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1. 发明专利

JP5511352B2 Multiple impingement complex for cooling the wall 有权
公开(公告)号：JP5511352B2
公开(公告)日：2014-06-04
申请号：JP2009283250
申请日：2009-12-14
申请人：シーメンスアクチエンゲゼルシヤフトSiemens Aktiengesellschaft
发明人：へーゼルハウスアンドレアス
IPC分类号： F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F28F3/02 , B22F7/064 , B22F7/08 , C21C5/4646 , F01D5/183 , F01D5/184 , F05D2250/185 , F23M5/00 , F23R3/002 , F23R2900/03044 , F28D2021/0078

2. 发明专利

JP4240808B2 Method for producing a turbine blade 有权
公开(公告)号：JP4240808B2
公开(公告)日：2009-03-18
申请号：JP2000517820
申请日：1998-10-27
申请人：シーメンスパワージェネレイションインコーポレイテッド
发明人：ザガー，トーマス，ウォルター , スウォーツベック，ゲーリー，ダブリュ , セス，ブリジ，ビイ , バーケ，マイケル，エイ , ハーバー，モーハン，エイ , フレヤー，ポウラ，ディー
IPC分类号： B23P15/02 , F01D5/14 , B23K20/02 , B23K20/16 , B23K35/30 , B23P15/04 , C22C19/03 , C22C19/05 , C22F1/00 , C22F1/10 , C30B11/00 , C30B29/52 , F01D5/18 , F01D5/28
CPC分类号： F01D5/28 , B23H9/10 , B23K20/023 , B23K20/16 , B23K35/3033 , B23K35/304 , B23K2201/001 , B23P15/04 , C22C19/057 , C22F1/10 , C30B11/00 , C30B29/52 , F01D5/147 , F01D5/18 , F01D5/184 , F05D2230/23 , F05D2230/40 , F05D2300/607 , Y02T50/67 , Y02T50/671 , Y02T50/673 , Y02T50/676 , Y10T428/12271 , Y10T428/12347 , Y10T428/12431 , Y10T428/12944
摘要： Large gas turbine blades made from separate cast segments of superalloys are disclosed. The turbine blade is designed such that bond lines between adjacent segments are placed in low stress regions of the blade. The cast superalloy segments of the blades are aligned and fitted together with specified tolerances. The turbine blade segments are then joined by transient liquid phase bonding, followed by a controlled heat treatment which produces the desired microstructure in the bond region. The method allows for the production of large, high quality turbine blades by joining small, high quality cast superalloy sections, in comparison with prior attempts to cast large turbine blades as single pieces which have produced very low yields and high individual component costs.

4. 发明专利

JP5252672B2 Method of cooling a device having a surface with the cooling medium and the porous member, a method of brewing cooling device, as well as the structure cools 有权
公开(公告)号：JP5252672B2
公开(公告)日：2013-07-31
申请号：JP2004213007
申请日：2004-07-21
申请人：ザ・ボーイング・カンパニーThe Boeing Company
发明人：ミクロス・ポール・ピーターバリー , ケビン・エイ・ローナー
IPC分类号： B64C1/38 , F01D5/18 , B64C3/36 , B64G1/58 , F01D25/12 , F02K1/82 , F02K9/40 , F02K9/64 , F04D29/38 , F04D29/58 , F23R3/00
CPC分类号： F01D5/184 , B64C1/38 , B64G1/401 , B64G1/58 , F01D25/12 , F02K1/825 , F02K9/64 , F02K9/972 , F05D2250/323 , F23R3/002 , F23R3/007 , F23R2900/03041 , F28D2021/0078 , F28F13/003 , F42B15/34 , Y02T50/433
摘要： System for transpiration coolong of an element in which a substantially non-porous laminate preform (40) is made porous by a pore forming member (34). Coolant (88) is then flown in an area (86) near the surface (84) between the element and the porous laminate. Part of the coolant is transported through the porous member.

