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1. 发明授权

US07174797B2 High temperature and pressure testing facility 有权
标题翻译：高温高压试验设备
公开(公告)号：US07174797B2
公开(公告)日：2007-02-13
申请号：US10685339
申请日：2003-10-14
申请人： Joseph Brostmeyer , Jack Wilson , Todd A. Ebert
发明人： Joseph Brostmeyer , Jack Wilson , Todd A. Ebert
IPC分类号： G01N33/00
CPC分类号： G01N25/00 , G01M15/14 , G01M99/002 , G01N3/18 , G01N17/002 , G01N2203/0042 , G01N2203/0057 , G01N2203/0226 , G01N2203/0232
摘要： A test facility is provided for testing materials under high temperature, pressure, and mechanical loads. The facility provides a physically scaled system that simulates conditions in hot sections of gas turbine engines. A test article is coated with a test material and exposed to a hot combusting flow in a test section housing. The article may be a pipe or conduit member oriented at any direction to the flow. A second cooler flow of fluid is channeled through the test article to create a sharp temperature gradient in the test article and through the test material. A liquid-cooled sleeve is disposed about the test article to create an annular channel of combusting flow over the test article. The downstream end of the second cooler flow is connected to the upstream end of the main hot flow at the combustion chamber.
摘要翻译：提供测试设备用于在高温，高压和机械负载下测试材料。该设施提供了一个物理尺度的系统，可模拟燃气轮机发动机热段的状况。测试物品涂覆有测试材料并暴露于测试部分壳体中的热燃烧流。制品可以是在流动的任何方向上定向的管道或管道构件。流体的第二个较冷的流动通过测试物品，以在测试物品和测试材料中产生尖锐的温度梯度。液体冷却的套筒围绕测试物品设置，以产生在测试物品上燃烧的环形通道。第二冷却器流的下游端连接到燃烧室的主热流的上游端。

2. 发明授权

US06675872B2 Heat energy dissipation device for a flywheel energy storage system (FESS), an FESS with such a dissipation device and methods for dissipating heat energy 有权
标题翻译：用于飞轮储能系统（FESS）的热能消散装置，具有这种耗散装置的FESS和耗散热能的方法
公开(公告)号：US06675872B2
公开(公告)日：2004-01-13
申请号：US10243359
申请日：2002-09-12
申请人： Eric Lewis , Todd A. Ebert
发明人： Eric Lewis , Todd A. Ebert
IPC分类号： F28D1900
CPC分类号： H02K9/22 , F16F2222/025 , F28D15/0266 , F28D15/0275 , H02K7/025 , H02K9/20 , Y02E60/16 , Y10T74/2119
摘要： Featured are a device, system and method for dissipating at least some heat energy generated by one or more heat generating components of a flywheel energy storage system (FESS). The method includes providing a heat pipe member, having first and second ends, and a heat dissipating member thermally engaged with the heat pipe member second end and configured to transfer heat energy therefrom. The method also includes thermally engaging the heat pipe member first end to the FESS so that at least some heat energy generated by the FESS heat generating component is communicated to the first end and thence through the heat pipe member to the heat dissipating member. Further, the method includes locating the heat dissipating member in a heat sink remote from the FESS.
摘要翻译：特征是用于耗散由飞轮能量存储系统（FESS）的一个或多个发热部件产生的至少一些热能的装置，系统和方法。该方法包括提供具有第一端和第二端的热管构件和与热管构件第二端热接合并且被配置为从其传热热能的散热构件。该方法还包括将热管构件第一端热接合到FESS，使得由FESS发热部件产生的至少一些热能被传递到第一端，并且从而通过热管构件传递到散热构件。此外，该方法包括将散热构件定位在远离FESS的散热器中。

