专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

11. 发明申请

WO2017189440A1 LOW PRESSURE COMPRESSOR DIFFUSER BLEED OFF ARRANGEMENT FOR AN INDUSTRIAL GAS TURBINE ENGINE 审中-公开
标题翻译：工业燃气涡轮发动机低压压气机扩压器出线安排
公开(公告)号：WO2017189440A1
公开(公告)日：2017-11-02
申请号：PCT/US2017/029152
申请日：2017-04-24
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： OROSA, John, A. , BROSTMEYER, Joseph, D. , JONES, Russell, B. , CEJKA, Justin, T.
IPC分类号： F02C3/04 , F02C6/08 , F02C7/18 , F02C9/18
CPC分类号： F02C6/08 , F02C3/04 , F02C7/18 , F02C9/18 , F04D19/02 , F04D29/541 , F04D29/545 , F04D29/682 , F05D2220/32 , F05D2220/76 , F05D2260/232
摘要： An industrial gas turbine engine with a high spool and a low spool in which low pressure compressed air is supplied to the high pressure compressor, and where a portion of the low pressure compressed air is bled off for use as cooling air for hot parts in the high pressure turbine of the engine. Annular bleed off channels are located in the LPC diffuser. The bleed channels bleed off around 15% of the core flow and pass the bleed off air into a cooling flow channel that then flows into the cooling circuits in the turbine hot parts.
摘要翻译：具有高阀芯和低阀芯的工业燃气涡轮发动机，其中低压压缩空气被供应到高压压缩机，并且其中一部分低压压缩空气被排放以供使用作为用于发动机的高压涡轮机中的热部件的冷却空气。环形泄放通道位于LPC扩散器中。泄放通道泄出大约15％的核心流量，并将泄出的空气送入冷却流动通道，然后流入涡轮机热部件的冷却回路。

12. 发明申请

WO2017155506A1 TURBINE LAST STAGE ROTOR BLADE WITH FORCED DRIVEN COOLING AIR 审中-公开
标题翻译：具有强迫驱动的冷却空气汽轮机末级旋翼桨叶
公开(公告)号：WO2017155506A1
公开(公告)日：2017-09-14
申请号：PCT/US2016/021217
申请日：2016-03-07
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： BROSTMEYER, Joseph D.
IPC分类号： F01D5/08 , F01D25/12 , F02C7/18
摘要： A turbine of a gas turbine engine with a rotor (11) and a stator (15, 16) forming a rim cavity (18), where the rotor includes a turbine rotor blade (12) with a cooling air channel opening into the rim cavity (18), and a centrifugal impeller (21) rotatably connected to the rotor in which the centrifugal impeller discharges pressurized cooling air into the rim cavity to improve the rim cavity seal and to supply pressurized cooling air to the rotor blade cooling air channel (13).
摘要翻译：
燃气涡轮发动机的涡轮机具有转子（11）和形成一个边缘腔体（18），其中所述转子包括一个涡轮转子叶片（12）的定子（15，16）冷却空气通道通向所述边缘腔体（18），和一个离心式叶轮（21）可旋转地连接到其中离心式叶轮排出的加压的冷却空气进入所述轮缘空腔，以提高轮缘空腔封条和供给加压冷却空气到所述转子转子叶片冷却空气通道（13）。

