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1. 发明授权

EP2336026B1 Integrated Nacelle Assembly 有权
公开(公告)号：EP2336026B1
公开(公告)日：2019-08-14
申请号：EP10195753.8
申请日：2010-12-17
申请人： General Electric Company
发明人： Lachapelle, Donald George , Glynn, Christopher Charles , Gardner, Donald Lee , Mitchell, Stephen Craig , Srinivas, Mullahalli Venkataramaniah , Rainous, Edward Atwood , Pennekamp, David Lance
IPC分类号： B64D27/26 , B64D27/18

2. 发明授权

EP0541325B1 Gas turbine engine case thermal control 失效
标题翻译：燃气涡轮发动机的壳体的热控制
公开(公告)号：EP0541325B1
公开(公告)日：1997-05-07
申请号：EP92310045.7
申请日：1992-11-03
申请人： GENERAL ELECTRIC COMPANY
发明人： Plemmons, Larry Wayne , Albers, Robert Joseph , Proctor, Robert , Gardner, Donald Lee
IPC分类号： F01D11/08
CPC分类号： F01D11/24

3. 发明公开

EP2574845A2 Combustion system and method of assembling the same 审中-公开
标题翻译： Verbrennungssystem und Montageverfahrendafür
公开(公告)号：EP2574845A2
公开(公告)日：2013-04-03
申请号：EP12186089.4
申请日：2012-09-26
申请人： General Electric Company
发明人： Patterson, David Bruce , Corsmeier, Donald Michael , Young, Craig Douglas , Gardner, Donald Lee , Thompson, James Edward , Brown, Daniel Dale , Wiehe, Glenn Edward
IPC分类号： F23R3/00 , F23R3/50 , F23R3/60
CPC分类号： F23R3/50 , F23R3/002 , F23R3/60 , Y02E20/16 , Y10T29/49229 , Y10T29/4932
摘要： A combustion system (106) for a gas turbine engine (100) is provided. The combustion system includes an inner casing structure (124), an outer casing structure (122), and a combustion chamber frame (200) mounted between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
摘要翻译：提供了一种用于燃气涡轮发动机（100）的燃烧系统（106）。燃烧系统包括内壳结构（124），外壳结构（122）和安装在内壳结构和外壳结构之间的燃烧室框架（200），使得燃烧室框架联接到内壳结构套管结构和外壳结构。

4. 发明公开

EP2025878A3 Aircraft gas turbine engine blade tip clearance control 审中-公开
标题翻译：用于飞机燃气涡轮发动机叶片尖端间隙控制
公开(公告)号：EP2025878A3
公开(公告)日：2013-05-29
申请号：EP08161497.6
申请日：2008-07-30
申请人： GENERAL ELECTRIC COMPANY
发明人： Hershey, John Erik , Osborn, Brock Estel , Gardner, Donald Lee , Ruiz, Rafael Jose , Herron, William Lee
IPC分类号： F01D11/02 , F01D11/20 , F01D11/24 , F02C9/48
CPC分类号： F01D11/24 , F02C9/00 , F02C9/26 , F02C9/48 , F05D2270/305 , F05D2270/44 , F05D2270/70
摘要： A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

5. 发明公开

EP2336026A2 Integrated Nacelle Assembly 有权
标题翻译： Integrierte Gondelbaugruppe
公开(公告)号：EP2336026A2
公开(公告)日：2011-06-22
申请号：EP10195753.8
申请日：2010-12-17
申请人： General Electric Company
发明人： Lachapelle, Donald George , Glynn, Christopher Charles , Gardner, Donald Lee , Mitchell, Stephen Craig , Srinivas, Mullahalli Venkataramaniah , Rainous, Edward Atwood , Pennekamp, David Lance
IPC分类号： B64D27/26 , B64D27/18
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
摘要： An assembly includes a unitary nacelle structure (11) and an integrated fan housing (30) for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl (50) region, and is configured to at least partially circumscribe the integrated fan housing (30). The integrated fan housing (30) comprises an integral composite structure and includes a fan case (32) sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes (38). The unitary nacelle structure (11) cooperates with the integrated fan housing (30) to transfer static and dynamic loads directly to a support structure (22), rather than through the engine core, to minimize backbone bending.
摘要翻译：组件包括用于燃气涡轮发动机组件的整体式机舱结构（11）和一体式风扇壳体（30）。整体式机舱结构包括入口区域和风扇整流罩（50）区域，并且构造成至少部分地围绕集成风扇壳体（30）。集成风扇壳体（30）包括整体复合结构，并且包括风扇壳体（32），其尺寸和构造用于环绕相关联的燃气涡轮发动机的风扇叶片组件，风扇轮毂和多个风扇出口导叶（38 ）。整体式机舱结构（11）与集成风扇壳体（30）配合，以将静态和动态负载直接传递到支撑结构（22），而不是通过发动机芯，以最小化主干弯曲。

