子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 221 | GAS TURBINE ENGINE VANE END DEVICES | US14132738 | 2013-12-18 | US20150003963A1 | 2015-01-01 | Linnea Taketa; John Munson; Ted J. Freeman |
| A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be a variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two. | ||||||
| 222 | Metal nanoparticle dispersion | US13041599 | 2011-03-07 | US08828276B2 | 2014-09-09 | Yasuyuki Hotta |
| According to one embodiment, metal nanoparticle dispersion includes organic solvent, and metal-containing particles dispersed in the organic solvent. The metal-containing particles include first metal nanoparticles and second metal nanoparticles. Each of the first metal nanoparticles has a high-molecular compound on at least part of a surface thereof. Each of the second metal nanoparticles has a low-molecular compound on at least part of a surface thereof. A total amount of the low-molecular compound on all of the second nanoparticles includes an amount of a primary amine as the low-molecular compound. | ||||||
| 223 | BRUSH SEAL SYSTEM WITH ELLIPTICAL CLEARANCE | US14253307 | 2014-04-15 | US20140225326A1 | 2014-08-14 | Xiaoqing Zheng; Mehmet Demiroglu; Michael Dennis Mack; Guoqiang Lu |
| The present application provides for a brush seal system for use about a rotor of a rotary machine. The brush seal system may include a number of brush seal segments, with each of the brush seal segments having a number of bristles, and one or more of the brush seal segments including an elliptical profile so as to vary a clearance between the brush seal segments and the rotor. | ||||||
| 224 | Article having vitreous monocoating | US13149533 | 2011-05-31 | US08802225B2 | 2014-08-12 | Brian K. Flandermeyer; Kathleen E. Sinnamon; Erica Prevost |
| An article includes a ceramic matrix composite substrate with a heat-exposure surface and a monocoating disposed directly on the heat-exposure surface. The monocoating includes vitreous glass to seal the ceramic matrix composite from the surrounding environment. | ||||||
| 225 | Method of assembling a gas turbine engine | US13367750 | 2012-02-07 | US08769816B2 | 2014-07-08 | Alexander R. Beeck |
| A method of assembling a seal in a horizontal split plane gas turbine engine including providing a rotor assembly including a turbine blade assembly defining a forward face and a seal ring extending axially from the forward face. The rotor assembly is positioned extending through a lower compressor casing and a lower turbine casing, the positioning including tilting the rotor assembly at an angle relative to the longitudinal axis for the engine. An upper turbine casing is positioned over the tilted rotor assembly, and the upper and lower turbine casings define a circumferentially extending seal groove. The rotor assembly is moved in an axially forward direction to position the seal ring in axially overlapping relation within the seal groove. The longitudinal axis of the rotor assembly is then aligned with the longitudinal axis of the turbine engine to further position the seal ring within the seal groove. | ||||||
| 226 | TURBINE PURGE FLOW CONTROL SYSTEM AND RELATED METHOD OF OPERATION | US13838037 | 2013-03-15 | US20140169938A1 | 2014-06-19 | Robert Joseph Reed; Kevin Thomas McGovern |
| A system configured to precisely control and/or modulate purge flow in a power plant system (e.g., a gas turbine) during operation is disclosed. In one embodiment, a system includes: at least one computing device adapted to control a purge flow in a gas turbine by performing actions comprising: obtaining operational data from the gas turbine; determining an inferred gas path pressure value for the gas turbine; determining an allowable purge flow for the gas turbine as a function of the operational data and the inferred gas path pressure value; and adjusting the purge flow based upon the allowable purge flow determination. | ||||||
| 227 | APPARATUS AND METHOD FOR MEASURING GAS FLOW THROUGH A ROTARY SEAL | US14072252 | 2013-11-05 | US20140133963A1 | 2014-05-15 | Colin BIRD |
| A method of measuring a flow rate of a first fluid through a rotary seal of a gas turbine engine comprising controlling a probe flow of a second fluid at an intra-seal cavity and measuring a pressure change in the first fluid caused by the probe flow. | ||||||
| 228 | Thermal Barrier Coating with Lower Thermal Conductivity | US14029104 | 2013-09-17 | US20140017477A1 | 2014-01-16 | Joel Larose |
| A thermal barrier coating includes a microstructure and a composition including: a ceramic based compound comprising gadolinia and zirconia. The coating includes a nano-structure having a porosity of at most 50% by volume of the coating. | ||||||
