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公开(公告)号：US09850769B2
公开(公告)日：2017-12-26
申请号：US15383524
申请日：2016-12-19
发明人： Harald Steiner , Yulia Smirnova
CPC分类号： F01D11/003 , F01D11/005 , F02C7/28 , F05D2220/32 , F05D2240/57 , F05D2250/184 , F05D2250/294 , F16J15/0887 , F23R3/002 , F23R3/60 , F23R2900/00012
摘要： A hula seal as disclosed extends in a circumferential direction, a radial direction and an axial direction relative to a central axis.The hula seal includes a first leaf extending from the first edge region to the second edge region and a second leaf extending from the first edge region to the second edge region. The first leaf is the same distance as the second leaf from the central axis in the radial direction, and is adjacent to and overlaps the second leaf in the circumferential direction, when installed in a gas turbine. The first leaf is attached to the second leaf such that the first leaf can move relative to the second leaf in the circumferential direction when installed in a gas turbine.
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公开(公告)号：US09803863B2
公开(公告)日：2017-10-31
申请号：US14711628
申请日：2015-05-13
CPC分类号： F23R3/002 , F23R3/045 , F23R3/06 , F23R3/50 , F23R2900/00012 , F23R2900/00014
摘要： A grommet for a combustor of a gas turbine engine is disclosed. The grommet includes a lower platform and a raised platform. The lower platform includes a plurality of top slots located in the top surface and a plurality of bottom slots located in the bottom surface. Each top slot and bottom slot may extend radially along the lower platform. The plurality of top slots may be spaced equidistantly from one another along the circumference of the lower platform. The plurality of bottom slots may be spaced equidistantly from one another along the circumference of the lower platform.
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公开(公告)号：US09777925B2
公开(公告)日：2017-10-03
申请号：US14531156
申请日：2014-11-03
CPC分类号： F23R3/005 , F01D5/18 , F01D9/023 , F05B2260/20 , F23R3/002 , F23R3/04 , F23R3/06 , F23R3/44 , F23R2900/00012 , F23R2900/00018 , F23R2900/03042 , F23R2900/03043
摘要： There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions.The gas turbine combustor includes: a cylindrical combustion chamber that burns combustion air and fuel to thereby produce combustion gas; an outer casing disposed concentrically on an outside of the combustion chamber; an end cover disposed at an upstream side end portion of the outer casing; an annular passage formed by an outer peripheral surface of the combustion chamber and an inner peripheral surface of the outer casing, the annular passage allowing the combustion air to flow therethrough; and a passage formed inside a combustion chamber wall between the outer peripheral surface and an inner peripheral surface of the combustion chamber, the passage having a U-shape turned sideways and having ends disposed on an upstream side in a transverse cross-sectional view, in which the passage includes a first passage that extends in parallel with an axial direction of the combustion chamber and has a supply hole on a first end side thereof, the supply hole communicating with an outside of the combustion chamber wall, and a second passage that has a second end side communicating with a second end side of the first passage and has a jet hole on a first end side thereof, the jet hole communicating with an inside of the combustion chamber wall.
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公开(公告)号：US09759427B2
公开(公告)日：2017-09-12
申请号：US14069812
申请日：2013-11-01
CPC分类号： F23R3/60 , F01D9/023 , F02C3/04 , F02C7/28 , F05D2240/35 , F05D2240/55 , F05D2240/56 , F05D2240/57 , F05D2240/58 , F23R2900/00012
摘要： An interface assembly for a combustor includes an interface housing having a channel defined by a forward wall and at least one aft wall segment, the aft wall segment operatively coupled to an aft flange of a flow sleeve. Also included is a piston ring fittingly disposed in the channel.
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公开(公告)号：US20170184306A1
公开(公告)日：2017-06-29
申请号：US14982642
申请日：2015-12-29
CPC分类号： F23R3/005 , F23R3/002 , F23R3/06 , F23R3/26 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018 , F23R2900/03043
摘要： A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.
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公开(公告)号：US20170176010A1
公开(公告)日：2017-06-22
申请号：US14971339
申请日：2015-12-16
申请人： Delavan Inc
CPC分类号： F23R3/283 , F02C7/222 , F05D2220/32 , F05D2230/237 , F05D2230/30 , F05D2250/281 , F23R2900/00012
摘要： An injector includes a feed arm extending from an inlet fitting to a nozzle body opposite the inlet fitting. The nozzle body includes a spray outlet in fluid communication with the inlet fitting for issuing a spray of fluid supplied at the inlet fitting. The inlet fitting of the feed arm includes a receptacle therein for receiving a fluid supply manifold inside the inlet fitting of the feed arm.
