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31. 发明授权

US10465907B2 System and method having annular flow path architecture 有权
公开(公告)号：US10465907B2
公开(公告)日：2019-11-05
申请号：US14849552
申请日：2015-09-09
申请人： General Electric Company
发明人： Nan Zong , Ahmed Mostafa ELKady , Mark Anthony Mueller , Pradeep Naik , Gerardo Antonio Salazar Lois , Rishikesh Prakash Karande , Jeffrey Michael Martini
IPC分类号： F23R3/04 , F23R3/00 , F23R3/10 , F23R3/28 , F23R3/44 , F23R3/46 , F04D29/54 , F23R3/50 , F23R3/54
摘要： A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.

32. 发明授权

US10370990B2 Flow path assembly with pin supported nozzle airfoils 有权
公开(公告)号：US10370990B2
公开(公告)日：2019-08-06
申请号：US15440320
申请日：2017-02-23
申请人： General Electric Company
发明人： Brandon ALlanson Reynolds , Jonathan David Baldiga
IPC分类号： F01D9/04 , F23R3/00 , F01D25/00 , F01D25/24 , F23R3/10 , F23R3/60 , F01D9/02
摘要： Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and an outer wall defining an opening therethrough, as well as a nozzle airfoil having an inner end radially opposite an outer end that is positioned within the opening defined in the outer wall such that the outer end projects radially outwardly from the outer wall. The flow path assembly also comprises a pin and a first support member. The pin extends from the first support member to the outer end of the nozzle airfoil to support the nozzle airfoil. In some embodiments, the outer end of the nozzle airfoil defines a flange configured to receive the pin and a radial stop configured to press against a radially outward external support, and the pin is configured to transfer a load on the nozzle airfoil to an external structure.

33. 发明授权

US10364988B2 Fuel nozzle 有权
公开(公告)号：US10364988B2
公开(公告)日：2019-07-30
申请号：US15788092
申请日：2017-10-19
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Eduardo David Hawie , Nigel Davenport , Yen-Wen Wang
IPC分类号： F23R3/28 , F23D11/10 , F23R3/10
摘要： A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine includes directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, filming the concentric two fuel flows on concentrically arranged inwardly facing filming surfaces that are disposed downstream of the flow splitter, and atomizing the concentric fuel flows into a core air flow.

34. 发明授权

US10352569B2 Multi-point centerbody injector mini mixing fuel nozzle assembly 有权
公开(公告)号：US10352569B2
公开(公告)日：2019-07-16
申请号：US15343672
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
IPC分类号： F23R3/28 , F23R3/10 , F23R3/04
摘要： The present disclosure is directed to a fuel injector for a gas turbine engine. The fuel injector includes an end wall defining a fluid chamber, a centerbody, an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector, and a fluid cavity wall. The centerbody includes an axially extended outer wall and inner wall extended from the end wall toward the 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 fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. 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 further defines a plurality of radially oriented first air inlet ports in circumferential arrangement at a first axial portion of the outer sleeve, and a plurality of radially oriented second air inlet ports in circumferential arrangement at a second axial portion of the outer sleeve. The fluid cavity wall is disposed axially between the first air inlet port and the second air inlet port and extends radially from the outer sleeve toward the centerbody. The fluid cavity wall defines a fluid cavity and a second fluid injection port in fluid communication with the fluid cavity. The second fluid injection port is in fluid communication with the premix passage.

35. 发明申请

US20190212008A1 COMBUSTOR HEAT SHIELD 审中-公开
公开(公告)号：US20190212008A1
公开(公告)日：2019-07-11
申请号：US16299386
申请日：2019-03-12
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Michael PAPPLE , Robert SZE
IPC分类号： F23R3/00 , F23R3/10 , F23R3/04
CPC分类号： F23R3/005 , F05D2260/20 , F23R3/002 , F23R3/04 , F23R3/10 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A gas turbine engine combustor has a dome and a shell extending axially from the dome. The dome and the shell cooperates to define a combustion chamber. A dome heat shield is mounted to the dome inside the combustion chamber. A front heat shield is mounted to the shell inside the combustion chamber. The dome heat shield and the front heat shield have axially overlapping portions cooperating to define a flow guiding channel. The flow guiding channel has a length (L) and a height (h). The length (L) is at least equal to the height (h).

