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公开(公告)号：US20150159490A1
公开(公告)日：2015-06-11
申请号：US14625734
申请日：2015-02-19
Applicant: ALSTOM Technology Ltd
Inventor： Joerg KRUECKELS , Brian Kenneth Wardle , Herbert Brandl , Marc Widmer
CPC classification number: F01D5/189 , B22C9/24 , F01D5/186 , F01D9/02 , F05D2260/201 , F05D2260/202
Abstract: The invention refers to an internally cooled casted airfoil for a rotary machine, preferably a gas turbine engine comprising a suction and a pressure side wall each extending in an axial direction, i.e. from a leading to a trailing edge region of said airfoil. At least one suction wall sided cooling channel extends in axial direction confined by the suction side wall and a first inner wall. At least one pressure wall sided cooling channel extends in axial direction confined by the pressure side wall and a second inner wall. At least one feed chamber is defined between the first and second inner wall for feeding said at least one suction and pressure sided cooling channel each by at least one through hole inside of the first and second inner wall. At least one suction wall sided cooling channel and the at least one pressure wall sided cooling channel extend into the trailing edge region separately. At least one suction wall sided cooling channel and at least one pressure wall sided cooling channel join before discharging at the trailing edge.
Abstract translation: 本发明涉及一种用于旋转机器的内部冷却铸造翼型件，优选地是包括抽吸和压力侧壁的燃气涡轮发动机，其各自在轴向方向上延伸，即从所述翼型的导向到后缘区域延伸。 至少一个抽吸壁侧冷却通道在被吸入侧壁和第一内壁限制的轴向方向上延伸。 至少一个压力壁侧冷却通道在受压侧壁和第二内壁限制的轴向方向上延伸。 至少一个进料室限定在第一和第二内壁之间，用于将第一和第二内壁内的至少一个通孔各自供给至少一个吸入和压力侧冷却通道。 至少一个抽吸壁侧冷却通道和至少一个压力壁侧冷却通道分别延伸到后缘区域。 至少一个抽吸壁侧冷却通道和至少一个压力壁侧冷却通道在后缘排放之前连接。
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公开(公告)号：US20140197601A1
公开(公告)日：2014-07-17
申请号：US14154487
申请日：2014-01-14
Applicant: ALSTOM Technology Ltd
Inventor： Paul MARLOW , Selma Zahirovic , Robert Marmilic , Marc Widmer , Joerg Krückels
IPC: F01D11/04
CPC classification number: F01D11/04 , F01D11/005 , F01D11/02 , F01D25/12 , F05D2240/121 , F05D2240/127 , F16J15/40 , F16J15/44 , F16J15/443
Abstract: The invention refers to an arrangement for sealing an open cavity against hot gas entrainment. The open cavity is arranged between two axially adjacent stationary components limiting radially a hot gas path of a rotary flow machine, of which at least the downstream component carries at least one airfoil extending radially into said hot gas path. A multitude of air jets is directed into the open cavity such that hot gas flowing over the open cavity is prevented from penetrating into the open cavity completely. The invention has an arrangement of supply conduits for air jets which are directed into the open cavity with a jet momentum such that hot gas is induced not to enter the open cavity and forming at least one hot gas vortex close to the hot gas path within the open cavity and preventing hot gas from penetrating into the open cavity beyond the extension of the hot gas vortex.
Abstract translation: 本发明涉及一种用于密封开放空腔以抵抗热气体夹带的装置。 敞开的空腔布置在两个轴向相邻的固定部件之间径向限制旋转流动机器的热气体通道，其中至少下游部件承载至少一个径向延伸到所述热气体通道中的翼型件。 多个空气射流被引导到开放空腔中，使得流过开放空腔的热气体被完全渗透到开口腔中。 本发明具有用于空气射流的供应管道的布置，其以射流动量被引导到开放空腔中，使得热气体被引入不进入开放空腔并且形成靠近该热气体路径内的至少一个热气体涡流 开放的腔体，防止热气体渗入热空气涡流延伸的开放空腔内。
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公开(公告)号：US20150267549A1
公开(公告)日：2015-09-24
申请号：US14662319
申请日：2015-03-19
Applicant: ALSTOM Technology Ltd.
