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41. 发明授权

US10393382B2 Multi-point injection mini mixing fuel nozzle assembly 有权
公开(公告)号：US10393382B2
公开(公告)日：2019-08-27
申请号：US15343634
申请日：2016-11-04
申请人： General Electric Company
发明人： Gregory Allen Boardman , Pradeep Naik , Manampathy Gangadharan Giridharan , David Albin Lind , Jeffrey Michael Martini , Clayton S. Cooper
IPC分类号： F23R3/28 , F23R3/04 , F23R3/14
摘要： The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward the downstream end of the fuel injector, and a thermal management conduit. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward a downstream end of the fuel injector. The outer wall, the inner wall, and the end wall together define a fluid conduit extended in a first direction toward the downstream end of the fuel injector and in a second direction toward an upstream end of the fuel injector. The outer sleeve and the centerbody define a premix passage radially therebetween and an outlet at the downstream end of the premix passage. The outer sleeve defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve. The outer sleeve defines a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve. The outer sleeve further defines a first fluid passage arranged between each first air inlet port and extended from the end wall. A fluid passage wall extends from the end wall within the first fluid passage to define a second fluid passage extended from the end wall within the first fluid passage. The outer sleeve further defines a first injection port in fluid communication with the first fluid passage and a second injection port in fluid communication with the second fluid passage. The thermal management conduit is defined by the fluid communication of the fluid conduit and the first fluid passage and the thermal communication of the second fluid passage in adjacent arrangement with the first fluid passage.

42. 发明申请

US20190226398A1 ULTRA COMPACT COMBUSTOR 审中-公开
公开(公告)号：US20190226398A1
公开(公告)日：2019-07-25
申请号：US16133362
申请日：2018-09-17
申请人： General Electric Company
发明人： Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Peter Daniel Silkowski
IPC分类号： F02C3/14 , B23P15/04 , F23R3/12 , F01D9/02 , F23R3/50 , F23R3/44 , F23R3/34 , F23R3/28 , F23R3/26 , F23R3/14 , F23R3/04 , F23R3/00 , F04D29/56 , F04D29/54 , F04D27/02 , F02C3/04
摘要： Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

43. 发明授权

US10337334B2 Gas turbine engine component with a baffle insert 有权
公开(公告)号：US10337334B2
公开(公告)日：2019-07-02
申请号：US14961685
申请日：2015-12-07
申请人： United Technologies Corporation
发明人： Brandon W. Spangler , Atul Kohli
IPC分类号： F01D5/18 , F23R3/00 , F23R3/04 , F01D9/02 , F01D11/08 , F01D25/12
摘要： A component of a gas turbine engine, the component having: an internal cooling cavity extending through an interior of the component; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; and at least one rib extending upwardly from the exterior surface of the baffle insert, wherein the plurality of trip strips and the at least one rib are spaced from an interior surface of the internal cooling cavity.

44. 发明申请

US20190162117A1 TURBINE ENGINE WITH COMBUSTOR 审中-公开
公开(公告)号：US20190162117A1
公开(公告)日：2019-05-30
申请号：US15823732
申请日：2017-11-28
申请人： GENERAL ELECTRIC COMPANY
发明人： Anquan Wang , Hojjat Nasr , Craig Alan Gonyou , Michael Anthony Benjamin
IPC分类号： F02C7/18 , F23R3/00 , F23R3/28 , F23R3/04
摘要： 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.

45. 发明申请

US20190128524A1 COMBUSTOR AND GAS TURBINE INCLUDING THE SAME 审中-公开
公开(公告)号：US20190128524A1
公开(公告)日：2019-05-02
申请号：US16166468
申请日：2018-10-22
申请人： DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
发明人： Donggon LEE
IPC分类号： F23R3/04 , F02C7/18
摘要： A combustor includes an inner liner forming a combustion chamber; an outer liner surrounding the inner liner to form a cooling passage in which compressed air flows; and a plurality of cooling guides installed around an inner circumferential surface of the outer liner to surround the combustion chamber, each of the cooling guides protruding from the inner circumferential surface to create an impinging jet from the compressed air flowing in the cooling passage. The plurality of cooling guides surrounding the combustion chamber are installed at regular intervals in a flow direction of the compressed air, and are arranged in staggered axial rows. Each cooling guide includes an air guiding surface facing the flow of the compressed air to guide the compressed air toward the inner liner. Accordingly, liner cooling efficiency can be enhanced by more effectively guiding the impinging jet toward the inner liner.

