-
公开(公告)号：US09835037B2
公开(公告)日：2017-12-05
申请号：US14746426
申请日：2015-06-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Goerig , Darek Tomasz Zatorski , Tsuguji Nakano , Patrick John Lonneman
IPC: F02C3/04 , F01D7/00 , F04D27/02 , F04D29/32 , F01D5/02 , F01D5/30 , F01D15/00 , F01D25/24 , F02K1/66 , F01D7/02
CPC classification number: F01D7/00 , F01D5/02 , F01D5/3007 , F01D7/02 , F01D15/00 , F01D25/24 , F02C3/04 , F02K1/66 , F04D27/0246 , F04D29/323 , F05D2220/32 , F05D2220/36 , F05D2240/20 , F05D2240/35 , Y02T50/671 , Y02T50/673
Abstract: An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.
-
公开(公告)号：US20250003375A1
公开(公告)日：2025-01-02
申请号：US18740613
申请日：2024-06-12
Applicant: General Electric Company
Inventor： Joseph George Rose , Thomas Ory Moniz , Tsuguji Nakano , Jeffrey S. Spruill , Brandon Wayne Miller , Randy M. Vondrell , David Marion Ostdiek , Craig William Higgins , Alexander Kimberley Simpson
Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct, a primary fan driven by the turbomachine, a secondary fan located downstream of the primary fan within the inlet duct, a heat exchanger disposed in the fan duct, and a booster upstream of the heat exchanger, the booster including a booster cowl extending into the fan duct, the booster cowl separating an upstream portion of the fan duct into an upper fan duct having an upper fan duct inlet and a lower fan duct having a lower fan duct inlet, the upper fan duct inlet and lower fan duct inlet collectively forming the fan duct inlet.
-
公开(公告)号：US11859515B2
公开(公告)日：2024-01-02
申请号：US17686843
申请日：2022-03-04
Applicant: General Electric Company
Inventor： Tsuguji Nakano , Darek Zatorski , Andrew Breeze-Stringfellow
CPC classification number: F01D9/041 , F01D5/145 , F01D9/02 , F01D9/04 , F01D25/28 , F05D2240/126 , F05D2240/129
Abstract: There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.
-
公开(公告)号：US20230287837A1
公开(公告)日：2023-09-14
申请号：US17691222
申请日：2022-03-10
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Tsuguji Nakano , Stefan Joseph Cafaro
IPC: F02C9/26
CPC classification number: F02C9/26 , F05D2220/323 , F05D2270/051
Abstract: A gas turbine engine and a method of operating the gas turbine engine is provided. The gas turbine engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, a nacelle surrounding and at least partially enclosing the fan, the nacelle defining an inlet and a longitudinal axis, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle. The method includes determining, by one or more computing devices, a thrust demand for the gas turbine engine, and in response to the thrust demand, controlling, by the one or more computing devices, a rotational speed of the fan and an angle of the inlet pre-swirl feature with respect to the longitudinal axis of the nacelle.
-
公开(公告)号：US20190257318A1
公开(公告)日：2019-08-22
申请号：US15900891
申请日：2018-02-21
Applicant: General Electric Company
Inventor： Veeraraju Vanapalli , Bhaskar Nanda Mondal , Jagata Laxmi Narasimharao , Tsuguji Nakano , Subramanian Narayanan
Abstract: The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.
-
Patent Agency Ranking
公开(公告)号：US20180363678A1
公开(公告)日：2018-12-20
申请号：US15625212
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
CPC classification number: F04D29/563 , F01D9/041 , F02C3/04 , F02C7/04 , F02K3/06 , F04D29/542 , F04D29/545 , F04D29/684 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2250/182 , F05D2250/184 , F05D2260/14
Abstract: A gas turbine engine includes a turbomachine and a fan rotatable by the turbomachine. The fan includes a plurality of fan blades, each of the plurality of fan blades defining a fan blade span along a radial direction. The gas turbine engine further includes an outer nacelle surrounding the plurality of fan blades and a plurality of part-span inlet guide varies attached to the outer nacelle at a location forward of the plurality of fan blades along an axial direction. Each of the plurality of inlet guide vanes defines an IGV span along the radial direction, the IGV span being at least about five percent of the fan blade span and up to about fifty-five percent of the fan blade span.
