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1. 发明授权

US08893856B2 Gravity scavenged generator with integral engine oil tank 有权
标题翻译：重力清理发电机与整体发动机油箱
公开(公告)号：US08893856B2
公开(公告)日：2014-11-25
申请号：US12179357
申请日：2008-07-24
申请人： Cristopher Frost
发明人： Cristopher Frost
IPC分类号： F01D25/18 , F02C7/06 , F02G3/00 , F02C7/32 , B64D41/00
CPC分类号： F01D25/18 , B64D2041/002 , F02C7/32 , F05D2260/602 , Y02T50/671
摘要： A generator having an integral oil tank for an auxiliary power unit (APU) is provided. A gas turbine engine has a turbine shaft extending from an aft portion to a forward portion where it is in communication with a gear box mounted thereto. The gearbox advantageously has at least one oil gravity drain passage in flow communication with a lower portion thereof and is suitable for reducing the speed of the turbine shaft by gear reduction to power an oil cooled generator attached thereto. The oil cooled generator has at least one oil gravity drain passage therein. An engine oil tank is integral with and advantageously removable from the generator and is in flow communication with each oil gravity drain passage making is suitable for gravity scavenging oil from the generator and advantageously the gearbox.
摘要翻译：提供具有用于辅助动力单元（APU）的整体油箱的发电机。燃气涡轮发动机具有从后部延伸到其与其安装的齿轮箱连通的前部的涡轮轴。齿轮箱有利地具有与其下部流动连通的至少一个油重力排水通道，并且适于通过齿轮减速来降低涡轮机轴的速度，为附着在其上的油冷却发电机供电。油冷发电机在其中具有至少一个油重力排水通道。发动机油箱与发生器成一体并且有利地从发生器移除，并且与每个重油排放通道的流动连通，适用于来自发电机的重力清除油，并且有利地是齿轮箱。

2. 发明申请

US20050056019A1 Integral compressor housing of gas turbine engines 失效
标题翻译：燃气轮机发动机的整体式压缩机外壳
公开(公告)号：US20050056019A1
公开(公告)日：2005-03-17
申请号：US10666611
申请日：2003-09-17
申请人： Ly Nguyen , Cristopher Frost , Ronald Maty , John Wait , Jason Smoke , Lori Wheeler , Richard Kocher
发明人： Ly Nguyen , Cristopher Frost , Ronald Maty , John Wait , Jason Smoke , Lori Wheeler , Richard Kocher
IPC分类号： F02C6/08 , F02C7/00 , F02C7/04 , F02C7/26
CPC分类号： F02C7/20 , F02C7/06 , F04D29/4206 , F05D2230/52 , Y02T50/672
摘要： A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.
摘要翻译：利用多部件集成的涡轮发动机压缩机设计，从而减少所需发动机部件的数量。在传统的压缩机设计中，多分量系统使得在瞬态条件下难以预测由于热和机械负载引起的结构行为。本发明的压缩机设计具有三个主要部分：前进轴承壳体，喇叭口（隔热罩）和耦合叶轮罩/扩散器。这样的设计实现了本发明的设计目标，包括减轻重量，降低成本，最小化公差建立，并通过利用多种发动机运行模式的多部件集成来改善空气动力性能。