| 229 | LADDER SEAL SYSTEM FOR GAS TURBINE ENGINES | US13485250 | 2012-05-31 | US20130323060A1 | 2013-12-05 | Kimberly Pash Boyington |
| A sealing system for a gas turbine engine includes an arcuate first ladder seal segment having a central portion, an upstream flange adjoining the central portion, a downstream flange adjoining the central portion opposite the upstream flange, and a plurality of openings. The upstream flange is arranged at an angle θU greater than 0° and less than 90° relative to a given tangential plane, and the downstream flange is arranged at an angle θD greater than 0° and less than 90° relative to the given tangential plane. | ||||||
| 230 | SHAFT SEALING DEVICE, AND ROTARY MACHINE EQUIPPED THEREWITH | US13994877 | 2011-12-20 | US20130259680A1 | 2013-10-03 | Tanehiro Shinohara; Hidekazu Uehara; Shin Nishimoto; Takashi Nakano |
| A shaft sealing device and a rotary machine equipped therewith are provided with a sealing body configured by stacking a plurality of thin sealing pieces; and a low-pressure-side side sealing plate in which a plate surface facing the low-pressure side is pressed against an inner wall surface of the housing facing the direction of the axis by means of the pressure of a fluid applied from a high-pressure side to the low-pressure side. A protrusion for blocking a downward flow toward the inside of the low-pressure-side side sealing plate in the radial direction along the low-pressure side of the sealing body is formed on the inside of the low-pressure-side side sealing plate in the radial direction, and a communication path for guiding the downward flow blocked by means of the protrusion to a low-pressure-side region is formed on the housing. | ||||||
| 231 | Windback Device for a Circumferential Seal | US13707136 | 2012-12-06 | US20130241153A1 | 2013-09-19 | Glenn M. Garrison |
| The disclosure describes a windback device for a circumferential seal within a turbine engine. The windback device includes an annular collar at one end of an annular fluid seal housing, at least one inclined thread, and a plurality of inclined baffles separately disposed along an outer circumferential surface of a rotatable runner. The housing is adapted at another end for an annular seal. The collar has an opening therethrough sized to receive the runner without contact. The annular seal surrounds and sealingly engages the runner. The threads extend from an inner face of the collar toward the runner. The baffles are separately recessed in or raised above the outer circumferential surface of the runner. The baffles are interposed between the runner and threads. Each baffle is separated from the threads via a radial clearance. Threads and baffles direct lubricant away from the annular seal. | ||||||
| 232 | THERMAL BARRIER COATING SYSTEM WITH POROUS TUNGSTEN BRONZE STRUCTURED UNDERLAYER | US13371519 | 2012-02-13 | US20130209786A1 | 2013-08-15 | David B. Allen; Anand A. Kulkarni |
| A system of layers in a protective coating (20) for a substrate (22), including at least an outer thermal barrier layer (32) and a tungsten bronze structure ceramic underlayer (30) that reduces spalling of the outer layer. The range of materials for the underlayer includes ceramics of the form Ba6−3mRe8+2mTi18O54, where 0 | ||||||
| 233 | Cross flange seal for a pressure vessel, especially for a turbomachine casing | US11822848 | 2007-07-10 | US08439220B2 | 2013-05-14 | Darran-Lee Norman; Mladen Matan |
| The invention relates to a pressure vessel for a machine, especially a turbomachine, which comprises at least 3 casing shell sections, wherein the intersection region of the parting joints is sealed off by a plug which in its interior has a system of holes and passages through which a sealing compound is pressed into the region between plug and casing shell sections, so that after its setting, an elastic, leakproof and non-destructively disassemblable sealing of the intersection region of the parting joints is created. The plug can be fastened on the casing shell sections by means of an integrated flange. | ||||||
| 234 | METHOD OF REPAIRING ROTATING MACHINE COMPONENTS | US13629105 | 2012-09-27 | US20130082446A1 | 2013-04-04 | Mark Dean Pezzutti |
| An apparatus and a method for repairing a component of a gas turbine engine is provided. The method includes locating a damaged area of the component, preparing a portion of the component that includes the damaged area leaving a remaining portion of the component, welding at least one layer of material to the remaining portion, using a cold metal transfer (CMT) process, and removing excess material from the component to a predetermined dimension. | ||||||