Inventor： Emanuele FACCHINETTI , Guillaume Wagner , Marc Henze , Joerg Krueckels , Marc Widmer
CPC classification number: F01D9/065 , F01D5/188 , F01D5/189 , F01D9/02 , F01D9/041 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/205
Abstract: The disclosure pertains to a vane comprising a platform and airfoil extending form said platform and connected to the platform by a fillet. An impingement tube is inserted into said airfoil delimiting a cooling channel between the impingement tube and the side walls. The vane further comprises a baffle structure positioned adjacent the fillet and which follows the inside contour of the fillet; delimiting a first cooling passage between the fillet and the baffle structure. A first obstruction is arranged on the inside of the airfoil at the connection of the fillet to the side walls for separating the first cooling passage from the cooling channel in the airfoil and to guide the cooling gas from the first cooling passage into the impingement tube. The disclosure further refers to a method for cooling such a vane.
Abstract translation: 本公开涉及一种叶片，其包括从所述平台延伸并且通过圆角连接到平台的平台和翼型件。 冲击管被插入到限定冲击管和侧壁之间的冷却通道的所述翼型件中。 所述叶片还包括邻近所述圆角定位并且跟随所述圆角的内部轮廓的挡板结构; 限定圆角和挡板结构之间的第一冷却通道。 在翼片与侧壁的连接处，在翼型件的内部设置第一障碍物，用于将第一冷却通道与翼型中的冷却通道分离，并将冷却气体从第一冷却通道引导到冲击管中。 本发明还涉及冷却这种叶片的方法。
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Patent Agency Ranking
公开(公告)号：US09903209B2
公开(公告)日：2018-02-27
申请号：US14574897
申请日：2014-12-18
Applicant: ALSTOM Technology Ltd
Inventor： Joerg Krueckels , Marc Widmer
CPC classification number: F01D5/187 , F01D9/02 , F05D2250/292 , F05D2260/2212 , F05D2260/22141
Abstract: The invention refers to a rotor blade or guide vane airfoil for a gas turbine engine having a longitudinal axis and a source of cooling fluid. The airfoil has a pressure wall, a suction wall, a leading edge, a trailing edge and at least one cooling fluid flow passage. The cooling fluid flow passage is in fluid communication with the source of cooling fluid. Means for directing cooling fluid at least to the trailing edge are provided, whereas the cooling fluid flow passage including: a plurality of axially extending walls, each of the walls extending laterally between the pressure wall and suction wall. The plurality of walls are radially spaced within the cooling fluid flow passage such that adjacent pairs of walls define a channel. The axial spacing between the adjacent walls include in radial direction of the airfoil a pins and a ribs structure, wherein the pins holistic or approximately cover the axial height of the channel. The ribs have a deeper level with respect to the pins and the ribs establish a bridge-like connection between each of adjacent ribs.
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公开(公告)号：US09890646B2
公开(公告)日：2018-02-13
申请号：US14625734
申请日：2015-02-19
Applicant: ALSTOM Technology Ltd
Inventor： Joerg Krueckels , Brian Kenneth Wardle , Herbert Brandl , Marc Widmer
CPC classification number: F01D5/189 , B22C9/24 , F01D5/186 , F01D9/02 , F05D2260/201 , F05D2260/202
Abstract: An internally cooled airfoil for a rotary machine, for example, a gas turbine engine includes a suction and pressure side wall each extending in an axial direction, i.e. from a leading to a trailing edge of the airfoil. A suction wall sided cooling channel and a pressure wall sided cooling channel extend in the axial direction. A feed chamber is defined between a first and second inner wall for feeding the suction wall and pressure wall sided cooling channel each by at least one through hole inside of the first and second inner wall. The suction wall sided cooling channel and the pressure wall sided cooling channel extend into the trailing edge region separately. The suction wall sided cooling channel and the pressure wall sided cooling channel join before discharging at the trailing edge.
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公开(公告)号：US20150176424A1
公开(公告)日：2015-06-25
申请号：US14574846
申请日：2014-12-18
Applicant: ALSTOM Technology Ltd.
Inventor： Carlos Simon-Delgado , Christoph Didion , Marc Widmer , Martin Schaefer , Guenter Filkorn
CPC classification number: F01D11/18 , F01D11/001 , F01D11/025 , F01D11/122 , F01D11/127 , F05D2250/283
Abstract: The invention pertains to a seal system for a passage between a turbine stator and a turbine rotor, including: a first arm extending radially outwards from the turbine rotor and toward the first seal arranged on the stator, and terminating short of the first seal thereby creating a first gap between the first seal and the first arm. The seal system further includes a second seal arranged on the turbine stator, and a second arm extending axially from the turbine rotor towards the second seal base, and terminating short of the second seal thereby creating a second gap between the second seal and the second arm. The invention further refers to a gas turbine including such a seal system.
