公开(公告)号：US09920644B2

公开(公告)日：2018-03-20

申请号：US14767341

申请日：2014-01-23

申请人： Siemens Aktiengesellschaft

发明人： Mike McKenna

IPC分类号： F01D9/04 ,  F01D11/00 ,  F01D11/02 ,  F01D5/12

CPC分类号： F01D11/008 ,  F01D5/12 ,  F01D9/041 ,  F01D11/005 ,  F01D11/006 ,  F01D11/02 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2240/80 ,  F05D2250/294 ,  F05D2250/611

摘要： A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto. The first surface is opposite the second surface, together defining boundaries of a fluid passage for the leakage flow. The first surface has a first surface riffle. A turbomachine has a seal described above, wherein the turbomachine is a gas turbine engine. A method of manufacturing a first component of a turbomachine with a reduced leakage flow between the first component and a second component of the turbomachine includes fabrication of a first surface riffle, in particular by grinding and/or by electrical discharge machining.

公开(公告)号：US10024182B2

公开(公告)日：2018-07-17

申请号：US14773346

申请日：2014-01-24

申请人： Siemens Aktiengesellschaft

发明人： Paul Jenkinson ,  Mike McKenna

IPC分类号： F03B11/00 ,  F01D9/06 ,  F23R3/00 ,  F01D5/14 ,  F01D5/28 ,  B32B15/04 ,  B32B3/26 ,  F01D25/12 ,  F01D11/24

CPC分类号： F01D9/065 ,  B32B3/266 ,  B32B15/04 ,  B32B2307/714 ,  B32B2603/00 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F01D11/24 ,  F01D25/12 ,  F05D2240/81 ,  F05D2260/204 ,  F23R3/002 ,  F23R3/005

摘要： A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.

公开(公告)号：US20160017740A1

公开(公告)日：2016-01-21

申请号：US14767341

申请日：2014-01-23

申请人： Siemens Aktiengesellschaft

发明人： Mike McKenna

IPC分类号： F01D11/00 ,  F01D9/04 ,  F01D5/12

CPC分类号： F01D11/008 ,  F01D5/12 ,  F01D9/041 ,  F01D11/005 ,  F01D11/006 ,  F01D11/02 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2240/80 ,  F05D2250/294 ,  F05D2250/611

摘要： A seal of a turbomachine reduces a leakage flow between a first and second component of the turbomachine. The first component has a first surface and the second component has a second surface, wherein the first component is stiff with regard to a first force exerted perpendicularly thereto and the second component is stiff with regard to a second force exerted perpendicularly thereto. The first surface is opposite the second surface, together defining boundaries of a fluid passage for the leakage flow. The first surface has a first surface riffle. A turbomachine has a seal described above, wherein the turbomachine is a gas turbine engine. A method of manufacturing a first component of a turbomachine with a reduced leakage flow between the first component and a second component of the turbomachine includes fabrication of a first surface riffle, in particular by grinding and/or by electrical discharge machining.

摘要翻译： 涡轮机的密封减少了涡轮机的第一和第二部件之间的泄漏流量。 所述第一部件具有第一表面，并且所述第二部件具有第二表面，其中所述第一部件相对于垂直于其施加的第一力而是刚性的，并且所述第二部件相对于垂直于其施加的第二力而是刚性的。 第一表面与第二表面相对，一起限定用于泄漏流的流体通道的边界。 第一个表面有一个第一个表面。 涡轮机具有如上所述的密封件，其中涡轮机是燃气涡轮发动机。 在第一部件和涡轮机的第二部件之间制造具有减小的泄漏流动的涡轮机的第一部件的方法包括特别是通过研磨和/或通过放电加工来制造第一表面阻挡部。

公开(公告)号：US20140314550A1

公开(公告)日：2014-10-23

申请号：US14359330

申请日：2012-10-23

申请人： Siemens Aktiengesellschaft

发明人： Paul Jenkinson ,  Mike McKenna

IPC分类号： F01D17/16

CPC分类号： F01D17/167 ,  F01D9/042 ,  F01D11/025 ,  F01D25/246 ,  F05D2230/644 ,  Y10T29/49321

摘要： The present invention relates to a stator stage (100) for a gas turbine and a method of adjusting a relative position between a vane segment (110) and a centre section (101) of the stator stage. A groove (102) is formed between a first rim (103) and a second rim (104) of a radially outer edge of the centre section, wherein the groove, the first rim and the second rim run along a circumferential direction (131). The vane segment comprises a radially inner shroud (111) from which a protrusion (112) protrudes radially inwards. The protrusion is inserted into the groove. An adjusting pin (120) comprises a first end section (121), a second end section (122) and an eccentric section (123) which runs between the first end section and the second end section. The first end section is coupled to the first rim, the second end section is coupled to the second rim and the eccentric section is coupled to the protrusion such that by pivoting the adjusting pin the relative position between the vane segment and the centre section is adjustable.