3. 发明授权

US09500094B1 Turbine with radial acting seal 有权
标题翻译：涡轮机带径向作用密封
公开(公告)号：US09500094B1
公开(公告)日：2016-11-22
申请号：US14030102
申请日：2013-09-18
申请人： Darryl S Eng , Todd A Ebert
发明人： Darryl S Eng , Todd A Ebert
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D11/005 , F05D2240/56 , F16J15/0887 , F16J15/3288
摘要： A floating brush seal in a rim cavity of a turbine in a gas turbine engine, where the floating brush seal includes a seal holder in which the floating brush seal floats, and a expandable seal that fits within two radial extending seal slots that maintains a seal with radial displacement of the floating brush seal and the seal holder.
摘要翻译：在燃气涡轮发动机中的涡轮机的轮辋腔中的浮动刷密封件，其中浮动刷密封件包括浮动刷密封件漂浮在其中的密封保持器，以及可扩张密封件，其适合于保持密封件的两个径向延伸的密封槽具有浮动刷密封件和密封件保持器的径向位移。

4. 发明授权

US08133014B1 Triple acting radial seal 有权
标题翻译：三倍径向密封
公开(公告)号：US08133014B1
公开(公告)日：2012-03-13
申请号：US12542495
申请日：2009-08-17
申请人： Todd A Ebert , John A Carella
发明人： Todd A Ebert , John A Carella
IPC分类号： F01D11/02
CPC分类号： F01D11/025 , F05D2240/56 , F05D2300/2261 , F16J15/3288 , F16J15/441 , F16J15/4472
摘要： A triple acting radial seal used as an interstage seal assembly in a gas turbine engine, where the seal assembly includes an interstage seal support extending from a stationary inner shroud of a vane ring, the interstage seal support includes a larger annular radial inward facing groove in which an outer annular floating seal assembly is secured for radial displacement, and the outer annular floating seal assembly includes a smaller annular radial inward facing groove in which an inner annular floating seal assembly is secured also for radial displacement. A compliant seal is secured to the inner annular floating seal assembly. The outer annular floating seal assembly encapsulates the inner annular floating seal assembly which is made from a very low alpha material in order to reduce thermal stress.
摘要翻译：用作燃气涡轮发动机中的级间密封组件的三重作用径向密封件，其中所述密封组件包括从叶片环的固定内护罩延伸的级间密封件支撑件，所述级间密封件支撑件包括较大的环形径向向内凹槽外环形浮动密封组件被固定以用于径向位移，并且外环形浮动密封组件包括较小的环形径向向内的凹槽，内环形浮动密封组件也固定在其中用于径向位移。柔性密封件固定到内环形浮动密封组件。外部环形浮动密封组件封装由非常低的α材料制成的内部环形浮动密封组件，以便减少热应力。

5. 发明授权

US07748959B1 Insulated turbine disc of a turbo-pump 失效
标题翻译：涡轮泵的绝缘涡轮盘
公开(公告)号：US07748959B1
公开(公告)日：2010-07-06
申请号：US11787559
申请日：2007-04-17
申请人： Alex Pinera , Todd A. Ebert
发明人： Alex Pinera , Todd A. Ebert
IPC分类号： F01D5/08
CPC分类号： F01D5/08 , F02K9/48 , F05D2250/621 , F05D2300/504
摘要： A turbine disc used in a turbo-pump that is exposed to a large thermal gradient across the sides of the rotor disc. The warm side of the turbine disc is covered by a cover plate that forms a sealed space between the turbine disc and the cover plate, and this space is evacuated or insulated to form a complete vacuum or as near as a complete vacuum as possible. The surfaces of the turbine disc and cover plate that form the vacuum space are also coated with a reflective coating such as with a highly polished surface of low emissivity in order to minimize the radiation heat loss through the vacuum space. The turbine disc can have a cover plate forming a vacuum space or insulated cavity on both sides of the turbine disc. Ribs are also used within the vacuum space as supports for the cover plate due to the difference in pressure from the ambient side and the vacuum.
摘要翻译：在涡轮泵中使用的涡轮盘，其在转子盘的侧面上暴露于大的热梯度。涡轮盘的温暖的一侧由盖板覆盖，该盖板在涡轮盘和盖板之间形成密封空间，并且该空间被抽空或绝缘以形成尽可能接近完全真空的完全真空。形成真空空间的涡轮盘和盖板的表面也涂覆有诸如具有低发射率的高抛光表面的反射涂层，以便使通过真空空间的辐射热损失最小化。涡轮盘可以具有在涡轮盘的两侧形成真空空间或绝缘腔的盖板。由于与环境侧和真空的压力差，在真空空间内还使用肋作为盖板的支撑。