5. 发明专利

JPS5728802A Rotor blade 失效
公开(公告)号：JPS5728802A
公开(公告)日：1982-02-16
申请号：JP8486481
申请日：1981-06-02
申请人： United Technologies Corp
发明人： JIYOOJI PEI RAIANGU
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/184 , Y02T50/673 , Y02T50/676

6. 发明专利

JP2014087924A Components with micro cooled coating layer and methods of manufacture 有权
标题翻译：微型冷却涂层的组成部分和制造方法
公开(公告)号：JP2014087924A
公开(公告)日：2014-05-15
申请号：JP2013220703
申请日：2013-10-24
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： BUNKER RONALD SCOTT , WEAVER SCOTT ANDREW
IPC分类号： B23P15/04 , B23H9/10 , B24C1/10 , F01D5/18 , F01D9/02 , F01D25/00 , F01D25/12 , F02C7/00 , F02C7/18
CPC分类号： F01D5/18 , B05D3/06 , B05D3/12 , C23C4/073 , C23C4/18 , C23C14/5886 , F01D5/184 , F01D5/187 , F01D5/288 , F05D2260/204 , Y02T50/672 , Y02T50/676 , Y10T428/13
摘要： PROBLEM TO BE SOLVED: To provide reduced fabrication time and simplified methods of manufacture.SOLUTION: A method includes providing a substrate with an outer surface and an interior space, applying a coating on a portion of the substrate, and forming grooves in the coating, where each groove extends at least partially along the coating. The method further includes processing at least a portion of the surface of the coating to plastically deform the coating in the vicinity of the top of each groove, and applying an additional coating over at least a portion of the surface of the coating.
摘要翻译：要解决的问题：提供缩短的制造时间和简化的制造方法。解决方案：一种方法包括提供具有外表面和内部空间的基板，在基板的一部分上施加涂层，以及在涂层中形成凹槽，其中每个凹槽至少部分地沿涂层延伸。该方法还包括处理涂层的表面的至少一部分以使涂层在每个凹槽的顶部附近塑性变形，并在涂层表面的至少一部分上施加另外的涂层。

7. 发明专利

JP4546760B2 Turbine blade with an integrated bridge 有权
公开(公告)号：JP4546760B2
公开(公告)日：2010-09-15
申请号：JP2004138380
申请日：2004-05-07
申请人：ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人：チン−パン・リー , ハーヴェイ・マイケル・マクリン , リチャード・クレイ・ハウベルト
IPC分类号： F01D5/18 , F01D5/20 , F02C7/18
CPC分类号： F01D5/20 , F01D5/184 , F01D5/186 , Y02T50/673 , Y02T50/676

8. 发明专利

JP2005030387A Turbine blade including integrated bridge 有权
标题翻译：涡轮叶片包括集成桥
公开(公告)号：JP2005030387A
公开(公告)日：2005-02-03
申请号：JP2004138380
申请日：2004-05-07
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： LEE CHING-PANG , HAUBERT RICHARD CLAY , MACLIN HARVEY MICHAEL
IPC分类号： F01D5/18 , F01D5/20 , F02C7/18
CPC分类号： F01D5/20 , F01D5/184 , F01D5/186 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To cool a turbine blade of a gas turbine engine. SOLUTION: This turbine blade 10 includes a hollow airfoil 12 integrally coupled to a dove tail 14. The airfoil 12 includes a first perforated bridge 30 forming a channel 32 in the rear of the leading edge 22 of the airfoil. A second bridge 40 is disposed at a space backward from the first bridge 30, and extended from the airfoil positive pressure side wall 18 on this side of the trailing edge 24 of the airfoil. A third bridge 44 has opposite end parts coupled to the positive pressure side wall 18 and the second bridge 40, a supply channel 46 for the leading edge channel 32 is formed with the first bridge, and a louver channel 48 extended along the second bridge backward to the distal end at the positive pressure side wall is formed with the second bridge. COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：为了冷却燃气涡轮发动机的涡轮机叶片。解决方案：该涡轮机叶片10包括一体地联接到鸽尾14的中空翼片12.翼型件12包括在翼型件的前缘22的后部形成通道32的第一穿孔桥30。第二桥40设置在距离第一桥30的后方的空间处，并且从翼型正压侧壁18在翼型的后缘24的该侧延伸。第三桥44具有联接到正压侧壁18和第二桥40的相对端部，用于前缘通道32的供应通道46形成有第一桥，并且沿着第二桥向后延伸的百叶窗通道48 在正压侧壁的远端形成有第二桥。版权所有（C）2005，JPO＆NCIPI

