发明名称 |
VERFAHREN ZUR HERSTELLUNG EINER ZUSAMMENGESETZTEN GASTURBINENSCHAUFEL BESTEHEND AUS FUSSSTUECK, SCHAUFELBLATT UND DECKPLATTE ODER DECKBAND, WOBEI DAS SCHAUFELBLATT AUS EINER DISPERSIONSGEHAERTETEN NICKELBASIS-SUPERLEGIERUNG BESTEHT, UND NACH DIESEM VERFAHREN HERGESTELLTE ZUSAMMENGESETZTE GASTURBINENSCHAUFEL. |
摘要 |
A composite gas turbine blade consists of an airfoil (1) in an oxide-dispersion-hardened nickel-based superalloy, in the condition of longitudinally directed coarse columnar crystals, and a shroud plate (6) or a shroud and a root (7), the latter items in a non-dispersion-hardened nickel-based superalloy (cast alloy). The gas turbine blade is manufactured by casting in and casting round, using the non-dispersion-hardened superalloy mentioned, the tip end (2) and root end (3)-provided with depressions (4) and/or protrusions (5)-of the airfoil (1), after preheating the latter to a temperature of between 50 DEG and 300 DEG C. below the solidus temperature of the lowest melting phase of the airfoil material. The casting temperature for this should be a maximum of 100 DEG C. above the liquidus temperature of the highest melting phase of this non-dispersion-hardened alloy. Any melting onto the airfoil (1) and any metallurgical connection is to be avoided. It is advantageous to provide a thermally insulating, mechanically damping intermediate layer (16) of an oxide of at least one of the elements Cr, Al, Si, Ti and Zr with a thickness of 5 to 200 mu m between the airfoil (1), on the one hand, and the shroud plate (6) and the root (7), on the other. |
申请公布号 |
DE3860472(D1) |
申请公布日期 |
1990.09.27 |
申请号 |
DE19883860472 |
申请日期 |
1988.02.19 |
申请人 |
BBC BROWN BOVERI AG, BADEN, AARGAU, CH |
发明人 |
VERPOORT, DR., CLEMENS, CH-5442 FISLISBACH, CH |
分类号 |
F01D5/28;B21D53/78;B22D19/00;C22C19/05;(IPC1-7):B22D19/00 |
主分类号 |
F01D5/28 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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