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公开(公告)号：US20080092514A1
公开(公告)日：2008-04-24
申请号：US11720463
申请日：2004-12-01
Applicant: Gabriel Suciu , James Norris , Brian Merry
Inventor： Gabriel Suciu , James Norris , Brian Merry
IPC: F02K1/04
CPC classification number: F02C3/073 , F02K1/04 , F02K3/068 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y10T29/49346
Abstract: A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
Abstract translation: 尖端涡轮发动机中的非金属尾管（202）包括围绕中心轴线设置（208）的锥形壁结构。 非金属尾管紧固在顶端涡轮发动机的后部的结构框架（44）上。 尖端涡轮发动机产生来自第一输出源的第一温度气体流和来自第二输出源的第二温度气体流。 第二温度气体流是比第一温度气体流更低的温度。 第二温度气流在末端涡轮发动机的内径处在尾骨的外表面上排出。 在内径处排出较冷的第二温度气流允许非金属物质用于形成尾骨。
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公开(公告)号：US20080008583A1
公开(公告)日：2008-01-10
申请号：US11720543
申请日：2004-12-01
Applicant: Gabriel Suciu , James Norris , Brian Merry
Inventor： Gabriel Suciu , James Norris , Brian Merry
Abstract: A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inwardly from the rear case. The exhaust mixer extends in a flow path of a combustor to mix a high energy gas stream from the combustor with bypass air from a bypass fan. The engine mounts are located on the periphery of the rear case for mounting the engine to an aircraft. The rear case, exit guide vanes, exhaust mixer, and engine mounts form a unitary engine support structure which is installable as a single piece into an engine.
Abstract translation: 尖端涡轮发动机组件包括具有后壳体，出口导向叶片，排气混合器和发动机支架的发动机支撑结构。 后壳围绕发动机中心线设置。 出口导向叶片从后壳径向向内延伸。 排气混合器在燃烧器的流路中延伸，以将来自燃烧器的高能气流与旁路风扇的旁路空气混合。 发动机支架位于后壳的外围，用于将发动机安装到飞机上。 后壳体，出口导向叶片，排气混合器和发动机支架形成一体的发动机支撑结构，其可作为单件安装到发动机中。
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公开(公告)号：US20070065287A1
公开(公告)日：2007-03-22
申请号：US11408453
申请日：2006-04-21
Applicant: Gabriel Suciu , James Norris
Inventor： Gabriel Suciu , James Norris
IPC: B64C11/00
CPC classification number: F01D11/001 , F01D5/06 , Y10T29/4932 , Y10T29/49716
Abstract: A gas turbine engine rotor stack may be engineered or reengineered to include one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.
Abstract translation: 燃气涡轮发动机转子堆可以被设计或重新设计成包括一个或多个纵向向外凹的间隔件。 间隔件可以提供随着转速而增加的纵向压缩力。
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公开(公告)号：US20060248900A1
公开(公告)日：2006-11-09
申请号：US11122336
申请日：2005-05-05
Applicant: Gabriel Suciu , Brian Merry
Inventor： Gabriel Suciu , Brian Merry
IPC: F02C6/00
CPC classification number: F02C7/36 , F02C7/32 , Y02T50/671 , Y10S74/05
Abstract: Provided is an accessory gearbox for a gas turbine engine that contributes minimally to engine weight and complexity. An accessory gearbox comprises a stationary frame that is circumferentially disposed about a central longitudinal axis of the engine. The frame includes a forward-directed axial face and a rearward-directed axial face for fastening the frame to the engine. A central bore accepts a rotational driving means and an outermost rim circumscribes the outer diameter of the frame. A compartment is located between the bore and the rim. At least one primary accessory is mounted to a face and proximate the compartment, remotely engaging the driving means and able to be driven concurrently therewith.
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公开(公告)号：US20050232773A1
公开(公告)日：2005-10-20
申请号：US10825255
申请日：2004-04-15
Applicant: Gabriel Suciu , James Norris
Inventor： Gabriel Suciu , James Norris
CPC classification number: F01D11/001 , F01D5/06 , Y10T29/4932 , Y10T29/49716
Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.
Abstract translation: 燃气涡轮发动机转子堆叠包括一个或多个纵向向外凹的间隔件。 间隔件可以提供随着转速而增加的纵向压缩力。
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Patent Agency Ranking
公开(公告)号：US20080093174A1
公开(公告)日：2008-04-24
申请号：US11718429
申请日：2004-12-01
Applicant: Gabriel Suciu , Brian Merry
Inventor： Gabriel Suciu , Brian Merry
CPC classification number: F01D25/20 , F01D15/12 , F01D25/12 , F02C3/073 , F02C7/32 , F02K3/068 , Y02T50/675
Abstract: A liquid-air heat exchanger extracts thermal energy from an engine lubricating fluid system. The liquid-air heat exchanger is located within a tailcone section and is in communication with a portion of the fan bypass airflow which enters the tailcone section through an annular tailcone exhaust nozzle entrance to transfer thermal energy into the combined airflow out of the engine to recover thrust loss ducted from the fan bypass stream.