36. 发明授权

US10295191B2 Gas turbine engine and annular combustor with swirler 有权
公开(公告)号：US10295191B2
公开(公告)日：2019-05-21
申请号：US13341941
申请日：2011-12-31
申请人： Jushan Chin
发明人： Jushan Chin
IPC分类号： F23R3/52 , F23R3/34 , F23R3/10 , F23R3/14
摘要： A combustor is provided in which a fuel and working fluid can be injected in an annulus. In one form the fuel and working fluid is circumferentially flowed within the annulus and traverses the annulus in an axial direction from one side to another side where the flow exits. The working fluid and air can be co-axially admitted to the combustor and in one form the working fluid can be swirled about the fuel dispensed from a fuel injector. The combustor can provide for a rich burning zone. In one embodiment the combustor is configured as an inter-turbine combustor having an outlet at one axial side of the combustor. A lean burn region can be created within a flow path of the turbine.

37. 发明授权

US10295190B2 Centerbody injector mini mixer fuel nozzle assembly 有权
公开(公告)号：US10295190B2
公开(公告)日：2019-05-21
申请号：US15343601
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
IPC分类号： F23R3/28 , F23R3/10
摘要： The present disclosure is directed to a fuel injector for a gas turbine engine including an end wall defining a fluid chamber, a centerbody, and an outer sleeve surrounding the centerbody from the end wall toward a downstream end of the fuel injector. The centerbody includes an axially extended outer wall and inner wall. The outer wall and inner wall extend from the end wall toward the 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 fluid conduit is in fluid communication with the fluid chamber. The outer wall defines at least one radially oriented fluid injection port in fluid communication with the fluid conduit. 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.

38. 发明授权

US10288290B2 Device for improved air and fuel distribution to a combustor 有权
公开(公告)号：US10288290B2
公开(公告)日：2019-05-14
申请号：US15139970
申请日：2016-04-27
申请人： Siemens Energy, Inc.
发明人： Walter Ray Laster , Reinhard Schilp
IPC分类号： F01D17/16 , F23R3/10 , F23R3/14 , F02C9/20 , F23R3/26 , F01D17/14
摘要： A flow conditioning device for a can annular gas turbine engine, including a plurality of flow elements disposed in a compressed air flow path leading to a combustor, configured such that relative adjustment of at least one flow directing element with respect to an adjacent flow directing element during operation of the gas turbine engine is effective to adjust a level of choking of the compressed air flow path.

39. 发明申请

US20190107283A1 COMBUSTOR AND GAS TURBINE 审中-公开
公开(公告)号：US20190107283A1
公开(公告)日：2019-04-11
申请号：US16087882
申请日：2017-03-28
申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.
发明人： Kenji MIYAMOTO , Satoshi TAKIGUCHI , Keijiro SAITO , Shinji AKAMATSU , Shinichi FUKUBA
IPC分类号： F23R3/18 , F02C3/04 , F23R3/10 , F23R3/28
摘要： A combustor includes: a first nozzle which extends along an axis and injects fuel toward a downstream side; a flame stabilizer which covers a downstream-side end portion of the first nozzle from an outer periphery side; and a plurality of second nozzles arranged at intervals in a circumferential direction around the axis on the outer periphery side of the flame stabilizer. The flame stabilizer has a cone portion expanding in diameter toward the downstream side from the upstream side, and a flange portion extending radially outward from a downstream-side end edge of the cone portion, and a penetrating portion which penetrates at least the flange portion in a direction of the axis is formed in the flame stabilizer.

40. 发明申请

US20190093893A1 COMBUSTION CHAMBER ASSEMBLY COMPRISING THERMAL SHIELD AND BURNER GASKET AS WELL AS MANUFACTURING METHOD 审中-公开
公开(公告)号：US20190093893A1
公开(公告)日：2019-03-28
申请号：US16141342
申请日：2018-09-25
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Carsten CLEMEN , Ruud EGGELS
IPC分类号： F23R3/28 , F23R3/10
摘要： A combustion chamber assembly group includes a burner seal with a bearing section that extends along a longitudinal axis and has a passage hole for positioning a fuel nozzle at a combustion chamber of an engine, and a heat shield which, when mounted according to the intended use at the combustion chamber of the engine, is located inside the combustion space of the combustion chamber and has a passage hole through which the bearing section of the burner seal extends. The burner seal that is manufactured in an additive manner and the heat shield form a constructional unit in which the heat shield is received at least partially between a radially outwardly pointing opening edge of the burner seal and a radially outwardly extending web of the burner seal, so that any separation of the heat shield from the burner seal along the longitudinal axis is excluded.

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