediya , Narasimhan S. Sahana
IPC分类号： F23R3/34 , F23R3/28
摘要： A pilot pre-mixer for a gas turbine engine has a pilot body that includes an internal mixing chamber, a first end on an upstream side of the internal mixing chamber, a second end on a downstream side of the internal mixing chamber, a fuel injector at the first end and communicable with the internal mixing chamber, a plurality of first oxidizer inlet ports arranged to provide an oxidizer agent from outside of the pilot body to the internal mixing chamber, and a plurality of pilot outlet ports at the second end and communicable with the internal mixing chamber, each of the plurality of pilot outlet ports having an outlet on the second end for dispensing a pilot fluid mixture into a combustion zone of a combustor.

7. 发明申请

US20220290863A1 GAS TURBINE FUEL MIXER COMPRISING A PLURALITY OF MINI TUBES FOR GENERATING A FUEL-AIR MIXTURE 有权
公开(公告)号：US20220290863A1
公开(公告)日：2022-09-15
申请号：US17199257
申请日：2021-03-11
申请人： General Electric Company
发明人： Pradeep Naik , Manampathy G. Giridharan , Vishal Sanjay Kediya , Gregory A. Boardman
IPC分类号： F23R3/28 , F02C7/22 , F23R3/12
摘要： A mixer for blending fuel and air in a combustor of a turbine engine. The mixer includes a central body having a central passageway and a central axis. The mixer includes a plurality of tubes positioned radially around the central axis and circumferentially around a periphery of the mixer. Each of the tubes of the mixer includes opposed openings and a tangential opening. Each of the tubes of the mixer includes a cylindrical interior mixing passage configured to receive air flow from the opposed openings and the tangential opening and a fuel flow. The opposed openings are configured to spread the fuel flow laterally and the tangential opening is configured to spread the fuel flow tangentially.

8. 发明申请

US20220357038A1 FURCATING PILOT PRE-MIXER FOR MAIN MINI-MIXER ARRAY IN A GAS TURBINE ENGINE 有权
公开(公告)号：US20220357038A1
公开(公告)日：2022-11-10
申请号：US17315016
申请日：2021-05-07
申请人： General Electric Company
发明人： Gregory A. Boardman , Pradeep Naik , Bassam Sabry Mohammad Abdelnabi , Manampathy G. Giridharan , Vishal Sanjay Kediya , Narasimhan S. Sahana
IPC分类号： F23R3/28 , F23R3/34 , F23D14/58
摘要： A pilot pre-mixer for a gas turbine engine has a pilot body that includes an internal mixing chamber, a first end on an upstream side of the internal mixing chamber, a second end on a downstream side of the internal mixing chamber, a fuel injector at the first end and communicable with the internal mixing chamber, a plurality of first oxidizer inlet ports arranged to provide an oxidizer agent from outside of the pilot body to the internal mixing chamber, and a plurality of pilot outlet ports at the second end and communicable with the internal mixing chamber, each of the plurality of pilot outlet ports having an outlet on the second end for dispensing a pilot fluid mixture into a combustion zone of a combustor.

9. 发明授权

US11156360B2 Fuel nozzle assembly 有权
公开(公告)号：US11156360B2
公开(公告)日：2021-10-26
申请号：US16278341
申请日：2019-02-18
申请人： General Electric Company
发明人： Gregory Allen Boardman , Michael Anthony Benjamin , Pradeep Naik , Vishal Sanjay Kediya
IPC分类号： F23R3/00 , F23R3/28 , F02C7/22
摘要： A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. A centerbody is positioned radially inward of the outer sleeve. The centerbody includes an outer annular wall extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction co-directional to the fuel nozzle centerline. The outer sleeve further includes a first radial wall extended from a downstream end of the outer annular wall. The centerbody defines a plenum radially inward thereof. The outer annular wall and the outer sleeve together define a first fuel air mixing passage extended along the longitudinal direction therebetween. A fuel injector is disposed in the plenum. The fuel injector includes a tubular outer wall extended co-directional to the fuel nozzle centerline. The outer wall defines a second fuel air mixing passage therewithin. The second fuel air mixing passage is extended through the first radial wall of the centerbody.

10. 发明授权

US10935245B2 Annular concentric fuel nozzle assembly with annular depression and radial inlet ports 有权
公开(公告)号：US10935245B2
公开(公告)日：2021-03-02
申请号：US16196383
申请日：2018-11-20
申请人： General Electric Company
发明人： Gregory Allen Boardman , Manampathy Gangadharan Giridharan , Michael Anthony Benjamin , Pradeep Naik , Clayton Stuart Cooper , Vishal Sanjay Kediya
IPC分类号： F23R3/28 , F02C7/22
摘要： A fuel nozzle for a gas turbine engine is generally provided. The fuel nozzle includes an outer sleeve extended circumferentially around a fuel nozzle centerline and extended along a longitudinal direction substantially co-directional to the fuel nozzle centerline. The outer sleeve defines a plurality of first radially oriented air inlet ports through the outer sleeve in circumferential arrangement relative to the fuel nozzle centerline. The fuel nozzle further includes a centerbody positioned radially inward of the outer sleeve. The centerbody is extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline and wherein the centerbody is concentric to the fuel nozzle centerline and the outer sleeve. The centerbody defines a plurality of second radially oriented air inlet ports through the centerbody in circumferential arrangement relative to the fuel nozzle centerline. The centerbody further defines an annular centerbody groove or depression relative to the fuel nozzle centerline at a downstream end directly adjacent to a combustion chamber. The fuel nozzle further includes an inner sleeve extended circumferentially around the fuel nozzle centerline and extended along the longitudinal direction substantially co-directional to the fuel nozzle centerline. The inner sleeve is positioned radially between the outer sleeve and the centerbody. The inner sleeve further defines an annular inner sleeve depression relative to the fuel nozzle centerline at the downstream end directly adjacent to the combustion chamber. The outer sleeve and the inner sleeve together define a first fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber. The inner sleeve and the centerbody together further define a second fuel air mixing passage radially therebetween and extended substantially along the longitudinal direction in direct fluid communication with the combustion chamber.

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