13. 发明申请

WO2017127629A1 TURBOPUMP WITH A SINGLE PIECE HOUSING AND A SMOOTH ENAMEL GLASS SURFACE 审中-公开
标题翻译： TURBOPUMP具有单件式外壳和平滑珐琅玻璃表面
公开(公告)号：WO2017127629A1
公开(公告)日：2017-07-27
申请号：PCT/US2017/014259
申请日：2017-01-20
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： MILLER, Timothy, J. , PINERA, Alex , BROOKS, Stephen, M. , APPLEBY, John, W. , LEONARD, Timothy, G.
IPC分类号： F04D29/02 , F02K9/46 , F04D29/22 , F04D29/42 , F04D29/62 , B22F3/00
CPC分类号： F04D29/026 , B22F3/115 , B22F7/08 , C22C32/001 , F02K9/46 , F04D13/04 , F04D29/2216 , F04D29/2222 , F04D29/2227 , F04D29/2294 , F04D29/426 , F04D29/4286 , F04D29/628 , F05D2300/175 , F05D2300/21 , F05D2300/2112 , F05D2300/2118 , F05D2300/611
摘要： A turbopump such as a liquid oxygen (LOX) turbopump for a liquid rocket engine is formed using a metal additive manufacturing process in which a single-piece impeller is formed within a single piece housing, the impeller being trapped within the single piece housing. The impeller is formed with an axial bore in which a shaft is inserted after the impeller and housing have been formed. The turbopump includes a protective coating that forms a reaction resistant surface on the base metal in areas of the base metal that are exposed to an oxidizer during pumping. The protective coating may be an enamel glass, a superalloy layer beneath an enamel glass layer, a composite layer of a mixture of enamel glass and superalloy, a composite mixture of oxide and superalloy, or a composite layer of a mixture of enamel glass, superalloy, and oxide.
摘要翻译：用于液体火箭发动机的诸如液氧（LOX）涡轮泵的涡轮泵是利用金属增材制造工艺形成的，其中在单件壳体内形成单件式叶轮，叶轮为被困在单件住房。叶轮形成有轴向孔，在叶轮和壳体已经形成之后，轴插入该轴向孔中。涡轮泵包括保护涂层，该保护涂层在泵送期间暴露于氧化剂的基体金属区域中的基体金属上形成抗反应表面。保护涂层可以是搪瓷玻璃，搪瓷玻璃层下面的超级合金层，搪瓷玻璃和超级合金的混合物的复合层，氧化物和超合金的复合混合物，或者搪瓷玻璃，高温合金的混合物的复合层，和氧化物。

14. 发明申请

WO2017058709A1 CAES COMBUSTOR TEST FACILITY 审中-公开
标题翻译： CAES COMBUSTOR测试设备
公开(公告)号：WO2017058709A1
公开(公告)日：2017-04-06
申请号：PCT/US2016/053694
申请日：2016-09-26
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： BROSTMEYER, Joseph D. , JONES, Russell B. , DOWNS, James P.
IPC分类号： G01M15/14
CPC分类号： G01M15/14
摘要： A system and method for testing a combustor or other component of a large industrial gas turbine engine. A test facility for testing a gas turbine engine component includes a storage reservoir, a heat exchanger (13) with a first fluid flow passage connected to the storage reservoir and a second fluid flow passage, a combustor (18) connected to the second fluid flow passage of the heat exchanger (13), a hot gas stream from the combustor flowing within the second fluid flow passage, and a test component of a gas turbine engine connected to the second fluid flow passage of the heat exchanger (13). The compressed air from the storage reservoir (11) passes through the heat exchanger (13) first fluid flow passage and is preheated from the hot gas stream passing through the second fluid flow passage, and the preheated compressed air from the heat exchanger (13) passes into the test component for testing.
摘要翻译：一种用于测试大型工业燃气涡轮发动机的燃烧器或其他部件的系统和方法。用于测试燃气涡轮发动机部件的测试设备包括存储容器，具有连接到存储容器的第一流体流动通道的热交换器（13）和第二流体流动通道，连接到第二流体流的燃烧器（18）热交换器（13）的通道，来自在第二流体通道内流动的燃烧器的热气流和连接到热交换器（13）的第二流体流动通道的燃气涡轮发动机的测试部件。来自储存容器（11）的压缩空气通过热交换器（13）第一流体流动通道，并且从通过第二流体流动通道的热气流和来自热交换器（13）的预热的压缩空气预热，进入测试组件进行测试。