3. 发明授权

US6101806A Tri-mode combustion system 有权
标题翻译：三模燃烧系统
公开(公告)号：US6101806A
公开(公告)日：2000-08-15
申请号：US143588
申请日：1998-08-31
申请人： Daih-Yeou Chen , Cristopher Frost , Hans Heydrich , Ronald B. Pardington
发明人： Daih-Yeou Chen , Cristopher Frost , Hans Heydrich , Ronald B. Pardington
IPC分类号： F02C3/13 , F02C6/16 , F02C7/268
CPC分类号： F02C6/16 , F02C3/13 , F05D2220/50 , Y02E60/15
摘要： A turbine engine is disclosed that is capable of operating in an emergency power mode, an air breathing auxiliary power mode and a bypass bleed environmental control mode. In a preferred embodiment of the invention, the engine comprises in working fluid flow order a compressor for compressing air, a combustion chamber and a power turbine for extracting mechanical work from heated and/or compressed air. The compressor and turbine are separately coupled by a shaft which is also coupled to a generator for supplying electrical power and a cooling turbine for supplying cooled air to the aircraft cabin and avionics. The combustion chamber has an upstream combustor inlet and a downstream combustor inlet, each of which may admit compressed air either to be mixed with fuel for combustion, or to pass directly to the combustor outlet which is operatively attached to the power turbine section inlet. During emergency/starting operation, the combustion chamber and turbine section receive compressed air from a stored air accumulator through a stored air inlet. During normal air breathing operation, the combustion chamber and turbine section receive compressed air from a compressor through an air breathing inlet. During bypass bleed operation, the combustion chamber and turbine section receive compressed air from the aircraft main engine through a bypass bleed air inlet. The tri-mode operation is made possible by a unique two-way bypass ring having a plurality of axial passages communicating the stored air inlet and air breathing inlet with the upstream combustor inlet and a plurality of radial passages communicating the bypass bleed inlet with the downstream combustor inlet. A valving system selectively admits compressed air into the combustor and turbine section from the stored air inlet, air breathing inlet or bypass bleed inlet depending on the mode of operation.
摘要翻译：公开了一种涡轮发动机，其能够在紧急动力模式，空气呼吸辅助动力模式和旁路出血环境控制模式下操作。在本发明的优选实施例中，发动机包括工作流体流动的压缩空气压缩机，燃烧室和动力涡轮机，用于从加热和/或压缩空气中提取机械作业。压缩机和涡轮机分别由轴连接，轴也耦合到用于提供电力的发电机和用于向飞机机舱和航空电子设备供应冷却空气的冷却涡轮机。燃烧室具有上游燃烧器入口和下游燃烧器入口，每个入口可以允许压缩空气与燃料混合以便燃烧，或者直接通到可操作地连接到动力涡轮机部分入口的燃烧室出口。在紧急/启动操作期间，燃烧室和涡轮部分通过储存的空气入口从储存的空气储存器接收压缩空气。在正常的呼吸呼吸操作期间，燃烧室和涡轮部分通过空气吸入口从压缩机接收压缩空气。在旁路泄放操作期间，燃烧室和涡轮部分通过旁路放气入口接收来自飞机主机的压缩空气。通过具有多个轴向通道的独特的双向旁路环来实现三模式操作，所述多个轴向通道将存储的空气入口和空气呼吸入口与上游燃烧器入口连通，以及多个径向通道将旁路出气口与下游燃烧器入口。阀门系统根据操作模式，从储存的空气入口，空气呼吸入口或旁路渗流入口选择性地将压缩空气进入燃烧器和涡轮机部分。

4. 发明申请

US20100019505A1 GRAVITY SCAVENGED GENERATOR WITH INTEGRAL ENGINE OIL TANK 有权
标题翻译：具有整体发动机油罐的重力发电机
公开(公告)号：US20100019505A1
公开(公告)日：2010-01-28
申请号：US12179357
申请日：2008-07-24
申请人： Cristopher Frost
发明人： Cristopher Frost
IPC分类号： F02B63/04
CPC分类号： F01D25/18 , B64D2041/002 , F02C7/32 , F05D2260/602 , Y02T50/671
摘要： A generator having an integral oil tank for an auxiliary power unit (APU) is provided. A gas turbine engine has a turbine shaft extending from an aft portion to a forward portion where it is in communication with a gear box mounted thereto. The gearbox advantageously has at least one oil gravity drain passage in flow communication with a lower portion thereof and is suitable for reducing the speed of the turbine shaft by gear reduction to power an oil cooled generator attached thereto. The oil cooled generator has at least one oil gravity drain passage therein. An engine oil tank is integral with and advantageously removable from the generator and is in flow communication with each oil gravity drain passage making is suitable for gravity scavenging oil from the generator and advantageously the gearbox.
摘要翻译：提供具有用于辅助动力单元（APU）的整体油箱的发电机。燃气涡轮发动机具有从后部延伸到其与其安装的齿轮箱连通的前部的涡轮轴。齿轮箱有利地具有与其下部流动连通的至少一个油重力排水通道，并且适于通过齿轮减速来降低涡轮机轴的速度，为附着在其上的油冷却发电机供电。油冷发电机在其中具有至少一个油重力排水通道。发动机油箱与发生器成一体并且有利地从发生器移除，并且与每个重油排放通道的流动连通，适用于来自发电机的重力清除油，并且有利地是齿轮箱。

