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1. 发明申请

WO2021230874A1 COMPRESSOR ROTOR STRUCTURE 审中-公开
公开(公告)号：WO2021230874A1
公开(公告)日：2021-11-18
申请号：PCT/US2020/032946
申请日：2020-05-14
申请人： DRESSER-RAND COMPANY
发明人： REIMANN, Martin , PEER, David J. , MEYER, Marcus , HUTH, Sebastian , MINY, Kevin
IPC分类号： F04D17/12 , F04D29/053 , F04D29/054 , F04D29/28 , F04D29/62
摘要： Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from sealing sleeves that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. The sealing sleeves may be affixed to adjoining structures (e.g., adjoining impeller bodies) by way of a slip fit connection to one of the adjoining structures and an interference fit connection with respect to the other adjoining structure, which is conducive to a user-friendly assembly of the sealing sleeves with the adjoining structures.

2. 发明申请

WO2021119049A1 PUMPED HEAT ENERGY STORAGE SYSTEM WITH ANNULAR DUCTING ARRANGEMENT 审中-公开
公开(公告)号：WO2021119049A1
公开(公告)日：2021-06-17
申请号：PCT/US2020/063882
申请日：2020-12-09
申请人： DRESSER-RAND COMPANY
发明人： KERTH, Jason M.
IPC分类号： F02C1/04 , F02C1/10 , F02C6/14 , F28D20/02
摘要： A pumped heat energy storage (PHES) system, involving an annular ducting arrangement is provided. Disclosed embodiments are believed to resolve the issue of containing a high temperature working fluid at elevated pressure by appropriately compartmentalizing by way of the annular ducting arrangement the functions of temperature management and pressure containment in a cost-effective and reliable manner.

3. 发明申请

WO2020068109A1 MODULAR COOLING ARRANGEMENT FOR COOLING AIRFOIL COMPONENTS IN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2020068109A1
公开(公告)日：2020-04-02
申请号：PCT/US2018/053393
申请日：2018-09-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： DYER, Zachary D. , FISCHLE, Moritz , MARSH, Jan H. , FU, Wentao , JAMES, Allister William , MILLER, Andrew , MITCHELL, David J.
IPC分类号： F01D5/14 , F01D5/28 , F01D9/04
摘要： A modular cooling arrangement for cooling an airfoil component (10) in a combustion turbine engine is provided. A body (16) of the airfoil component, and a cooling manifold (18) or a flow sleeve (50, 60) may be disposed in a cavity in the body of the airfoil component. By way of example, the body of the airfoil component may be a ceramic matrix composite body, a MAX phase ternary ceramic body, or a metallic body. Disclosed embodiments are effective to reliably and cost-effectively reduce a level of internal pressurization in the component while providing appropriate cooling to portions of the component subject to a hot flow of gases and accommodating thermal growth differences that may develop between components of the modular cooling arrangement and anchoring structures to which the modular cooling arrangement may be affixed.

4. 发明申请

WO2020040774A1 CENTRIFUGAL COMPRESSOR AND METHOD FOR DIRECTING FLOW OF PROCESS FLUIDS IN SUCH A CENTRIFUGAL COMPRESSOR 审中-公开
公开(公告)号：WO2020040774A1
公开(公告)日：2020-02-27
申请号：PCT/US2018/047745
申请日：2018-08-23
申请人： DRESSER-RAND COMPANY
发明人： SRINIVASAN, Ravichandra , SARETTO, Silvano R. , ALLES, Katherine , BROWN, Paul Morrison
IPC分类号： F04D29/28 , F04D29/44 , F04D29/66 , F04D21/00
摘要： Process fluid flow in the primary flow passage (70) of a compressor (20) is altered by selective inclusion of one or more tooth-like, annular circumferential flanges (48) in its secondary flow passage (72). The compressor's secondary flow passage is defined between opposing surfaces of a hub (40) of the impeller (26) and the opposing hub side (64) of the housing (21). The annular circumferential flange is coupled to the hub of the impeller and/or the hub side of the compressor housing within the secondary flow passage. A compressor incorporating one or more of the annular circumferential flanges in its secondary flow passage achieves more uniform flow velocity flow within the primary flow passage.

5. 发明申请

WO2019160537A1 MODULAR LINEAR RECIPROCATING COMPRESSOR 审中-公开
公开(公告)号：WO2019160537A1
公开(公告)日：2019-08-22
申请号：PCT/US2018/018102
申请日：2018-02-14
申请人： DRESSER-RAND COMPANY
发明人： DELMOTTE, Scott J. , BISSELL, Daniel , YONKER, Gregory W.
IPC分类号： F04B35/04
摘要： A linear motor for moving a piston rod of a reciprocating compressor. The motor includes a guidance assembly having a moveable secondary carrier that is attached to the piston rod. The motor also includes at least one permanent magnet attached to the secondary carrier and at least one primary winding attached to the guidance assembly. In addition, the motor includes a controller that controls power supplied to the primary winding to generate a magnetic field that interacts with a magnetic field generated by the permanent magnet to provide a force that moves the permanent magnet, the secondary carrier and the piston rod in a reciprocating linear motion.

