Patent ID: 7438523
Filing Date: 2008-10-21
Classification: B23P,F01D,F05D,Y02T,Y10T

Abstract:
1. A blade or vane of a turbomachine having a blade or vane profile made from a titanium alloy, comprising: a first shell-like titanium alloy component piece delimited by a first contact surface and a second shell-like titanium alloy component piece delimited by a second contact surface, the first piece bonded to the second piece by a high-pressure and high-temperature joint to form a joining region between the first and second component pieces; a groove that runs in a longitudinal direction of the blade or vane and is arranged at the joining region between a first inner side of the first component piece and the first contact surface, such that the groove on one side of the first component piece adjoins the first contact surface and on the other side of the first component piece adjoins the first inner side, and only the first contact surface is bonded to the second component piece; and a joining angle of greater than 70° formed between the groove and the first and second contact surfaces wherein the groove runs along the entire joining region, wherein the groove has a groove depth which varies along the groove direction wherein the first component piece and the second component piece, in the joining region, form a common wall thickness which varies along the joining region, the groove depth becoming deeper as the wall thickness increases.