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公开(公告)号：US09605550B2
公开(公告)日：2017-03-28
申请号：US14137409
申请日：2013-12-20
发明人： Charles Bryce Graves
IPC分类号： F23R3/00 , F16K31/00 , G05D23/27 , F02M31/07 , F23R3/26 , F01D11/00 , G05D23/185 , G05D23/275 , F16J15/16 , F16J15/08
CPC分类号： F01D11/003 , F01D11/005 , F02M31/07 , F05D2240/35 , F05D2240/57 , F05D2270/303 , F05D2270/42 , F05D2300/175 , F05D2300/505 , F05D2300/6033 , F16J15/0806 , F16J15/164 , F16K31/002 , F23M2900/05002 , F23M2900/05005 , F23R3/002 , F23R3/007 , F23R3/26 , F23R2900/00012 , G05D23/1854 , G05D23/2754 , Y02T10/126 , Y02T50/672 , Y10T137/7737 , Y10T137/7847
摘要： An improved seal assembly for use with a combustion liner assembly is employed with a gas turbine engine so as to control fluid flow. The seal assembly has a bi-metal sealing member that is affixed to a first surface that is proximal to a second perpendicular surface that is not in contact with the first surface, thus providing a potential fluid flow path. Upon heating, the bi-metal sealing member “uncoils” contacting the second perpendicular surface, thus blocking the flowpath between the two surfaces. Various metals may be provided to provide predetermined sealing characteristics.
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公开(公告)号：US20170082030A1
公开(公告)日：2017-03-23
申请号：US15371138
申请日：2016-12-06
发明人： Keith Cletus Belsom
CPC分类号： F02C7/28 , F01D9/023 , F01D9/041 , F01D11/003 , F02C3/14 , F05D2220/3212 , F05D2240/55 , F23R3/46 , F23R3/60 , F23R2900/00012
摘要： A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas turbine and the plurality of turbine combustors. The first seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors. The gas turbine engine also includes a second seal disposed between the gas turbine and the plurality of turbine combustors. The second seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors.
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89.发明申请WEAR PAD SYSTEM FOR TURBINE COMBUSTION SYSTEMS AND METHOD FOR COUPLING WEAR PAD INTO TURBINE COMBUSTION SYSTEM 审中-公开用于涡轮机燃烧系统的磨损系统和用于将磨损垫片连接到涡轮机燃烧系统中的方法公开(公告)号：US20170059158A1
公开(公告)日：2017-03-02
申请号：US14833388
申请日：2015-08-24
CPC分类号： F23R3/002 , B23P15/00 , B23P2700/13 , F01D9/023 , F23R3/46 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , F23R2900/03044
摘要： An aspect of the invention provides for a wear pad system for a turbine combustion system including a transition piece (TP) forward ring, an impingement sleeve substantially surrounding the TP forward ring, and a gap between the TP forward ring and the impingement sleeve, the wear pad system comprising: a wear pad extending through a hole in the impingement sleeve and through the gap to contact the TP forward ring, the wear pad having a radially outer portion and a radially inner portion, the radially outer portion in contact with a radially outer surface of the impingement sleeve and the radially inner portion in contact with a radially outer surface of the TP forward ring.
摘要翻译： 本发明的一个方面提供了一种用于涡轮机燃烧系统的磨损系统，其包括过渡件（TP）前环，基本上围绕TP前进环的冲击套筒以及TP前进环和冲击套筒之间的间隙， 磨损垫系统，包括：磨损垫，其延伸穿过冲击套筒中的孔并且穿过间隙以接触TP前进环，所述磨损垫具有径向外部部分和径向内部部分，所述径向外部部分与径向外部接触 冲击套筒的外表面和与TP前进环的径向外表面接触的径向内部。
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公开(公告)号：US20160298848A1
公开(公告)日：2016-10-13
申请号：US15077050
申请日：2016-03-22
申请人： ROLLS-ROYCE plc
发明人： Alan GEARY , Keith BELL
CPC分类号： F23R3/286 , F02C7/222 , F02C7/28 , F23R3/283 , F23R2900/00012
摘要： A fuel injector system with a fuel feed arm extending inwardly from an outer casing of combustion equipment of a gas turbine engine to a flame tube of the equipment, which ends in an injection nozzle which penetrates a head of the tube to deliver fuel. The system has a swirler arranged coaxially with the nozzle at the head of the tube, including one or more circuits which produce flows of swirling air around the fuel. A seal ring seals the nozzle to the swirler, the nozzle being removably inserted into the ring. The ring has a flange portion, and the swirler has a pair of spaced retention grooves at a front face thereof. Opposite edges of the flange portion slidingly locate in the grooves so it sealingly engages to the front face. The swirler has a spring mechanism which retains the flange portion in the grooves.
摘要翻译： 一种燃料喷射器系统，其具有从燃气涡轮发动机的燃烧设备的外壳向内延伸到设备的火焰管的燃料进给臂，燃料喷射器的末端是穿过管的头部以输送燃料的喷嘴。 该系统具有与管头处的喷嘴同轴布置的旋流器，包括一个或多个在燃料周围产生涡旋空气流的回路。 密封环将喷嘴密封到旋流器，喷嘴可拆卸地插入环中。 环具有凸缘部分，并且旋流器在其正面具有一对间隔的保持槽。 凸缘部分的相对边缘滑动地定位在凹槽中，使得其密封地接合到前表面。 旋流器具有将凸缘部分保持在凹槽中的弹簧机构。
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