6. 发明申请

WO2019156666A1 TRANSITION-TO-TURBINE SEAL ASSEMBLY AND METHOD FOR MANUFACTURING SAME 审中-公开
公开(公告)号：WO2019156666A1
公开(公告)日：2019-08-15
申请号：PCT/US2018/017333
申请日：2018-02-08
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： BARTLEY, Robert H. , SLOBODA, Richard L. , CASSAR, Daniel
IPC分类号： F01D9/02 , F01D11/00
CPC分类号： F01D9/023 , F01D11/005
摘要： A transition-to-turbine seal assembly, and method for manufacturing same are provided. The method allows forming an arcuate seal piece (110) including a first sealing flange (112) and a second sealing flange (114). Each sealing flange defining a respective sealing surface (116, 118). The method further allows forming an arcuate fastening piece (120) including circumferentially spaced fastening hooks (122) interspersed between circumferentially extending gap-sections (124). The fastening piece may be affixed to the seal piece by way of a joint 130 to form the transition-to-turbine seal assembly. The simplicity of the proposed design is conducive to manufacturing-friendly and time-efficient operations that improve manufacturability, dimensional accuracy and repeatability, while reducing costs of the transition-to-turbine seal assembly.

7. 发明申请

WO2018208513A1 GAS TURBINE INLET INTERFACE ASSEMBLY 审中-公开
公开(公告)号：WO2018208513A1
公开(公告)日：2018-11-15
申请号：PCT/US2018/029821
申请日：2018-04-27
申请人： DRESSER-RAND AS , DRESSER-RAND COMPANY
发明人： MAIER, William C. , EIDSMOEN, OEivind
IPC分类号： F02C7/04
摘要： An inlet duct (106) for a gas turbine wherein the inlet duct (106) may include a gas turbine inlet interface assembly (124) and a plurality of walls (126a-d) defining a first portion (128a) of an inlet flow channel (128a, 128b). The gas turbine inlet interface assembly (124) may include a mounting plate (148) pivotably connected to a first wall of the plurality of walls (126a-d) and defining a plate opening (156). The gas turbine inlet interface assembly (124) may also include an annular duct having a first end (152) coupled to or integral with the mounting plate (148), and a first end (152) configured to sealingly connect with an inlet component (116) of the gas turbine. The annular duct may define a second portion of the inlet flow channel (128b) extending from the plate opening (156). The first portion (128a) and the second portion (128b) of the inlet flow channel (128a, 128b) may be configured to fluidly couple a motive gas source with the gas turbine.

8. 发明申请

WO2017155914A1 DUCTING ARRANGEMENT IN A COMBUSTION SYSTEM OF A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气轮机发动机燃烧系统的运行布置
公开(公告)号：WO2017155914A1
公开(公告)日：2017-09-14
申请号：PCT/US2017/021039
申请日：2017-03-07
申请人： SIEMENS ENERGY, INC.
发明人： LASTER, Walter Ray , MEADOWS, Joseph , NORTH, Andrew J. , PORTILLO BILBAO, Juan Enrique
IPC分类号： F23R3/28 , F23R3/34 , F01D9/02 , F23R3/00
CPC分类号： F01D9/023 , B22F3/1055 , B22F5/10 , B33Y80/00 , F02C7/222 , F05D2220/32 , F05D2230/50 , F05D2250/50 , F23R3/002 , F23R3/286 , F23R3/346 , F23R2900/00018 , Y02P10/295
摘要： A ducting arrangement (30) in a combustion system of a gas turbine engine is provided. The ducting arrangement may be formed by duct segments (32) circumferentially adjoined with one another to form a flow duct structure (e.g., a flow-accelerating structure (34)) and a pre-mixing structure (35). The flow duct structure is fluidly coupled to pass a cross-flow of combustion gases. The pre-mixing structure (35) may include an array of pre-mixing tubes (48) fluidly coupled to receive air and fuel conveyed by a manifold (42) to inject a mixture of air and fuel into the cross-flow of combustion gases that passes through the flow duct structure. The duct segments or the entire ducting arrangement may be formed as a unitized structure, such as a single piece using a rapid manufacturing technology, such as 3D Printing/Additive Manufacturing (AM) technology.
摘要翻译：提供了燃气涡轮发动机的燃烧系统中的管道装置（30）。管道装置可以通过沿周向彼此邻接的管道段（32）形成，以形成流动管道结构（例如，流动加速结构（34））和预混合结构（35）。流动通道结构流体耦合以传递燃烧气体的交叉流动。预混合结构（35）可以包括流体联接以接收由歧管（42）输送的空气和燃料以将空气和燃料的混合物喷射到燃烧气体的交叉流动中的预混合管（48）的阵列穿过流动通道结构。管道段或整个管道布置可以使用诸如3D打印/增材制造（AM）技术的快速制造技术形成为单元结构，诸如单件。