5. 发明授权

US07356926B2 Removal tool and method of removing a bearing assembly 失效
标题翻译：拆卸工具和拆卸轴承组件的方法
公开(公告)号：US07356926B2
公开(公告)日：2008-04-15
申请号：US10742206
申请日：2003-12-18
申请人： Eric B. Bridges , Cristopher Frost
发明人： Eric B. Bridges , Cristopher Frost
IPC分类号： B23P19/00
CPC分类号： B25B27/062 , F16C19/06 , F16C33/586 , F16C33/60 , F16C35/062 , F16C2237/00 , F16C2300/02 , Y10T29/49696 , Y10T29/49698 , Y10T29/49815 , Y10T29/49822 , Y10T29/53848 , Y10T29/53857 , Y10T29/53861 , Y10T29/53865 , Y10T29/5387 , Y10T29/53874
摘要： A compact removal feature comprises a plurality of recesses, such as radius slots, on an inner diameter (ID) of a bearing inner ring. The removal tool can engage the removal feature and remove the entire bearing assembly without damage to the parts. The placement of the removal feature on the bearing inner ring ID allows for a reduction in inner ring length (and weight) while maintaining bearing assembly integrity.
摘要翻译：紧凑的移除特征包括在轴承内圈的内径（ID）上的多个凹槽，例如半径槽。移除工具可以接合移除特征并移除整个轴承组件而不损坏部件。移除部件在轴承内圈ID上的放置允许在保持轴承组件完整性的同时减小内圈长度（和重量）。

6. 发明授权

US06968697B2 Integral compressor housing of gas turbine engines 失效
公开(公告)号：US06968697B2
公开(公告)日：2005-11-29
申请号：US10666611
申请日：2003-09-17
申请人： Ly D. Nguyen , Cristopher Frost , Ronald P. Maty , John M. Wait , Jason C. Smoke , Lori M. Wheeler , Richard D. Kocher
发明人： Ly D. Nguyen , Cristopher Frost , Ronald P. Maty , John M. Wait , Jason C. Smoke , Lori M. Wheeler , Richard D. Kocher
IPC分类号： F02C6/08 , F02C7/00 , F02C7/04 , F02C7/26
CPC分类号： F02C7/20 , F02C7/06 , F04D29/4206 , F05D2230/52 , Y02T50/672
摘要： A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.

7. 发明申请

US20050097896A1 Dual mode power unit having a combustor bypass system 失效
标题翻译：具有燃烧器旁路系统的双模式动力单元
公开(公告)号：US20050097896A1
公开(公告)日：2005-05-12
申请号：US10705580
申请日：2003-11-10
申请人： Ian Critchley , Barry Kingery , Cristopher Frost , David Walhood , Robert Sumegi
发明人： Ian Critchley , Barry Kingery , Cristopher Frost , David Walhood , Robert Sumegi
IPC分类号： F02C6/00 , F02C7/268
CPC分类号： F02C6/00 , F05D2220/50 , Y02T50/671
摘要： A gas turbine engine integrates the functions of an auxiliary power unit (APU) with one or more functions of an ECS, and that is capable of operating in both an unfired mode and a fired mode. The gas turbine engine includes a combustor system that is configured to allow the gas turbine to quickly transition from the unfired mode to the fired mode, by bypassing a portion of the air flowing to the combustor system around the combustor.
摘要翻译：燃气涡轮发动机将辅助动力单元（APU）的功能与ECS的一个或多个功能集成，并且能够在未燃烧模式和燃烧模式下操作。燃气涡轮发动机包括燃烧器系统，其被构造成允许燃气涡轮机通过绕流动到燃烧器系统周围的燃烧器的一部分空气而从未燃烧模式快速转变到燃烧模式。

8. 发明申请

US20070022731A1 Compact, light weight eductor oil cooler plenum and surge flow plenum design 有权
标题翻译：紧凑，重量轻的喷射器油冷却器集气室和浪涌气流通风设计
公开(公告)号：US20070022731A1
公开(公告)日：2007-02-01
申请号：US11303180
申请日：2005-12-15
申请人： Yogendra Sheoran , Cristopher Frost
发明人： Yogendra Sheoran , Cristopher Frost
IPC分类号： F02C7/00
CPC分类号： F02C7/32 , B64D41/00 , B64D2033/0213 , B64D2041/002 , F01D25/18 , Y02T50/671
摘要： An eductor assembly is provided that includes a primary nozzle, a cooler plenum, and a surge plenum. In one embodiment, and by way of example only, the primary nozzle is configured to accelerate and discharge turbine exhaust gas therefrom and the cooler plenum surrounds the primary nozzle and includes at least a fluid inlet and a fluid outlet. The surge plenum partially surrounds the primary nozzle and the cooler plenum and includes at least a fluid inlet and a fluid outlet. The surge plenum fluid outlet axially aligns and is coterminous with the cooler plenum fluid outlet.
摘要翻译：提供了一种喷射器组件，其包括主喷嘴，较冷气室和浪涌气室。在一个实施例中，仅作为示例，主喷嘴构造成从其中加速和排放涡轮废气，并且冷却器压力室围绕主喷嘴并且至少包括流体入口和流体出口。浪涌气室部分地围绕主喷嘴和冷却器气室，并且至少包括流体入口和流体出口。浪涌增压室流体出口轴向对准并与冷却器增压室流体出口相连。