6. 发明授权

US09416674B1 Floating air riding seal for a turbine 有权
标题翻译：用于涡轮机的浮动空气骑行密封件
公开(公告)号：US09416674B1
公开(公告)日：2016-08-16
申请号：US14066364
申请日：2013-10-29
申请人： Todd A Ebert
发明人： Todd A Ebert
IPC分类号： F01D11/00 , F01D11/02
CPC分类号： F01D11/001 , F01D11/003 , F01D11/02 , F16J15/342 , F16J15/3448
摘要： A floating air riding seal for a gas turbine engine with a rotor and a stator, an annular piston chamber with an axial moveable annular piston assembly within the annular piston chamber formed in the stator, an annular cavity formed on the annular piston assembly that faces a seal surface on the rotor, where the axial moveable annular piston includes an inlet scoop on a side opposite to the annular cavity that scoops up the swirling cooling air and directs the cooling air to the annular cavity to form an air cushion with the seal surface of the rotor.
摘要翻译：一种用于具有转子和定子的燃气涡轮发动机的浮动气动密封件，在形成在定子中的环形活塞室内具有轴向可移动环形活塞组件的环形活塞室，形成在环形活塞组件上的环形空腔，密封表面在转子上，其中轴向可移动环形活塞在与环形空腔相对的一侧上包括入口勺，该入口勺向上旋转冷却空气，并将冷却空气引导到环形空腔，以形成气垫，其密封表面为转子。

7. 发明授权

US07574904B1 Advanced hot section materials and coatings test rig 有权
标题翻译：先进的热段材料和涂料试验台
公开(公告)号：US07574904B1
公开(公告)日：2009-08-18
申请号：US11263522
申请日：2005-11-01
申请人： Daniel O Davies , Khalil O Qader , Joseph Brostmeyer , Jack W Wilson , Todd A Ebert
发明人： Daniel O Davies , Khalil O Qader , Joseph Brostmeyer , Jack W Wilson , Todd A Ebert
IPC分类号： G01M15/14
CPC分类号： G01M15/14
摘要： A test rig that reproduces high temperature and high pressure conditions found in a gas turbine engine for testing materials under these conditions. The test rig is formed of a plurality of modules connected in series to form the test rig. A specimen rotation module is connected to a mechanical load module, which is connected to a combustor module, which is connected to a test section module on which one or more test specimens are placed, which connects to an exhaust section module, which is connected to a thrust bearing & air inlet section module. The modules are cylindrical in shape and connected in series to form a compact test rig.
摘要翻译：在这种条件下，用于测试燃料涡轮发动机中测试材料的高温和高压条件的试验台。试验台由多个串联连接的模块形成，形成试验台。样本旋转模块连接到机械负载模块，该机械负载模块连接到燃烧器模块，该燃烧器模块连接到其上放置有一个或多个测试样本的测试部分模块，其连接到排气部分模块，该排气部分模块连接到推力轴承和进气部分模块。模块是圆柱形的并且串联连接以形成紧凑的测试台。

8. 发明授权

US07540709B1 Box rim cavity for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的箱体边缘腔
公开(公告)号：US07540709B1
公开(公告)日：2009-06-02
申请号：US11255125
申请日：2005-10-20
申请人： Todd A. Ebert
发明人： Todd A. Ebert
IPC分类号： F04D29/08
CPC分类号： F01D11/02 , F01D5/02 , F01D9/041 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/128 , F05D2240/30 , F05D2240/55
摘要： A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions.
摘要翻译：一种具有带叶片和静止叶片的转子的燃气涡轮发动机，在叶片和叶片之间形成平台密封，用于阻止热气从通过涡轮机的热气流吸入涡轮机叶轮空间，平台密封件包括轴向延伸平台在叶片和叶片上，以及从平台延伸并且在指状物和平台之间形成限制的径向延伸的指状物，以及形成在限制之间的缓冲腔，其中手指以大致径向方向布置，使得叶片能够被移除从涡轮发动机沿径向方向，而不必首先移除叶片。在另外的实施例中，平台密封组件可以具有在附加限制之间形成的两个或三个缓冲腔。