| 235 | Spring loaded seal assembly for turbines | US12797272 | 2010-06-09 | US08398090B2 | 2013-03-19 | Kevin Weston McMahan; Mehmet Demiroglu; Timur Rustamovich Repikov |
| A spring loaded seal assembly is disclosed for sealing a gap between adjacent turbine components. The seal assembly may generally include a turbine seal and a spring member. The turbine seal may extend between the adjacent turbine components and may be configured to seal the gap defined between the turbine components. The spring member may be configured to engage the turbine seal so as to maintain the seal in sealing engagement with the adjacent turbine components. | ||||||
| 236 | SEAL GAS MONITORING AND CONTROL SYSTEM | US13564374 | 2012-08-01 | US20130031960A1 | 2013-02-07 | Joe Delrahim; Paul A. Hosking |
| A monitoring and control system for a seal gas supply system for a non-contacting gas seal. The supply includes several gas conditioning elements or units. The monitoring and control system includes an evanescent wave sensor to sense the presence of liquid in the seal gas. Multiple sensors to sense the temperature and pressure of the treated seal gas are disposed at the outlet of the conditioning elements. A programmable logic device is provided with information regarding the phase of the gas at various pressures and temperatures and compares the sensed data to the baseline data. Recognition of liquid concentrate results in an output signal. | ||||||
| 237 | Transversal conduction lightning protection system | US12491520 | 2009-06-25 | US08342805B2 | 2013-01-01 | Yaru Najem Mendez Hernandez; Robert Roesner |
| A lightning protection system for a wind turbine blade or aircraft wing includes a glass-reinforced fiber or carbon-reinforced wind turbine blade or aircraft wing having a tip region, a suction side, a pressure side, a leading edge and a trailing edge. A substantially planar sheet of conductive or semi-conductive material is disposed internal to the blade tip region or wing tip region and between the suction side and pressure side. The sheet operates during a lightning discharge to form an electric field control mechanism causing the lightning discharge to attach to the tip region. The sheet is in electrical communication or galvanic connection with a conductive or semi-conductive path such that the electric field control mechanism and the path together operate to protect the wind turbine blade or aircraft wing from damage caused by the lightning strike in the tip region of the wind turbine blade or aircraft wing by controlling an electric field in the tip region caused by the lightning strike. | ||||||
| 238 | Shaft Seal for Steam Turbines | US13525688 | 2012-06-18 | US20120251294A1 | 2012-10-04 | Edwin Gobrecht; Achim Hammann; Dirk Knudsen; Karsten Peters; Jan Walkenhorst |
| A steam turbine with a shaft seal is provided. The shaft seal steam barrier is supplied with a slight excess pressure. In order to avoid complex additional devices necessary for liquefying the water vapor once again, a condensation chamber, which is sealed from the surrounding air as well as from the steam barrier chamber with brush seals, is provided between the steam barrier chamber and the surrounding air. The condensation chamber is constructed in such a manner that the heat, developing in the interior thereof, is discharged to the outside. | ||||||
| 239 | Turbocharger with variable nozzle having vane sealing surfaces | US12115245 | 2008-05-05 | US08056336B2 | 2011-11-15 | Philippe Arnold; Dominique Petitjean; Anthony Ruquart; Guillaume Dupont; Denis Jeckel |
| A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) at least one step that defines sealing surfaces positioned to be substantially abutted by airfoil surfaces of the vanes in the closed position of the vanes and to be spaced from the airfoil surfaces in positions other than the closed position. This substantial abutment between the airfoil surfaces and the sealing surfaces serves to substantially prevent exhaust gas from leaking past the ends of the airfoil portions. At the same time, clearances between the nozzle ring face and the end faces of the airfoil portions can be sufficiently large to prevent binding of the vanes under all operating conditions. | ||||||
| 240 | GAS TURBINE ENGINE WITH NON-AXISYMMETRIC SURFACE CONTOURED ROTOR BLADE PLATFORM | US12753211 | 2010-04-02 | US20110243749A1 | 2011-10-06 | Thomas J. Praisner; Eric A. Grover |
| A rotor blade for a gas turbine engine includes a platform section between a root section and an airfoil section, the platform section having a non-axisymmetric surface contour. | ||||||
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