15. 发明申请

WO2015057288A1 GAS TURBINE ENGINE WITH LIQUID METAL COOLING 审中-公开
标题翻译：气体涡轮发动机带液体金属冷却
公开(公告)号：WO2015057288A1
公开(公告)日：2015-04-23
申请号：PCT/US2014/048494
申请日：2014-07-28
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： BROSTMEYER, Joseph D. , APPLEBY JR., John W. , JONES, Russell
IPC分类号： F01D5/18 , F01D9/04 , F02C7/16
CPC分类号： F01D5/181 , F01D5/188 , F01D9/04 , F02C7/16 , F05D2260/207 , F05D2300/1606 , F05D2300/1612
摘要： A gas turbine engine with a closed-loop liquid metal cooling fluid system for cooling stator vanes within the turbine, in which the stator vanes are made of a metallic material that will not react with the liquid metal cooling fluid. The stator vane may be made from a typical metal material such as ferrous metal alloys, nickel alloys or cobalt (Co) alloys, and an insert or liner made of molybdenum or tantalum may be placed inside to protect the outer vane material from reacting with a liquid metal such as bismuth, lead (Pb), indium, or alloy mixtures of thereof. In the case where the liquid coolant is bismuth, the liquid bismuth may be purged from the cooling system before the fluid cools and solidifies so the solidified bismuth does not expand and break the vanes.
摘要翻译：一种具有用于冷却涡轮内的定子叶片的闭环液态金属冷却流体系统的燃气涡轮发动机，其中定子叶片由不会与液态金属冷却流体反应的金属材料制成。定子叶片可以由诸如黑色金属合金，镍合金或钴（Co）合金的典型金属材料制成，并且可以将由钼或钽制成的插入件或衬垫放置在内部以保护外部叶片材料不与液态金属如铋，铅（Pb），铟或其合金混合物。在液体冷却剂为铋的情况下，液体铋可以在流体冷却并固化之前从冷却系统清除，因此凝固的铋不会膨胀并破坏叶片。

16. 发明申请

WO2018182816A1 TURBINE AIRFOIL WITH THIN TRAILING EDGE COOLING CIRCUIT 审中-公开
公开(公告)号：WO2018182816A1
公开(公告)日：2018-10-04
申请号：PCT/US2018/012553
申请日：2018-01-05
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： JONES, Russell, B.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D9/065 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/81 , F05D2250/185 , F05D2260/202 , F05D2260/205
摘要： A cooling circuit for a trailing edge region of a turbine airfoil where the trailing edge is relatively thin, the cooling circuit having a series of aftward-flowing channels alternating with a series of forward-flowing cooling channels, and a turn channel at the trailing edge of the airfoil where the aftward-flowing channels flow into the forward-flowing channels in order to keep the airfoil thin and to provide cooling to the thin trailing edge. Spanwise extending cooling supply channels and cooling return channels are connected to the aftward and forward-flowing channels and positioned to allow for a thinner airfoil.

17. 发明申请

WO2017142873A1 INDUSTRIAL GAS TURBINE ENGINE WITH FIRST AND SECOND STAGE ROTOR COOLING 审中-公开
标题翻译：工业燃气轮机的第一和第二阶段转子冷却
公开(公告)号：WO2017142873A1
公开(公告)日：2017-08-24
申请号：PCT/US2017/017820
申请日：2017-02-14
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： JONES, Russell B. , BROWN, Wesley D.
IPC分类号： F01D5/08 , F01D25/12
CPC分类号： F01D5/085 , F01D25/12 , F05D2260/205
摘要： An industrial gas turbine engine with first and stage turbine rotor blade cooling circuit in which the blade cooling air flows through a central passage within the rotor of the engine, flows through a space between first and second stage rotors, separates into two flows with one flow going to the first stage blades and the second flow going to the second stage blades, the two flows then collecting in a common manifold, where the spent blade cooling air flows forward through the first stage rotor and along a rotor cooling passage and into a stator cavity, where the cooling air then is discharged into a combustor.
摘要翻译：具有第一级涡轮转子叶片冷却回路的工业燃气涡轮发动机，其中叶片冷却空气流过发动机转子内的中央通道，流过第一级转子和第二级转子之间的空间分成两路流，一路流到达第一级叶片，第二路流到达第二级叶片，然后两路流聚集在一个共用歧管中，在这里，用过的叶片冷却空气向前流过第一级转子并沿着一个转子冷却通道并进入一个定子腔，然后冷却空气被排入燃烧室。