6. 发明公开

EP2336026A3 Integrated Nacelle Assembly 有权
标题翻译：集成的机舱组件
公开(公告)号：EP2336026A3
公开(公告)日：2017-05-24
申请号：EP10195753.8
申请日：2010-12-17
申请人： General Electric Company
发明人： Lachapelle, Donald George , Glynn, Christopher Charles , Gardner, Donald Lee , Mitchell, Stephen Craig , Srinivas, Mullahalli Venkataramaniah , Rainous, Edward Atwood , Pennekamp, David Lance
IPC分类号： B64D27/26 , B64D27/18
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
摘要： An assembly includes a unitary nacelle structure (11) and an integrated fan housing (30) for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl (50) region, and is configured to at least partially circumscribe the integrated fan housing (30). The integrated fan housing (30) comprises an integral composite structure and includes a fan case (32) sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes (38). The unitary nacelle structure (11) cooperates with the integrated fan housing (30) to transfer static and dynamic loads directly to a support structure (22), rather than through the engine core, to minimize backbone bending.
摘要翻译：一种组件包括用于燃气涡轮发动机组件的整体式机舱结构（11）和整体式风扇壳体（30）。整体式机舱结构包括入口区域和风扇罩（50）区域，并且构造成至少部分地包围整体式风扇壳体（30）。集成风扇壳体（30）包括整体复合结构并且包括风扇壳体（32），该风扇壳体的尺寸和构造被设计成用于环绕相关联的燃气涡轮发动机的风扇叶片组件，风扇轮毂和多个风扇出口导叶（38 ）。整体式机舱结构（11）与集成式风扇壳体（30）协作以将静态和动态负载直接传递到支撑结构（22），而不是通过发动机芯，以使主干弯曲最小化。

7. 发明公开

EP2574845A3 Combustion system and method of assembling the same 审中-公开
标题翻译：燃烧系统及其组装方法
公开(公告)号：EP2574845A3
公开(公告)日：2013-12-04
申请号：EP12186089.4
申请日：2012-09-26
申请人： General Electric Company
发明人： Patterson, David Bruce , Corsmeier, Donald Michael , Young, Craig Douglas , Gardner, Donald Lee , Thompson, James Edward , Brown, Daniel Dale , Wiehe, Glenn Edward
IPC分类号： F23R3/00 , F23R3/50 , F23R3/60
CPC分类号： F23R3/50 , F23R3/002 , F23R3/60 , Y02E20/16 , Y10T29/49229 , Y10T29/4932
摘要： A combustion system (106) for a gas turbine engine (100) is provided. The combustion system includes an inner casing structure (124), an outer casing structure (122), and a combustion chamber frame (200) mounted between the inner casing structure and the outer casing structure such that the combustion chamber frame is coupled to the inner casing structure and the outer casing structure.
摘要翻译：提供了用于燃气涡轮发动机（100）的燃烧系统（106）。燃烧系统包括内壳结构（124），外壳结构（122）和安装在内壳结构和外壳结构之间的燃烧室框架（200），使得燃烧室框架联接到内壳外壳结构和外壳结构。

8. 发明公开

EP2025878A2 Aircraft gas turbine engine blade tip clearance control 审中-公开
标题翻译： Schaufelspitzen-Abstandssteuerungfüreinen Flugzeuggasturbenenotors
公开(公告)号：EP2025878A2
公开(公告)日：2009-02-18
申请号：EP08161497.6
申请日：2008-07-30
申请人： GENERAL ELECTRIC COMPANY
发明人： Hershey, John Erik , Osborn, Brock Estel , Gardner, Donald Lee , Ruiz, Rafael Jose , Herron, William Lee
IPC分类号： F01D11/02 , F01D11/20
CPC分类号： F01D11/24 , F02C9/00 , F02C9/26 , F02C9/48 , F05D2270/305 , F05D2270/44 , F05D2270/70
摘要： A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.
摘要翻译：一种方法和系统预计在改变发动机转速的发动机命令之前和之前调整旋转的飞机燃气涡轮发动机叶片尖端和周围的护罩之间的叶片顶端间隙。该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调节顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞行器机组数据。飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。确定什么时候开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或在其他飞行器上的其它喷气发动机的操作经验和/或操作经验。

9. 发明公开

EP0541325A1 Gas turbine engine case thermal control 失效
标题翻译： Thermische Steuerung einesGehäuseseines Gasturbinentriebwerks。
公开(公告)号：EP0541325A1
公开(公告)日：1993-05-12
申请号：EP92310045.7
申请日：1992-11-03
申请人： GENERAL ELECTRIC COMPANY
发明人： Plemmons, Larry Wayne , Albers, Robert Joseph , Proctor, Robert , Gardner, Donald Lee
IPC分类号： F01D11/08
CPC分类号： F01D11/24
摘要： A thermal control apparatus is provided for gas turbine engine cases and particularly for thermal control of clearances between turbine rotors and surrounding shrouds. Thermal control of an annular case section or ring is provided by counterflowing two heat transfer fluid flowpaths in heat transfer communication with the section of engine casing. The flowpaths may be in parallel or series such that there is substantially no circumferential gradient in the mass flowrate weighted average temperature of the heat transfer fluid supplied by the two counterflowing fluid flowpaths. One embodiment provides forward and aft rings cooled by three spray tubes in each of two 180° sectors whereby the forward and aft spray tubes flow thermal control air flowing in one circumferential direction and the middle spray tubes flows thermal control air in an opposite circumferential direction.
摘要翻译：为燃气涡轮发动机壳体提供热控制装置，特别是用于对涡轮转子和周围罩之间的间隙的热控制。通过与发动机壳体的部分传热连通的两个传热流体流路逆流来提供环形壳体部分或环的热控制。流路可以是平行的或串联的，使得在由两个逆流流体流动路径供应的传热流体的质量流量加权平均温度中基本上没有周向梯度。一个实施例提供由两个180度扇区中的每一个中的三个喷射管冷却的前后环，其中前喷射管和后喷射管流动在一个圆周方向上流动的热控制空气，并且中间喷管在相反的圆周方向上流动热控制空气。

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