Abstract translation: 本发明涉及一种用于在涡轮机定子和涡轮机转子之间的通道的密封系统，包括：第一臂从涡轮转子径向向外延伸并且朝向布置在定子上的第一密封件延伸，并且终止于第一密封件之外，从而产生 第一密封件和第一臂之间的第一间隙。 所述密封系统还包括布置在所述涡轮机定子上的第二密封件，以及从所述涡轮机转子朝向所述第二密封基座轴向延伸并且终止于所述第二密封件的第二臂，从而在所述第二密封件和所述第二臂之间形成第二间隙 。 本发明还涉及一种包括这种密封系统的燃气轮机。
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公开(公告)号：US09097119B2
公开(公告)日：2015-08-04
申请号：US13668274
申请日：2012-11-04
Applicant: ALSTOM Technology Ltd
Inventor： Thomas Heinz-Schwarzmaier , Marc Widmer , Selma Zahirovic , Paul Marlow
CPC classification number: F01D9/023 , F01D11/005 , F02C6/003 , F05D2240/127
Abstract: A gas turbine is provided having a secondary combustion chamber and a first guide vane row of a low-pressure turbine, the row being arranged directly downstream of the chamber. The radially outer boundary of the secondary combustion chamber is formed by at least one outer wall segment, which is secured on at least one support element arranged radially outwardly. The flow path of the hot gases is bounded radially outwardly, in the region of the guide vane row, by an outer platform which is secured at least indirectly on at least one guide vane support. A substantially radially extending gap-shaped cavity having a width in the range of 1-25 mm in the axial direction in the inlet region is arranged between the wall segment and the outer platform. At least one step element, which reduces the width by at least 10% in at least one step, extending substantially perpendicularly to the direction of flow of the hot gas in the cavity, is arranged in the inlet region.
Abstract translation: 提供一种燃气轮机，其具有二次燃烧室和低压涡轮机的第一导向叶片排，该排直接设置在室的下游。 二次燃烧室的径向外边界由至少一个外壁段形成，该外壁段固定在径向向外布置的至少一个支撑元件上。 热气体的流动路径在导向叶片排的区域中径向向外限定外部平台，该外部平台至少间接地固定在至少一个导向叶片支撑件上。 在壁部段和外部平台之间布置有在入口区域中在轴向方向上具有1-25mm范围内的宽度的大致径向延伸的间隙形腔。 在入口区域中布置有至少一个步进元件，其在基本垂直于空腔中的热气体的流动方向的至少一个步骤中将至少10％的宽度减小。
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公开(公告)号：US09074488B2
公开(公告)日：2015-07-07
申请号：US14154487
申请日：2014-01-14
Applicant: ALSTOM Technology Ltd
Inventor： Paul Marlow , Selma Zahirovic , Robert Marmilic , Marc Widmer , Joerg Krückels
CPC classification number: F01D11/04 , F01D11/005 , F01D11/02 , F01D25/12 , F05D2240/121 , F05D2240/127 , F16J15/40 , F16J15/44 , F16J15/443
Abstract: The invention refers to an arrangement for sealing an open cavity against hot gas entrainment. The open cavity is arranged between two axially adjacent stationary components limiting radially a hot gas path of a rotary flow machine, of which at least the downstream component carries at least one airfoil extending radially into said hot gas path. A multitude of air jets is directed into the open cavity such that hot gas flowing over the open cavity is prevented from penetrating into the open cavity completely. The invention has an arrangement of supply conduits for air jets which are directed into the open cavity with a jet momentum such that hot gas is induced not to enter the open cavity and forming at least one hot gas vortex close to the hot gas path within the open cavity and preventing hot gas from penetrating into the open cavity beyond the extension of the hot gas vortex.
Abstract translation: 本发明涉及一种用于密封开放空腔以抵抗热气体夹带的装置。 敞开的空腔布置在两个轴向相邻的固定部件之间径向限制旋转流动机器的热气体通道，其中至少下游部件承载至少一个径向延伸到所述热气体通道中的翼型件。 多个空气射流被引导到开放空腔中，使得流过开放空腔的热气体被完全渗透到开口腔中。 本发明具有用于空气射流的供应管道的布置，其以射流动量被引导到开放空腔中，使得热气体被引入不进入开放空腔并且形成靠近该热气体路径内的至少一个热气体涡流 开放的腔体，防止热气体渗入热空气涡流延伸的开放腔内。
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