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公开(公告)号：US20200263873A1
公开(公告)日：2020-08-20
申请号：US16278341
申请日：2019-02-18
Applicant: General Electric Company
Abstract: 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.
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公开(公告)号：US10739006B2
公开(公告)日：2020-08-11
申请号：US15459309
申请日：2017-03-15
Applicant: General Electric Company
Inventor： Nayan Vinodbhai Patel , Alfred Albert Mancini , Duane Douglas Thomsen , Michael Anthony Benjamin
Abstract: A fuel nozzle for a gas turbine engine includes an outer body defining a plurality of openings in an exterior surface. The fuel nozzle also includes a main injection ring disposed at least partially inside the outer body. The main injection ring includes a plurality of fuel posts extending into or through the plurality of openings of the outer body. The plurality of fuel posts include an LP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the LP fuel post extending in the top surface in a first direction relative to the centerline axis away from the main fuel orifice. The plurality of fuel posts also include an HP fuel post defining a main fuel orifice, a top surface, and a scarf, the scarf of the HP fuel post extending in the top surface f in a second direction relative to the centerline axis away from the main fuel orifice, the second direction being at least ninety degrees different than the first direction.
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公开(公告)号：US10352570B2
公开(公告)日：2019-07-16
申请号：US15086384
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael Anthony Benjamin , Shih-Yang Hsieh , Yuxin Zhang , Owen James Sullivan Rickey , Nayan Vinodbhai Patel , Duane Douglas Thomsen , Kevin Vandevoorde
Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.
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公开(公告)号：US20190203929A1
公开(公告)日：2019-07-04
申请号：US15861791
申请日：2018-01-04
Applicant: General Electric Company
Inventor： Michael Anthony Benjamin , Girish Venkata Satya Sesha Goda , Habeeb Kunnummal Manat , Karthikeyan Sampath
Abstract: A method and structure for operating a combustion system of a gas turbine engine to mitigate low frequency combustion acoustics is generally provided. The method includes flowing an oxidizer through a fuel nozzle passage defining an inner wall and an outer wall, in which each of the inner wall and the outer wall are contoured from a first radius to a second radius smaller than the first radius; flowing the oxidizer at a higher axial velocity at the inner wall relative to the outer wall upstream of a fuel injection port; flowing a fuel through the fuel injection port to the fuel nozzle passage to mix with the flow of oxidizer to produce a fuel-oxidizer mixture; and igniting the fuel-oxidizer mixture downstream of the fuel injection port.
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公开(公告)号：US20190162413A1
公开(公告)日：2019-05-30
申请号：US15823633
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F23R3/06 , F02C3/04 , F02C7/18 , F02K1/822 , F05D2220/32 , F05D2240/35 , F23R3/002 , F23R3/26
Abstract: A combustor liner, a gas turbine engine including a combustor having the combustor liner, and a method for regulating jet wakes in the combustor are disclosed. The combustor liner includes a panel, at least one first through-hole, and a plurality of second through-holes including first and second set of through-holes. The at least one first through-hole is disposed on a section of the panel in a first row. The plurality of second through-holes is disposed on the section along axial and circumferential directions and arranged adjacent to the at least one first through-hole. The first set and the second set of through-holes are arranged in a second row and a third row respectively. The first, second, and third rows extend along the circumferential direction. The at least one first through-hole and the plurality of second through-holes collectively cover circumferential plane of the section along the first, second, and third rows.
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Patent Agency Ranking
公开(公告)号：US20190162117A1
公开(公告)日：2019-05-30
申请号：US15823732
申请日：2017-11-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Anquan Wang , Hojjat Nasr , Craig Alan Gonyou , Michael Anthony Benjamin
Abstract: A combustor assembly for a turbine engine and method for cooling a portion of the combustor assembly, the combustor assembly comprising a combustor liner defining a combustion chamber with an inlet and an outlet, a fuel dome located in the inlet and having a wall adjacent at least a portion of the combustor liner, and a deflector overlying and spaced from at least a portion of the wall.
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公开(公告)号：US20190063753A1
公开(公告)日：2019-02-28
申请号：US15684083
申请日：2017-08-23
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , Randall Charles Boehm , Michael Anthony Benjamin , Beverly Stephenson Duncan , Jeffrey Lyal Powell
Abstract: Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.
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118.发明授权公开(公告)号：US10184665B2
公开(公告)日：2019-01-22
申请号：US14735732
申请日：2015-06-10
Applicant: General Electric Company
Abstract: A fuel nozzle is provided for a gas turbine engine, and can include a pilot fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot centerbody wall, with the axially-elongated, inner pilot centerbody wall extending from an upstream end to an annular fuel passage defining the downstream end of the pilot fuel injector. The fuel passage intersects with the inner pilot centerbody wall at a pilot fuel metering orifice. The fuel nozzle also includes a pilot fuel film surface downstream from the annular fuel passage and an annular splitter surrounding the pilot fuel injector. The annular splitter comprises, in axial sequence: an upstream section, a splitter throat having a diameter that is larger than a downstream diameter defined by the pilot fuel film surface, and a downstream diverging surface having an average diverging angle of about 24° to about 40° in relation to a centerline axis.
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公开(公告)号：US10072845B2
公开(公告)日：2018-09-11
申请号：US14443160
申请日：2013-11-15
Applicant: General Electric Company
Inventor： Joshua Tyler Mook , Michael Anthony Benjamin , David Richard Barnhart , Sean James Henderson , Ramon Martinez , Neerav Atul Patel , Mark Richard Shaw
CPC classification number: F23R3/283 , B23P6/005 , B23P15/00 , F02C7/18 , F23R3/14 , F23R2900/00005 , F23R2900/03042 , F23R2900/03044 , Y02T50/675
Abstract: An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.
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公开(公告)号：US20170284678A1
公开(公告)日：2017-10-05
申请号：US15086384
申请日：2016-03-31
Applicant: General Electric Company
Inventor： Krishnakumar Venkatesan , Michael Anthony Benjamin , Shih-Yang Hsieh , Yuxin Zhang , Owen James Sullivan Rickey , Nayan Vinodbhai Patel , Duane Douglas Thomsen , Kevin Vandevoorde
CPC classification number: F23R3/38 , F02C7/22 , F23D2900/11101 , F23R3/14 , F23R3/28
Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.
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