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 |
|---|---|---|---|---|---|---|
| 181 | MOBILE VANE FOR A TURBINE ENGINE, COMPRISING A LUG ENGAGING IN A LOCKING NOTCH OF A ROTOR DISK | US15515195 | 2015-09-28 | US20170226875A1 | 2017-08-10 | Jean-Baptise Vincent DESFORGES; Damien Bernard QUELVEN; Maurice Guy JUDET; Ba-Phuc TANG |
| A mobile vane for a turbine engine, including a root designed to be inserted into a receiving element of a rotor disk for a turbine engine, a platform carried by the root, and a blade extending from the platform. The platform includes an upstream edge. The upstream edge includes a lug for engaging in a locking notch of the disk in such a way as to hold the vane axially in relation to the disk, according to the longitudinal direction of the receiving element. | ||||||
| 182 | Flow deflector arrangement | US14459820 | 2014-08-14 | US09726030B2 | 2017-08-08 | Oliver George Feaver; Andrew James Mullender |
| A flow deflector arrangement is used in combination with a pipe arrangement secured through a component, the flow deflector arrangement comprising: a nut to secure the pipe arrangement to the component, and a shroud for attachment to the component so as to extend at least partially around the pipe arrangement when the pipe arrangement is secured to the component by the nut. The nut has an outwardly directed flange to adopt a position spaced from the component, and the shroud defines at least one deflector surface which, when the shroud is attached to the component, extends away from the component in spaced relation to the pipe arrangement. The flange and the deflector surface cooperate in deflecting a flow of fluid flowing from the component and along the outside of the pipe arrangement such that the flow is deflected generally outwardly from the pipe arrangement with a degree of swirl. | ||||||
| 183 | APPARATUS FOR CASTING MULTIPLE COMPONENTS USING A DIRECTIONAL SOLIDIFICATION PROCESS | US15399438 | 2017-01-05 | US20170216912A1 | 2017-08-03 | Paul A. TENNANT; Kevin GOODWIN |
| An apparatus for the simultaneous casting of multiple components using a directional solidification process includes; a pouring cup arranged on a centreline, an array of moulds encircling the pouring cup and centre line, an array of feed channels extending from the pouring cup to a top end of each mould, and a heat deflector. The heat deflector comprises a wall arranged between the array of moulds and the centreline extending along the length of the moulds and in thermal contact with the moulds. | ||||||
| 184 | Leaf seal | US14317651 | 2014-06-27 | US09714711B2 | 2017-07-25 | Gervas Franceschini; David Anthony Edwards |
| A leaf seal is proposed for effecting a seal between two coaxial and relatively rotating components. The seal has an annular pack of stacked leaves, the pack being mountable to a first one of the components at root portions of the leaves and extending towards the other component such that end edges of the leaves cooperate to define a seal surface of the pack which is presented for air-riding interaction with a surface of the other component during relative rotation between the components such that, in use, a pressure drop is maintained axially across the pack. The seal surface of the pack incorporates a plurality of hydrodynamic lift-generating recesses spaced circumferentially around the pack. Each said recess extends circumferentially across a plurality of adjacent leaves in the pack, each of which leaves being spaced radially from said surface of the other component along at least part of its end edge. | ||||||
| 185 | SYSTEM FOR AN INLET GUIDE VANE SHROUD AND BAFFLE ASSEMBLY | US15336831 | 2016-10-28 | US20170191500A1 | 2017-07-06 | Marcin Jacek LOBOCKI; Wiktor Karol WARDECKI; Joseph Charles KULESA; Maciej STASZEWSKI |
| A system for an inlet guide vane shroud and baffle assembly includes a shroud. The shroud includes a first end configured to couple to an annular support member of the gas turbine engine, and a second end. The shroud also includes a distal end including an axially aft extending lip, and a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine. The shroud further includes an arcuate shroud body extending between the distal end and the second end. The shroud and baffle assembly also includes a baffle coupled to an aft side of the shroud. The baffle includes a radially outward end coupled to the aft side, a radially inward end coupled to the axially aft extending lip, and an arcuate baffle body extending there between. Both the shroud and the baffle extend circumferentially about a central axis. | ||||||