9. 发明专利

JP4976614B2 Coupling methods of super alloy castings 有权
公开(公告)号：JP4976614B2
公开(公告)日：2012-07-18
申请号：JP2000517821
申请日：1998-10-27
申请人：シーメンスエナジーインコーポレイテッド
发明人：ザガー，トーマス，ウォルター , スウォーツベック，ゲーリー，ダブリュ , セス，ブリジ，ビイ , バーケ，マイケル，エイ , ハーバー，モハン，エイ , フレヤー，ポウラ，ディー
IPC分类号： B23P15/02 , B23P15/04 , B23K20/02 , B23K20/16 , B23K35/30 , C22C19/03 , C22C19/05 , C22F1/00 , C22F1/10 , C30B11/00 , C30B29/52 , F01D5/14 , F01D5/18 , F01D5/28
CPC分类号： F01D5/28 , B23H9/10 , B23K20/023 , B23K20/16 , B23K35/3033 , B23K35/304 , B23K2201/001 , B23P15/04 , C22C19/057 , C22F1/10 , C30B11/00 , C30B29/52 , F01D5/147 , F01D5/18 , F01D5/184 , F05D2230/23 , F05D2230/40 , F05D2300/607 , Y02T50/67 , Y02T50/671 , Y02T50/673 , Y02T50/676 , Y10T428/12271 , Y10T428/12347 , Y10T428/12431 , Y10T428/12944
摘要： Large gas turbine blades made from separate cast segments of superalloys are disclosed. The turbine blade is designed such that bond lines between adjacent segments are placed in low stress regions of the blade. The cast superalloy segments of the blades are aligned and fitted together with specified tolerances. The turbine blade segments are then joined by transient liquid phase bonding, followed by a controlled heat treatment which produces the desired microstructure in the bond region. The method allows for the production of large, high quality turbine blades by joining small, high quality cast superalloy sections, in comparison with prior attempts to cast large turbine blades as single pieces which have produced very low yields and high individual component costs.

10. 发明专利

JP2010144722A Multilayered impingement complex for cooling wall 有权
标题翻译：用于冷却墙的多层印刷复合材料
公开(公告)号：JP2010144722A
公开(公告)日：2010-07-01
申请号：JP2009283250
申请日：2009-12-14
申请人： Siemens Ag , シーメンスアクチエンゲゼルシヤフトSiemens Aktiengesellschaft
发明人： HESELHAUS ANDREAS
IPC分类号： F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F28F3/02 , B22F7/064 , B22F7/08 , C21C5/4646 , F01D5/183 , F01D5/184 , F05D2250/185 , F23M5/00 , F23R3/002 , F23R2900/03044 , F28D2021/0078
摘要： PROBLEM TO BE SOLVED: To provide a multilayered impingement complex for cooling a wall, which generates multiple collisional cooling flows, and also to provide a method of manufacturing the multilayered impingement complex.
SOLUTION: The multilayered impingement complex has: a plurality of pinhole layers (2) each provided with a plurality of through-holes (3) dispersedly arranged over a surface thereof, the through-holes being configured as pinholes; and a plurality of web layers (6). The web layers are layered alternately with the pinhole layers (2), and each includes a plurality of webs (7). The webs are dispersedly arranged over the surface of the pinhole layer (2), and each bridges the pinhole layers. Each web (7) of one web layer (6) is aligned in a line with each web (7) of the other web layer (7), and each through-hole (3) of one pinhole layer (2) is offset with respect to a through-hole (3) of an adjacent pinhole layer (3).
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于冷却壁的多层冲击复合体，其产生多个碰撞冷却流，并且还提供制造多层冲击复合体的方法。多层冲击复合体具有多个针孔层（2），每个针孔层分别设置有多个分布在其表面上的通孔（3），该通孔被构造成针孔; 和多个网状物层（6）。纤维网层与针孔层（2）交替分层，并且每个包括多个网（7）。网分散布置在针孔层（2）的表面上，并且每个桥接针孔层。一个腹板层（6）的每个腹板（7）与另一腹板层（7）的每个腹板（7）成直线对准，并且一个针孔层（2）的每个通孔（3）与相对于相邻针孔层（3）的通孔（3）。版权所有（C）2010，JPO＆INPIT

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