46. 发明申请

US20190128523A1 DOUBLE SKIN COMBUSTOR 审中-公开
公开(公告)号：US20190128523A1
公开(公告)日：2019-05-02
申请号：US15798906
申请日：2017-10-31
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Robert SZE , Sri SREEKANTH , Honza STASTNY , Jeffrey VERHIEL
IPC分类号： F23R3/04 , F23R3/00
摘要： There is disclosed a double skin combustor for a gas turbine engine. The combustor has a radially inner liner and a radially outer liner defining therebetween an annular combustion chamber. The radially inner liner and the radially outer liners both have a hot skin and a cold skin defining a cooling cavity therebetween. The cold skin has a plurality of segments joined to one another by sliding joints. The cooling cavity between the hot skin and the cold skin may be compartmentalized into individual cavities between the sliding joints.

47. 发明申请

US20190128187A1 FLOAT WALL COMBUSTOR PANELS HAVING AIRFLOW DISTRIBUTION FEATURES 审中-公开
公开(公告)号：US20190128187A1
公开(公告)日：2019-05-02
申请号：US15795301
申请日：2017-10-27
申请人： United Technologies Corporation
发明人： Jason Shenny , John J. Rup, JR. , Robert M. Sonntag , James B. Hoke , San Quach , Richard G. Ullrich
IPC分类号： F02C7/18 , F23R3/00 , F23R3/04
摘要： Combustor panels including panel bodies with first and second sides, a pin array extending from the first side, wherein each pin extends a first height, has a pin diameter, and is separated from adjacent pins by a pin array separation distance. A structural protrusion extends from the first side. No pins of the pin array are located within a flashing distance that is equal to a protrusion separation distance plus half of the pin diameter, wherein a location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. At least one pin array extension is integrally formed with the structural protrusion, the pin array extension extending along the first side to a position that replaces a pin of the pin array that would be within the flashing distance.

48. 发明授权

US10253985B2 Sequential liner for a gas turbine combustor 有权
公开(公告)号：US10253985B2
公开(公告)日：2019-04-09
申请号：US15050161
申请日：2016-02-22
申请人： General Electric Technology GmbH
发明人： Michael Thomas Maurer , Jeffrey De Jonge , Felix Baumgartner , Patrik Meng
IPC分类号： F23R3/04 , F01P7/02 , F23R3/00
摘要： The invention concerns a sequential liner for a gas turbine combustor, having a sequential liner outer wall spaced apart from a sequential liner inner wall to define a sequential liner cooling channel between the sequential liner outer wall and the sequential liner inner wall. The sequential liner outer wall includes a first face, a first adjacent face and a second adjacent face, the first and second adjacent faces each being adjacent to the first face, the first face of the sequential liner outer wall having a first convective cooling hole adjacent to the first adjacent face and a second convective cooling hole adjacent to the second adjacent face, each convective cooling hole being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face. The invention also concerns a method of cooling using the sequential liner and a method of retrofitting a gas turbine.

49. 发明授权

US10253690B2 Turbine system with exhaust gas recirculation, separation and extraction 有权
公开(公告)号：US10253690B2
公开(公告)日：2019-04-09
申请号：US15014950
申请日：2016-02-03
申请人： General Electric Company , ExxonMobil Upstream Research Company
发明人： Jonathan Kay Allen , Bradford David Borchert , Jesse Edwin Trout , Ilya Aleksandrovich Slobodyanskiy , Almaz Valeev , Igor Petrovich Sidko , Andrey Pavlovich Subbota
IPC分类号： F23R3/28 , F23C9/00 , F02C3/34 , F23R3/00 , F23R3/04 , F23R3/26 , F23C9/08
摘要： A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.

50. 发明申请

US20190093891A1 GAS TURBINE ASSEMBLIES AND METHODS 审中-公开
公开(公告)号：US20190093891A1
公开(公告)日：2019-03-28
申请号：US15714118
申请日：2017-09-25
申请人： General Electric Company
发明人： Owen Graham , Kwanwoo Kim , Nicholas Magina , Sharath Nagaraja , Fei Han
IPC分类号： F23R3/26 , F23R3/00 , F23R3/28 , F23R3/04
摘要： The systems and methods described herein relate to a dome of a gas turbine assembly configured to suppress pressure pulsations. The systems and methods provide a dome having an aperture configured to surround an injector assembly of a combustor. The dome having a front panel extending radially from the aperture. The systems and methods couple a first cavity to the front panel. The first cavity includes a series of ducts. A first duct of the series of ducts is configured to receive airflow into the first cavity from a compressor and a second set of ducts of the series of ducts and a third duct of the series of ducts are configured to direct airflow to the combustor from the first cavity, wherein the third duct has a larger diameter than the second set of ducts.

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