18. 发明申请

WO2011056425A2 BEARINGLESS FLOATING WIND TURBINE 审中-公开
标题翻译：无轴承风力涡轮机
公开(公告)号：WO2011056425A2
公开(公告)日：2011-05-12
申请号：PCT/US2010/053349
申请日：2010-10-20
申请人： FLORIDA TURBINE TECHNOLOGIES, INC. , RYZNIC, John E. , BROSTMEYER, Joseph D. , WILSON, Jack, W., Jr.
发明人： RYZNIC, John E. , BROSTMEYER, Joseph D. , WILSON, Jack, W., Jr.
IPC分类号： F03D11/04
CPC分类号： F03D3/005 , F03D13/25 , F05B2220/7066 , F05B2220/7068 , F05B2240/212 , F05B2240/301 , F05B2240/61 , F05B2240/93 , F05B2240/95 , F05B2260/85 , F05B2260/90 , Y02E10/727 , Y02E10/74
摘要： A bearingless floating wind turbine has a tall narrow main support structure with a center of buoyancy located well above the center of gravity to provide stability to the wind turbine while supported for rotation in a body of water, a vertical axis turbine blade extends from the main support structure and rotates together under a wind, and a non-rotating shaft extends through the main support structure with a vertical axis direct drive generator connected between the main support structure and the non-rotating shaft to produce electricity when the main support structure rotates. An anchor line connected to the non-rotating shaft prevents the floating wind turbine from drifting in a body of water.
摘要翻译：无轴承浮动风力涡轮机具有高的窄的主要支撑结构，其浮力中心位于重心之上，以便在风力涡轮机同时被支撑以在水体中旋转时提供稳定性，垂直轴线涡轮机叶片从主体支撑结构并在风中一起旋转，并且非旋转轴通过连接在主支撑结构和非旋转轴之间的垂直轴直接驱动发生器延伸穿过主支撑结构，以在主支撑结构旋转时产生电力。连接到非旋转轴的锚线防止浮动风力涡轮机在水体中漂移。

19. 发明申请

WO2006022761A1 HIGH TEMPERATURE AND PRESSURE TESTING FACILITY 审中-公开
标题翻译：高温和压力测试设备
公开(公告)号：WO2006022761A1
公开(公告)日：2006-03-02
申请号：PCT/US2004/033551
申请日：2004-10-12
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： BROSTMEYER, Joseph , WILSON, Jack , EBERT, Todd, A.
IPC分类号： G01N25/00
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 (100) is provided for testing materials under high temperature, pressure, and mechanical loads. The facility (100) 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 (105). The article may be a pipe or conduit member oriented at any direction to the flow. A second cooler flow (210) 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 (240).
摘要翻译：提供测试设备（100）用于在高温，高压和机械负载下测试材料。设备（100）提供了模拟燃气涡轮发动机热段条件的物理缩放系统。测试物品涂覆有测试材料并暴露于测试部分壳体（105）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。流体的第二冷却器流（210）被引导通过测试物品，以在测试物品和测试材料中产生急剧的温度梯度。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（240）处的主热流的上游端。

20. 发明申请

WO2019059888A1 APPARATUS AND PROCESS FOR CONVERTING AN AERO GAS TURBINE ENGINE INTO AN INDUSTRIAL GAS TURBINE ENGINE FOR ELECTRIC POWER PRODUCTION 审中-公开
公开(公告)号：WO2019059888A1
公开(公告)日：2019-03-28
申请号：PCT/US2017/052225
申请日：2017-09-19
申请人： FLORIDA TURBINE TECHNOLOGIES, INC.
发明人： BROSTMEYER, Joseph, D. , JONES, Russell, B.
IPC分类号： F01D15/10 , B64D41/00 , F02C3/10 , F02C6/00 , F02C7/32
摘要： An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式