-
21.发明申请ASSEMBLY FOR CONTROLLING CLEARANCE BETWEEN A LINER AND STATIONARY NOZZLE WITHIN A GAS TURBINE 审中-公开用于控制气体涡轮机内衬和静止喷嘴之间的间隙的组件公开(公告)号：US20140260280A1
公开(公告)日：2014-09-18
申请号：US13845565
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Christopher Paul Willis , Richard Martin DiCintio , Patrick Benedict Melton , Lucas John Stoia
IPC: F23R3/00
CPC classification number: F23R3/002 , F01D9/023 , F01D11/18 , F01D25/24 , F05D2230/642 , F05D2300/50212 , F23R3/005 , F23R3/60 , F23R2900/00012
Abstract: An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell.
Abstract translation: 用于控制燃气涡轮机内的衬套和静止喷嘴之间的间隙的组件包括具有设置在衬套的后端的后框架的环形衬套和联接到后架的安装支架。 组件还包括涡轮机，其具有至少部分地限定涡轮机入口的外涡轮机外壳和内涡轮机外壳。 固定喷嘴设置在后框架和入口之间。 固定喷嘴包括顶部平台部分，其具有朝向后部框架延伸的前缘和底部平台部分。 在后框架的后端和顶部平台部分的前缘之间限定间隙。 安装支架联接到外涡轮机外壳，而固定喷嘴与内涡轮机外壳相连。
-
公开(公告)号：US11774099B2
公开(公告)日：2023-10-03
申请号：US17852617
申请日：2022-06-29
Applicant: General Electric Company
Inventor： Charlie Edmond Jones , Lucas John Stoia , Homayoon Feiz , Anthony Michael DiNardi
Abstract: A fuel nozzle includes a center body that extends from an upstream end to a downstream end. A nozzle tip, which is fixedly coupled to the downstream end of the center body, includes an outer annular wall that has a forward end and an aft end. A solid aft wall is disposed at the aft end of the outer annular wall. The solid aft wall and the outer annular wall at least partially define a plenum. A nozzle portion, which is disposed within the plenum, includes an inner annular wall and an impingement wall. The impingement wall is spaced apart from the solid aft wall and defines a plurality of apertures configured to direct fluid to impinge upon the solid aft wall. A plurality of outlets is defined in the outer annular wall forward of the solid aft wall to direct post-impingement fluid from the nozzle tip.
-
公开(公告)号：US11629857B2
公开(公告)日：2023-04-18
申请号：US17218393
申请日：2021-03-31
Applicant: General Electric Company
Inventor： Lucas John Stoia , Homayoon Feiz , Shreekrishna Rao , Emily Klara Happ
Abstract: Combustors and gas turbines are provided. A combustor includes an axial centerline and an end cover. The combustor further includes at least one fuel nozzle that extends from the end cover and at is least partially surrounded by a combustion liner. The combustion liner extends between the at least one fuel nozzle and an aft frame and that defines a combustion chamber. An outer sleeve is spaced apart from and surrounds the combustion liner such that an annulus is defined therebetween. The outer sleeve defines at least one aperture. A wake energizer is mounted on the outer sleeve. The wake energizer defines at least one passage that is angled with respect to the axial centerline of the combustor. The at least one passage aligns and is in fluid communication with the at least one aperture of the outer sleeve.
-
公开(公告)号：US20220404020A1
公开(公告)日：2022-12-22
申请号：US17350529
申请日：2021-06-17
Applicant: General Electric Company
Inventor： Lucas John Stoia , Terese Marinita Martinez , Ronnie Ray Pentecost , Elizabeth Leigh Exley
Abstract: A combustor includes an end cover and at least one fuel nozzle extending from the end cover and at least partially surrounded by a combustion liner. The combustor further includes an outer sleeve spaced apart from and surrounding the combustion liner such that an annulus is defined therebetween. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extending to the fuel injector. A shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The at least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.
-
公开(公告)号：US20220316708A1
公开(公告)日：2022-10-06
申请号：US17218393
申请日：2021-03-31
Applicant: General Electric Company
Inventor： Lucas John Stoia , Homayoon Feiz , Shreekrishna Rao , Emily Klara Happ
Abstract: Combustors and gas turbines are provided. A combustor includes an axial centerline and an end cover. The combustor further includes at least one fuel nozzle that extends from the end cover and at is least partially surrounded by a combustion liner. The combustion liner extends between the at least one fuel nozzle and an aft frame and that defines a combustion chamber. An outer sleeve is spaced apart from and surrounds the combustion liner such that an annulus is defined therebetween. The outer sleeve defines at least one aperture. A wake energizer is mounted on the outer sleeve. The wake energizer defines at least one passage that is angled with respect to the axial centerline of the combustor. The at least one passage aligns and is in fluid communication with the at least one aperture of the outer sleeve.