| 186 | GUIDE VANE FOR A TURBOMACHINE, GUIDE VANE CASCADE, AND METHOD FOR MANUFACTURING A GUIDE VANE OR A GUIDE VANE CASCADE | US15446241 | 2017-03-01 | US20170175756A1 | 2017-06-22 | Georg Zotz |
| A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade. | ||||||
| 187 | EXHAUST BYPASS VALVE OF MULTI-STAGE TURBOCHARGER | US14964798 | 2015-12-10 | US20170167364A1 | 2017-06-15 | Arthur Jeanson; Bassam Chammas; Jean-Luc Perrin |
| An assembly for a two-stage turbocharger can include a first turbocharger stage and a second turbocharger stage where one of the stages includes a boss that includes a bore; an exhaust bypass valve that includes an arm pivotable to orient the exhaust bypass valve in an open state and a closed state; a valve shaft disposed at least in part in the bore and operatively coupled to the exhaust bypass valve where the valve shaft includes an inner end, an outer end and an axial stop disposed between the inner end and the outer end; an outer bushing disposed at least in part in the bore and located axially along the valve shaft; and an inner bushing disposed at least in part in the bore and located axially along the valve shaft between the axial stop and a portion of the arm of the exhaust bypass valve. | ||||||
| 188 | Shaft sealing device, and rotary machine equipped therewith | US13994877 | 2011-12-20 | US09677410B2 | 2017-06-13 | 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. | ||||||
| 189 | PLASMA SPRAY PHYSICAL VAPOR DEPOSITION DEPOSITED ENVIRONMENTAL BARRIER COATING | US15343076 | 2016-11-03 | US20170130313A1 | 2017-05-11 | Matthew R. Gold; Kang N. Lee |
| A technique may include controlling, by a computing device, a vacuum pump to evacuate a vacuum chamber to high vacuum. The technique also may include controlling, by the computing device, a coating material source to provide a coating material to a plasma spray device, the coating material having a first composition including a first amount of a metal oxide and a second amount of silica. The second amount of silica may be greater than an amount of silica in a metal silicate including the first amount of metal oxide. The technique further may include controlling, by the computing device, the plasma spray device to deposit an environmental barrier coating on a substrate in the vacuum chamber using plasma spray physical vapor deposition, wherein the coating comprises the metal silicate. | ||||||
| 190 | Apparatus and method for measuring gas flow through a rotary seal | US14072252 | 2013-11-05 | US09645038B2 | 2017-05-09 | 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. | ||||||
| 191 | APPARATUS AND METHOD FOR SEALING TURBINE ASSEMBLY | US15301659 | 2014-04-02 | US20170114654A1 | 2017-04-27 | Srinivas PAKKALA; Robert JAMIOLKOWSKI; Tomasz JENDRZEJEWSKI; Rohit PRUTHI |
| A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser. | ||||||
| 192 | LEAF SEAL REACH OVER SPRING WITH RETENTION MECHANISM | US14920963 | 2015-10-23 | US20170114653A1 | 2017-04-27 | Johnnattan Tennessee Ugarte; Darrell Glenn Senile; Mullahalli Venkataramaniah Srinivas; Jonathon Farmer; Hugh Quill |
| A gas turbine sealing assembly includes a first static gas turbine wall, a second static gas turbine wall, and a leaf seal having a first side and a second side. The first static gas turbine wall contacts the second side at a first position, and the second static gas turbine wall contacts the second side at a second position. A spring exerts force on the first side. The spring includes a first spring wall coupled to the first static gas turbine wall. A second spring wall extends radially outward from the first spring wall. A third spring wall extends axially away from the second spring wall. A fourth spring wall extends radially inward from the third spring wall and includes a radially inner end. The radially inner end of the fourth spring wall contacts the first side of the leaf seal between the first position and the second position. | ||||||
| 193 | FABRICATION OF GAS TURBINE ENGINE COMPONENTS USING MULTIPLE PROCESSING STEPS | US14921023 | 2015-10-23 | US20170114649A1 | 2017-04-27 | Michael J. Verrilli; Mark Eugene Noe; Mark Willard Marusko; Paul Izon; Robert Tyler; Christopher Hasse |
| Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly. | ||||||
| 194 | Internally cooled seal runner | US13917075 | 2013-06-13 | US09631508B2 | 2017-04-25 | Daniel Blais; Alain Lewis; Alain C. Martel |
| A contact seal assembly for a shaft of a gas turbine engine includes a seal runner adapted to be connected to the shaft and rotatable relative to a carbon ring. The seal runner includes concentric inner and outer annular portions radially spaced apart to define at least one internal fluid passage between the inner and outer annular portions of the seal runner. | ||||||
| 195 | Turbine abradable layer with composite non-inflected bi-angle ridges and grooves | US15119061 | 2015-02-18 | US09631506B2 | 2017-04-25 | Ching-Pang Lee; Erik Johnson; Steven Koester, Jr. |
| Turbine and compressor casing abradable component embodiments for turbine engines, with composite, non-inflected, bi-angle, “hockey stick” like pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments the grooves are split or divided into multiple sections to interrupt flow traveling inside the groove and cause a local pressurization that reduces tip leakage flow. Some ridge or rib embodiments also have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. | ||||||
| 196 | Turbine, manufacturing method thereof, and power generating system | US13921525 | 2013-06-19 | US09598969B2 | 2017-03-21 | Kunihiko Wada; Satoru Kuboya; Daizo Saito; Hideyuki Maeda; Nobuhiro Okizono; Iwataro Sato; Kazutaka Tsuruta; Naoyuki Okamura |
| A turbine according to an embodiment includes: a formation object member; a facing member; and a seal part. A formation object member is one of a static part and a rotation part. A facing member is the other of the static part and the rotation part. A seal part at the formation object member is configured to reduce combustion gas leaking between the formation object member and the facing member. The seal part including a ceramics layer. The ceramics layer has a heat conductivity lower than that of the formation object member, and has a concave and convex shape at a surface thereof. The ceramics layer is not in contact with the facing member, or has hardness higher than that of the facing member so that the facing member is preferentially abraded when the facing member and the ceramics layer are in contact with each other. | ||||||
| 197 | Turbine Exhaust Housing | US15168157 | 2016-05-30 | US20160348524A1 | 2016-12-01 | Arnaud Gerard; Aurelien Tingaud; Shankar Pandurangasa Solanki; Mohan Javvadi |
| A turbine assembly can include a turbine wheel, a shroud component, a turbine housing and a seal that includes a wall and a lower lip that that extends radially outwardly from the wall where the seal is disposed, at least in part, between an outer surface of the shroud component and an inner surface of the turbine housing and where the lower lip is in contact with the turbine housing. | ||||||
| 198 | Diffuser seal for geared turbofan or turboprop engines | US13409758 | 2012-03-01 | US09447695B2 | 2016-09-20 | Paul W. Baumann; Charles H. Warner; Brian Ellis Clouse |
| A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event. | ||||||
| 199 | Gas turbine | US14584811 | 2014-12-29 | US09416676B2 | 2016-08-16 | Walter Gieg; Petra Kufner; Rudolf Stanka |
| The present invention relates to a gas turbine having a housing (1), an outer sealing ring (2) that can be fastened detachably to the housing, a clamping member (3) for clamping the outer sealing ring and the housing together radially, and a rotation locking member that has at least one housing groove (10) and a radial flange (20) of the outer sealing ring that can be locked against rotation in the housing groove in form-fitting manner with play (sa) in the axial and/or peripheral direction. | ||||||
| 200 | Turbine generator | US14531240 | 2014-11-03 | US09376929B2 | 2016-06-28 | Tatsumi Inomata; Kaoru Kaneko |
| A turbine generator includes a bearing device configured to rotatably support a rotor inside a housing. The bearing device separates an internal space of the housing from its outside. Communicating portions are formed in the bearing device. The communicating portions are formed in regions which are out of contact with lubricant. Each communicating portion establishes communication between the internal space of the housing and its outside. | ||||||
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