摘要翻译： 本发明涉及一种用于燃气轮机的定子级（100）和一种调节定子级的叶片段（110）和中心段（101）之间的相对位置的方法。 在中心部分的径向外边缘的第一边缘（103）和第二边缘（104）之间形成有凹槽（102），其中，所述凹槽，所述第一边缘和所述第二边缘沿圆周方向（131）延伸， 。 叶片节段包括径向内部护罩（111），突出物（112）从该内部径向向内突出。 突起插入槽中。 调节销（120）包括在第一端部和第二端部之间延伸的第一端部（121），第二端部（122）和偏心部（123）。 第一端部联接到第一边缘，第二端部联接到第二边缘，并且偏心部分联接到突起，使得通过枢转调节销，叶片段和中心部分之间的相对位置是可调节的 。

公开(公告)号：US20160017736A1

公开(公告)日：2016-01-21

申请号：US14773346

申请日：2014-01-24

申请人： SIEMENS AKTIENGESELLSCHAFT

发明人： Paul Jenkinson ,  Mike McKenna

IPC分类号： F01D9/06 ,  F01D25/12 ,  F23R3/00 ,  B32B3/26

CPC分类号： F01D9/065 ,  B32B3/266 ,  B32B15/04 ,  B32B2307/714 ,  B32B2603/00 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F01D11/24 ,  F01D25/12 ,  F05D2240/81 ,  F05D2260/204 ,  F23R3/002 ,  F23R3/005

摘要： A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.

摘要翻译： 一种燃气轮机部件用层压片材，其特征在于，所述层叠片材具有第一覆盖层，第二覆盖层和第一中间层，其中，第一覆盖层，第二覆盖层和第一中间层在每个顶层 其他。 第一中间层位于第一覆盖层和第二覆盖层之间。 第一中间层具有至少一个第一细长通孔，其中冷却流体可流过第一细长通孔。

公开(公告)号：US20160108737A1

公开(公告)日：2016-04-21

申请号：US14889701

申请日：2014-04-04

申请人： SIEMENS AKTIENGESELLSCHAFT

发明人： Stephen Batt ,  Mike McKenna

IPC分类号： F01D5/16 ,  F01D5/14

CPC分类号： F01D5/16 ,  F01D5/147 ,  F01D5/225 ,  F01D5/24 ,  F01D11/006 ,  Y02T50/673

摘要： A blade system for a gas turbine has a blade device and a further blade device. The blade device has a shroud, an airfoil extending from the shroud along the radial direction, the shroud has at a circumferential end a wedge face having a recess extending with a component along the axial direction, and a damping wire arranged within the recess such that the damping wire is adapted for contacting the shroud and a further wedge face of a further shroud of a further blade device arranged adjacent to the shroud along the circumferential direction. The recess includes an inclining side surface which has a normal, non-parallel with the radial direction, the further wedge face has a plane surface onto which the damping wire is abuttable. A method of manufacturing a blade system includes arranging the further shroud adjacent to the shroud and arranging a damping wire within the recess.

摘要翻译： 用于燃气轮机的叶片系统具有刀片装置和另外的刀片装置。 叶片装置具有护罩，沿着径向方向从护罩延伸的翼型件，护罩在周向端具有楔形面，楔形面具有沿着轴向方向与部件延伸的凹部，以及设置在凹部内的阻尼丝，使得 所述阻尼线适于接触所述护罩和沿着所述圆周方向布置成与所述护罩相邻布置的另外的刀片装置的另一护罩的另一楔形面。 所述凹部包括倾斜侧表面，所述倾斜侧表面具有法向的，与所述径向方向不平行的，所述另外的楔面具有平面，所述阻尼丝可抵靠在该平面上。 制造叶片系统的方法包括将另外的护罩布置在护罩附近并在凹槽内布置阻尼丝。