-
Patent Agency Ranking
公开(公告)号：US20220034509A1
公开(公告)日：2022-02-03
申请号：US16940965
申请日：2020-07-28
Applicant: General Electric Company
Inventor： Neal William Grooms , Charlie Edmond Jones , Lucas John Stoia
Abstract: An insert for an impingement plate and an impingement plate including the insert are disclosed. The impingement plate includes a plurality of cooling holes therein. The insert includes a body including an opening extending longitudinally therethrough. The body also includes a discharge end configured for positioning in an impingement air plenum between the impingement plate and an upstream surface of a combustor cap plate; a flexible insertion end configured for insertion into a respective cooling hole of the plurality of cooling holes; and a fixation element between the discharge end and the flexible insertion end. The fixation element has an outer dimension configured to fixedly couple the body in the respective cooling hole.
-
公开(公告)号：US11187152B1
公开(公告)日：2021-11-30
申请号：US17038370
申请日：2020-09-30
Applicant: General Electric Company
Inventor： Emily Klara Happ , Lucas John Stoia
Abstract: A sealing arrangement includes a transition duct having an aft frame that circumferentially surrounds the downstream end of the transition duct. The aft frame defines a cooling circuit that has an outlet configured to direct cooling air in a radial direction. A first stage nozzle is spaced apart from the aft frame and defines a gap therebetween. A sealing assembly that extend circumferentially along at least a portion of the aft frame and is coupled to the aft frame. The sealing assembly includes a flexible sealing element that extends from the aft frame, across the gap, to the first stage nozzle. The flexible sealing element is forced into sealing engagement with the first stage nozzle by pressure from a compressed working fluid. A cooling flow director that is disposed between the outlet of the cooling circuit and the flexible sealing element.
-
公开(公告)号：US10578306B2
公开(公告)日：2020-03-03
申请号：US15625044
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Timothy James Purcell , Ronald James Chila , Lucas John Stoia
Abstract: A liquid fuel cartridge unit for a gas turbine combustor includes a cartridge tip having an aft plate and a side wall circumscribing the aft plate. First injection ports are defined through the side wall, and second injection ports are defined through the side wall upstream of the first injection ports, relative to fuel flow through the cartridge tip. Nested conduits extend into the cartridge tip with the concentric conduits defining therebetween respective flow passages. The first injection ports are in fluid communication with a first flow passage, and the second injection ports are in fluid communication with a second flow passage. A method of assembling the liquid fuel cartridge unit is also provided.
-
公开(公告)号：US20180363907A1
公开(公告)日：2018-12-20
申请号：US15625044
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Timothy James Purcell , Ronald James Chila , Lucas John Stoia
CPC classification number: F23R3/286 , F02C7/22 , F23D11/38 , F23R3/04 , F23R3/28 , F23R3/283 , F23R3/34 , F23R3/343 , F23R3/36 , F23R2900/00004
Abstract: A liquid fuel cartridge unit for a gas turbine combustor includes a cartridge tip having an aft plate and a side wall circumscribing the aft plate. First injection ports are defined through the side wall, and second injection ports are defined through the side wall upstream of the first injection ports, relative to fuel flow through the cartridge tip. Nested conduits extend into the cartridge tip with the concentric conduits defining therebetween respective flow passages. The first injection ports are in fluid communication with a first flow passage, and the second injection ports are in fluid communication with a second flow passage. A method of assembling the liquid fuel cartridge unit is also provided.
-
公开(公告)号：US20180306118A1
公开(公告)日：2018-10-25
申请号：US15496021
申请日：2017-04-25
Applicant: General Electric Company
Inventor： Donald Mark Bailey , Mark William Pinson , Lucas John Stoia
Abstract: The present disclosure is directed to an end cover assembly for a combustor of a turbomachine. The end cover assembly includes an end cover and a bundled tube fuel nozzle assembly positioned downstream from the end cover. The bundled tube fuel nozzle assembly includes a plurality of fuel nozzle tubes. A flame detector sight tube couples to the end cover. The flame detector sight tube is aligned with one of the fuel nozzle tubes.
-
-
-
-
-
-
-
-
-
Search Results
118
records
(took 0.019 seconds)