9. 发明授权

US07097411B2 Turbomachine compressor scroll with load-carrying inlet vanes 失效
标题翻译：涡轮机压缩机蜗轮带有承载入口叶片
公开(公告)号：US07097411B2
公开(公告)日：2006-08-29
申请号：US10829114
申请日：2004-04-20
申请人： Jason C. Smoke , Cristopher Frost , Richard D. Kocher , Jeff D. Guymon , Ly D. Nguyen
发明人： Jason C. Smoke , Cristopher Frost , Richard D. Kocher , Jeff D. Guymon , Ly D. Nguyen
IPC分类号： F01D1/02 , F04D29/44
CPC分类号： F04D29/444 , F01D9/026 , F04D29/624 , F05D2220/40 , F05D2250/52
摘要： A compressor scroll housing for use in conjunction with turbo-machinery, particularly applicable in aircraft. The scroll housing can include a plurality of scroll vanes arrayed around the scroll housing. Scroll vanes, integrally formed with the scroll housing, carry stress load on the scroll housing, including the load from fluid pressure within the scroll and carcass loading from the engine. The plurality of scroll vanes adapted for guiding flow of fluid from an inlet to an outlet while supporting the scroll housing. Chord length and cross sectional area of each scroll vane can be sized to maintain an equal stress in all scroll vanes. A method of making the scroll housing for use with an impeller connected to an engine is disclosed, as well as a method of operating turbo-machinery including supporting a load on the scroll housing with scroll vanes while maintaining an equal stress on each scroll vane.
摘要翻译：一种与涡轮机械结合使用的压缩机涡旋壳体，特别适用于飞机。涡旋壳体可以包括围绕涡旋壳体排列的多个涡旋叶片。与涡旋壳体一体形成的涡旋叶片在涡旋壳体上承受应力负荷，包括来自涡卷内的流体压力的负载和来自发动机的胎体负载。多个涡旋叶片适于在支撑涡旋壳体的同时引导流体从入口到出口的流动。每个涡旋叶片的弦长和横截面面积的尺寸可以确保在所有涡旋叶片中保持相等的应力。公开了一种制造与连接到发动机的叶轮一起使用的涡旋壳体的方法，以及一种操作涡轮机械的方法，包括在涡轮叶片上支撑负载，同时在每个涡旋叶片上保持相等的应力。

10. 发明授权

US07007475B2 Conical helical of spiral combustor scroll device in gas turbine engine 有权
标题翻译：燃气涡轮发动机中螺旋燃烧器涡旋装置的锥形螺旋
公开(公告)号：US07007475B2
公开(公告)日：2006-03-07
申请号：US10386771
申请日：2003-03-11
申请人： Ly D. Nguyen , Hakan Aksoy , Stony Kujala , Cristopher Frost
发明人： Ly D. Nguyen , Hakan Aksoy , Stony Kujala , Cristopher Frost
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/52 , F23R3/425
摘要： A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.
摘要翻译：用于涡轮机燃烧器涡旋盘的锥形螺旋设计通过在涡旋中增加轴向移动和不规则横截面形状而尽可能多地利用燃烧器壳体的空腔，而不会不利地影响空气动力性能。燃烧器涡旋件的轴向移动区域将涡旋件的横截面积重心延伸超过涡旋件的排放区域B-宽度。所得到的涡卷设计允许使用具有较大燃烧器的高性能发动机，同时通过使燃烧器壳体尽可能小地减小系统的重量。此外，涡旋设计通过减小涡旋件和壳体之间的间隙来增加用于对流冷却的空气速度。本发明的涡轮涡旋盘可用于需要高性能的发动机，例如某些高性能飞机。

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