Abstract translation: 液体 - 空气热交换器从发动机润滑流体系统中提取热能。 液体 - 空气热交换器位于尾部部分内，并且与通过环形尾气排气喷嘴入口进入尾部部分的风扇旁路气流的一部分连通，以将热能传递到从发动机外部的组合气流中以回收 从风扇旁路流引导的推力损失。
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公开(公告)号：US20080014078A1
公开(公告)日：2008-01-17
申请号：US11720083
申请日：2004-12-01
Applicant: Gabriel Suciu , Gary Roberge
Inventor： Gabriel Suciu , Gary Roberge
IPC: F01D25/14
CPC classification number: F02C3/045 , F01D5/022 , F01D25/12 , F01D25/14 , F02C3/073 , F02C7/18 , F02K3/068 , Y02T50/675
Abstract: A tip turbine engine (10) includes a combustor (30) radially outward of a fan. In order to reduce the heat transfer from the combustor and the high-energy gas stream generated by the combustor, a cold air ejector (38) radially outward of the combustor extends from a forward end of the nacelle (12) to a point rearward of the combustor and an exhaust mixer (110). The cold air ejector includes an annular inlet (17) at the forward end of the nacelle. The cold air ejector draws air over the outer engine case (39) to provide a boundary between the nacelle and the hot outer engine case. The layer of air being pulled past the engine case ejects the heat, thereby preventing the heat from escaping into the nacelle or engine bay.
Abstract translation: 顶端涡轮发动机（10）包括在风扇的径向外侧的燃烧器（30）。 为了减少来自燃烧器的热传递和由燃烧器产生的高能气流，从燃烧器径向向外的冷空气喷射器（38）从机舱（12）的前端延伸到 燃烧器和排气混合器（110）。 冷空气喷射器包括在机舱前端的环形入口（17）。 冷空气喷射器将空气吸引到外部发动机壳体（39）上，以提供机舱和热外部发动机壳体之间的边界。 被拉动通过发动机舱的空气层排出热量，从而防止热量逸出到机舱或发动机舱中。
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公开(公告)号：US20070107219A1
公开(公告)日：2007-05-17
申请号：US11479334
申请日：2006-06-30
Applicant: Gabriel Suciu , James Norris
Inventor： Gabriel Suciu , James Norris
IPC: B23P11/00
CPC classification number: F01D5/066 , F01D5/025 , F01D11/001 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49947
Abstract: A rotor stack is assembled to a turbine engine shaft. A force is exerted to at least one of the rotor stack and the shaft to at least one of place the shaft under tension and place the rotor stack under compression. One or more retainer segments are inserted into a rebate in the shaft. The exerted force is released to permit the rotor stack to bear against the retainer segments.
Abstract translation: 转子堆叠组装到涡轮发动机轴上。 对转子堆和轴中的至少一个施加力至至少一个将轴处于张紧状态，并将转子叠层置于压缩状态。 一个或多个保持器段被插入轴中的槽口中。 施加的力被释放以允许转子堆叠抵靠保持器段。
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公开(公告)号：US20060099070A1
公开(公告)日：2006-05-11
申请号：US10985863
申请日：2004-11-10
Applicant: Gabriel Suciu , James Norris
Inventor： Gabriel Suciu , James Norris
IPC: F01D1/02
CPC classification number: F01D11/001 , F01D5/066 , F05D2250/70 , F05D2250/712 , F05D2260/30
Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The spacers may provide a longitudinal compression force that increases with rotational speed.
Abstract translation: 燃气涡轮发动机转子堆叠包括一个或多个纵向向外凹的间隔件。 间隔件的外侧表面可以靠近翼片翼型的内侧尖端。 间隔件可以提供随着转速而增加的纵向压缩力。
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公开(公告)号：US20050232774A1
公开(公告)日：2005-10-20
申请号：US10825256
申请日：2004-04-15
Applicant: Gabriel Suciu , James Norris
Inventor： Gabriel Suciu , James Norris
CPC classification number: F01D5/066 , F01D5/025 , F01D11/001 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49947
Abstract: A gas turbine engine has a rotor stack carried by a central shaft. A number of retainer segments each have a first surface engaging the rotor stack and a second surface engaging the central shaft so as to transmit a precompression force from the central shaft to the rotor stack.
Abstract translation: 燃气涡轮发动机具有由中心轴承载的转子堆。 多个保持器段各自具有接合转子堆叠的第一表面和接合中心轴的第二表面，以便将预压力从中心轴传递到转子堆叠。
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