-
公开(公告)号：US09777642B2
公开(公告)日：2017-10-03
申请号：US14919825
申请日：2015-10-22
Applicant: General Electric Company
Inventor： Kurt David Murrow , Andrew Breeze-Stringfellow , Randy M. Vondrell , Tsuguji Nakano , Jeffrey Anthony Hamel , Darek Tomasz Zatorski
IPC: F02C1/00 , F02C9/20 , F01D7/00 , F01D15/12 , F01D17/08 , F01D17/10 , F01D17/16 , F02K1/66 , F02K3/04 , F02K3/075 , F02C3/13 , F02C7/36 , F02C9/18 , F02C3/04 , F02C7/042
CPC classification number: F02C9/20 , F01D7/00 , F01D15/12 , F01D17/085 , F01D17/105 , F01D17/162 , F02C3/04 , F02C3/13 , F02C7/042 , F02C7/36 , F02C9/18 , F02K1/66 , F02K3/04 , F02K3/075 , F05D2220/36 , F05D2270/101 , F05D2270/303 , F05D2300/30 , Y02T50/672
Abstract: A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.
-
公开(公告)号：US20160369639A1
公开(公告)日：2016-12-22
申请号：US14746426
申请日：2015-06-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Trevor Goerig , Darek Tomasz Zatorski , Tsuguji Nakano , Patrick John Lonneman
CPC classification number: F01D7/00 , F01D5/02 , F01D5/3007 , F01D7/02 , F01D15/00 , F01D25/24 , F02C3/04 , F02K1/66 , F04D27/0246 , F04D29/323 , F05D2220/32 , F05D2220/36 , F05D2240/20 , F05D2240/35 , Y02T50/671 , Y02T50/673
Abstract: An actuation assembly for a variable pitch fan for a gas turbine engine is provided. The actuation assembly generally includes a plurality of fan blades, a scheduling ring, and a plurality of linkage arms. The plurality of fan blades are rotatably coupled to a disk and extend radially therefrom. The scheduling ring is rotatable relative to the disk and has a plurality of slots. Each of the plurality of linkage arms are operatively coupled to one of the plurality of fan blades and to one of the plurality of slots. Each of the plurality of fan blades rotate according to a blade pitch schedule defined by the slot to which it is operatively coupled, and at least two of the plurality of slots define different blade pitch schedules.
Abstract translation: 提供了一种用于燃气涡轮发动机的变桨距风扇的致动组件。 致动组件通常包括多个风扇叶片，调度环和多个连杆臂。 多个风扇叶片可旋转地联接到盘并从其径向延伸。 调度环可相对于盘旋转并具有多个槽。 多个联动臂中的每一个可操作地联接到多个风扇叶片中的一个和多个狭槽中的一个。 多个风扇叶片中的每一个根据由其可操作地联接的狭槽限定的叶片间距调度旋转，并且多个狭槽中的至少两个限定不同的叶片间距调度。
-
公开(公告)号：US12292017B1
公开(公告)日：2025-05-06
申请号：US18744069
申请日：2024-06-14
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Egbert Geertsema , Arthur W. Sibbach , Andrew Hudecki , Timothy Richard DePuy , John C. Schilling , Frank Worthoff , Tsuguji Nakano
Abstract: A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.
-
公开(公告)号：US12085024B2
公开(公告)日：2024-09-10
申请号：US18307201
申请日：2023-04-26
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Christopher James Kroger , Jeffrey Donald Clements , Sean Christopher Binion , Tsuguji Nakano
CPC classification number: F02C7/36 , F02K3/06 , F05D2220/36 , F05D2260/40311 , F05D2260/606
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of rotatable fan blades, each fan blade defining a fan tip speed; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; and a gear box, wherein the turbomachine is operably coupled to the fan through the gear box, wherein a gear ratio of the gear box is greater than or equal to 1.2 and less than or equal to 3.0; wherein during operation of the turbofan engine at a rated speed the fan tip speed is greater than or equal to 1000 feet per second. In exemplary embodiments, during operation of the turbofan engine at the rated speed the fan pressure ratio is less than or equal to about 1.5.
-
-
-
-
-
-
-
-
-
Search Results
37
records
(took 0.021 seconds)
