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公开(公告)号：US09856738B2
公开(公告)日：2018-01-02
申请号：US14376428
申请日：2012-12-12
发明人： Fathi Ahmad , Nihal Kurt , Mario Nitsche , Marco Schuler , Andreas Varnholt
CPC分类号： F01D5/188 , F01D5/187 , F01D9/02 , F05D2250/185 , F05D2260/221
摘要： A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.
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公开(公告)号：US10233767B2
公开(公告)日：2019-03-19
申请号：US14900225
申请日：2014-06-10
发明人： Fathi Ahmad , Nihal Kurt , Ralf Müsgen , Eckart Schumann
摘要： A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.
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公开(公告)号：US09745852B2
公开(公告)日：2017-08-29
申请号：US14398464
申请日：2013-04-15
发明人： Fathi Ahmad , Nihal Kurt
CPC分类号： F01D5/18 , F01D5/082 , F01D5/30 , F01D5/3015 , F05B2260/201 , F05D2260/201 , Y02T50/676
摘要： A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface.
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公开(公告)号：US20160201497A1
公开(公告)日：2016-07-14
申请号：US15023391
申请日：2014-08-29
发明人： Fathi Ahmad , Michael Händler , Kevin Kampka , Christian Kowalski , Christian Kowalzik , Nihal Kurt , Stefan Schmitt , Peter Schröder
CPC分类号： F01D5/143 , F01D5/02 , F01D5/12 , F01D11/08 , F01D21/003 , F05D2220/32 , F05D2230/60 , F05D2260/30 , F05D2260/83
摘要： An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.
摘要翻译： 插入元件紧固到燃气轮机的涡轮机的环形段主体。 环形段主体在热气侧具有凹部。 插入元件被设计成覆盖凹部，并且具有凹入的前侧和后侧，其具有用于定位在环形段主体上的至少一个成形部分。 环形段具有插入元件，燃气轮机具有插入元件，并且安装方法安装插入元件。
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公开(公告)号：US10047626B2
公开(公告)日：2018-08-14
申请号：US14910035
申请日：2014-08-05
发明人： Fathi Ahmad , Michael Händler , Kevin Kampka , Christian Kowalski , Christian Kowalzik , Nihal Kurt , Stefan Schmitt , Peter Schröder
摘要： A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.
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公开(公告)号：US20150167476A1
公开(公告)日：2015-06-18
申请号：US14413357
申请日：2013-06-11
发明人： Fathi Ahmad , Nihal Kurt
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2230/21
摘要： A turbine rotor blade for a gas turbine, including a blade root and an adjoining aerodynamically curved airfoil which has a suction-side lateral wall and a pressure-side lateral wall is provided herein. These lateral walls extend in the chord direction from a common leading edge to a trailing edge and in a span direction having a total span from a blade root end to a blade tip end, a coolant duct for guiding a coolant being provided in the airfoil. In order to provide a sufficiently coolable turbine rotor blade of a comparatively small profile thickness, the airfoil, starting from its blade root end, is devoid of cooling ducts as of a span of 75% of the total span, preferably 60% of the total span.
摘要翻译： 本文提供了一种用于燃气轮机的涡轮转子叶片，其包括叶片根部和相邻的空气动力学弯曲的翼型件，其具有吸力侧侧壁和压力侧侧壁。 这些侧壁从翼形方向从共同的前缘延伸到后缘，并且跨度方向具有从叶片根端至叶片末端的总跨度，用于引导设置在翼型中的冷却剂的冷却剂导管。 为了提供具有相对小的轮廓厚度的足够冷却的涡轮转子叶片，从其叶片根端开始的翼型没有冷却管道，跨度为总跨度的75％，优选为总跨度的60％ 跨度。
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公开(公告)号：US20140377058A1
公开(公告)日：2014-12-25
申请号：US14376428
申请日：2012-12-12
发明人： Fathi Ahmad , Nihal Kurt , Mario Nitsche , Marco Schuler , Andreas Varnholt
CPC分类号： F01D5/188 , F01D5/187 , F01D9/02 , F05D2250/185 , F05D2260/221
摘要： A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant.
摘要翻译： 本发明提供一种具有空气动力学弯曲叶片翼型的涡轮引导叶片，其具有配备有节流元件的通道系统。 通道系统包括用于引导冷却液的通道部分。 为了提供替代的涡轮引导叶片，通过该涡轮导向叶片可以调节在内部流动的部分冷却剂流和从涡轮引导叶引出的局部冷却剂流; 因此，在一个实施例中，节流元件被设计用于去除冷却剂。
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公开(公告)号：US10287892B2
公开(公告)日：2019-05-14
申请号：US15509625
申请日：2015-08-27
摘要： A turbine blade having an internally cooled turbine blade airfoil in which a hollow space is divided by rib elements into at least one cooling duct carrying a coolant, wherein in at least one of the rib elements a separating tear initiating device for producing a separating tear is disposed, which extends at least partially in the longitudinal direction of the at least one rib element.
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公开(公告)号：US10018051B2
公开(公告)日：2018-07-10
申请号：US15023391
申请日：2014-08-29
发明人： Fathi Ahmad , Michael Händler , Kevin Kampka , Christian Kowalski , Christian Kowalzik , Nihal Kurt , Stefan Schmitt , Peter Schröder
CPC分类号： F01D5/143 , F01D5/02 , F01D5/12 , F01D11/08 , F01D21/003 , F05D2220/32 , F05D2230/60 , F05D2260/30 , F05D2260/83
摘要： An insert element fastens to an annular segment body of a turbine of a gas turbine. The annular segment body has a recess on a hot-gas side. The insert element is designed to cover the recess and has a concave front side and a rear side having at least one shaped portion for positioning on the annular segment body. An annular segment has the insert element, a gas turbine has the insert element, and a mounting method mounts the insert element.
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公开(公告)号：US20180156046A1
公开(公告)日：2018-06-07
申请号：US15575503
申请日：2016-04-27
发明人： Fathi Ahmad , Nihal Kurt , Uwe Paul , Albrecht Rieger
CPC分类号： F01D5/3007 , F01D5/14 , F01D5/147 , F05D2220/32 , F05D2230/10 , F05D2230/80 , F05D2240/20 , F05D2260/941 , Y02T50/673
摘要： A rotor blade for a gas turbine, the rotor blade having an aerofoil with a pressure side and an intake side which transition into a platform to which an attachment region is connected, the region having a fir tree spring which has a plurality of lateral toothed extensions arranged on the pressure side and the intake side, which extensions extend in an azimuthal direction. In addition, the azimuthal extent of one lateral toothed extension is reduced in an axial region of the lateral toothed extension, in which region the pressure load during operation exceeds a predefined threshold.
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