9. 发明申请

WO2017091318A1 FUEL NOZZLE HAVING RESPECTIVE ARRAYS OF PRE-MIXING CONDUITS WITH RESPECTIVE VORTEX GENERATORS 审中-公开
标题翻译：燃料喷嘴具有相对的涡旋发生器的预混合管道的阵列
公开(公告)号：WO2017091318A1
公开(公告)日：2017-06-01
申请号：PCT/US2016/058972
申请日：2016-10-27
申请人： SIEMENS ENERGY, INC.
发明人： BECK, Christian , MEADOWS, Joseph
IPC分类号： F23R3/28 , F23D14/02 , F23D14/64
CPC分类号： F23R3/286 , F02C7/222 , F05D2220/32 , F05D2240/35 , F05D2260/60 , F23D14/02 , F23D14/64 , F23D2206/10 , F23D2900/14004 , F23D2900/14021
摘要： A fuel nozzle including vortex generating features for use in a combustion turbine engine is provided. An array of inner pre-mixing conduits (20) extends between an inlet end (14) and an outlet end (16) of the nozzle. An array of outer pre-mixing conduits (22) may be disposed radially outwardly relative to the inner pre-mixing conduits (20). A fuel-directing tube (24) includes fuel-directing arms (26) structured to direct fuel flow into the outer pre-mixing conduits (22) to be mixed with a flow of air. The fuel-directing arms include a bluff structural arrangement (30) that may be disposed upstream of fuel injection locations (32, 32) into the outer pre-mixing conduits (22). The proposed nozzle is believed to provide superior micro-mixing capability, such as by increasing the depth of penetration of jets of fuel in a cross-flow of air, and/or formation of vortices in a wake zone downstream from the vortex generating features.
摘要翻译：提供了包括用于燃气涡轮发动机的涡流产生特征的燃料喷嘴。内部预混合管道（20）的阵列在喷嘴的入口端（14）和出口端（16）之间延伸。外部预混合导管（22）的阵列可相对于内部预混合导管（20）径向向外布置。燃料引导管（24）包括燃料引导臂（26），燃料引导臂构造成引导燃料流入外部预混合管道（22）以与空气流混合。燃料引导臂包括可设置在燃料喷射位置（32,32）的上游进入外部预混合管道（22）的钝体结构布置（30）。所提出的喷嘴被认为提供优异的微混合能力，例如通过增加燃料的喷射的穿透深度在空气横流，和/或从所述涡流生成特征在尾流区的形成旋涡的下游。

10. 发明申请

WO2016178664A1 TURBINE TRANSITION DUCT WITH IMPROVED LAYOUT OF COOLING FLUID CONDUITS FOR A COMBUSTION TURBINE ENGINE 审中-公开
标题翻译：具有改进的燃油涡轮发动机冷却流体布置的涡轮转换管
公开(公告)号：WO2016178664A1
公开(公告)日：2016-11-10
申请号：PCT/US2015/029135
申请日：2015-05-05
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： SCHILP, Reinhard
IPC分类号： F01D9/02 , F01D25/12 , F23R3/00
CPC分类号： F01D9/023 , F01D25/12 , F23R3/005 , F23R2900/03043
摘要： An improved layout of cooling fluid conduits in a turbine transition duct is provided. The transition duct (10) may include a transition body made with a multi-panel arrangement (12, 14) that defines a passage to route a hot combustion gas from an inlet to an outlet of the transition duct. One or more longitudinally-extending cooling fluid conduits (18) may be disposed in the multi-panel arrangement. The longitudinally-extending cooling fluid conduits may extend along a flow direction in the transition duct. One or more circumferentially-extending cooling fluid conduits (20) may be further disposed in the multi-panel arrangement. The circumferentially-extending cooling fluid conduits may extend perpendicular to the flow direction in the transition duct. A layout of the longitudinally-extending cooling fluid conduits and the circumferentially-extending cooling fluid conduits may be configured in the multi-panel arrangement based on an expected heat load profile in the transition duct.
摘要翻译：提供了一种改进的涡轮转换管道中冷却流体管道的布局。过渡管道（10）可以包括由多面板装置（12,14）制成的过渡体，所述过渡体限定了将热燃烧气体从过滤管道的入口引导到出口的通道。一个或多个纵向延伸的冷却流体管道（18）可以设置在多面板装置中。纵向延伸的冷却流体管道可以沿着过渡管道中的流动方向延伸。一个或多个周向延伸的冷却流体导管（20）可以进一步设置在多面板装置中。沿周向延伸的冷却流体管道可以在过渡管道中垂直于流动方向延伸。纵向延伸的冷却流体管道和周向延伸的冷却流体管道的布置可以基于过渡管道中的期望的热负荷分布来配置在多面板布置中。

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