9. 发明授权

US09394826B1 Circulating fluidized bed cooling for an industrial gas turbine engine 有权
标题翻译：用于工业燃气轮机的循环流化床冷却
公开(公告)号：US09394826B1
公开(公告)日：2016-07-19
申请号：US13835692
申请日：2013-03-15
申请人： Todd A Ebert
发明人： Todd A Ebert
IPC分类号： F02C1/00 , F02C7/00
CPC分类号： F02C7/16
摘要： The present invention is an industrial gas turbine engine with a circulating fluidized bed cooling system to provide cooling to certain parts of the engine such as a transition duct or a stator vane. The circulating fluidized bed cooling system can be used to cool a stator vane, a casing, or any stationary part of the engine. A circulating fluidized bed cooling system uses very fine particles that pass along with a cooling fluid such as cooling air and provide for a much higher heat transfer coefficient than does turbulent flow cooling air because of the particles. The fine particles produce conduction cooling from the hot surface to the particles that are then carried along in the circulating fluid flow to another location where the heat picked up by the particles is then transferred out from the particles.
摘要翻译：本发明是一种具有循环流化床冷却系统的工业燃气涡轮发动机，以向诸如过渡管道或定子叶片的发动机的某些部分提供冷却。循环流化床冷却系统可用于冷却定子叶片，壳体或发动机的任何静止部分。循环流化床冷却系统使用非常细的颗粒，其与诸如冷却空气的冷却流体一起传递，并且由于颗粒而提供比湍流冷却空气高得多的传热系数。细颗粒产生从热表面到颗粒的传导冷却，然后颗粒在循环流体流中被传送到另一个位置，其中由颗粒吸收的热量然后从颗粒中移出。

10. 发明申请

US20160017741A1 Box Rim Cavity for a Gas Turbine Engine 审中-公开
标题翻译：燃气轮机发动机箱体腔
公开(公告)号：US20160017741A1
公开(公告)日：2016-01-21
申请号：US14674261
申请日：2015-03-31
申请人： Todd A. Ebert
发明人： Todd A. Ebert
IPC分类号： F01D11/02 , F01D5/02 , F01D9/04
CPC分类号： F01D11/02 , F01D5/02 , F01D9/041 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/128 , F05D2240/30 , F05D2240/55
摘要： A gas turbine engine having a rotor with blades and a stationary vane, a platform seal is formed between the blade and vane for inhibiting ingestion of hot gas from a hot gas flow through the turbine into turbine wheel spaces, the platform seal including axial extending platforms on the blade and vane, and radial extending fingers extending from the platforms and forming restrictions between the fingers and the platforms, and a buffer cavity formed between the restrictions, where the fingers are so arranged in a generally radial direction that the vane can be removed from the turbine engine in a radial direction without having to remove the blades first. In additional embodiments, the platform seal assembly can have two or three buffer cavities formed between additional restrictions.
摘要翻译：一种具有带叶片和静止叶片的转子的燃气涡轮发动机，在叶片和叶片之间形成平台密封，用于阻止热气从通过涡轮机的热气流吸入涡轮机叶轮空间，平台密封件包括轴向延伸平台在叶片和叶片上，以及从平台延伸并且在指状物和平台之间形成限制的径向延伸的指状物，以及形成在限制之间的缓冲腔，其中手指以大致径向方向布置，使得叶片能够被移除从涡轮发动机沿径向方向，而不必首先移除叶片。在另外的实施例中，平台密封组件可以具有在附加限制之间形成的两个或三个缓冲腔。

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