초록 ▼

Methods for repairing abradable seals of gas turbine engines include providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate; providing a first preform to restore the structural substrate; and providing a second preform to form an abradable lay

Methods for repairing abradable seals of gas turbine engines include providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate; providing a first preform to restore the structural substrate; and providing a second preform to form an abradable layer of the component. Preforms include a multilayer stack having a first layer and a second layer.

대표청구항 ▼

1. A method for repairing an abradable seal of a gas turbine engine comprising: providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate; andusing a preform made of first structural material and a second abradable material to simultaneously rest

1. A method for repairing an abradable seal of a gas turbine engine comprising: providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate; andusing a preform made of first structural material and a second abradable material to simultaneously restore the structural substrate and form an abradable layer of the component. 2. The method of claim 1, wherein, in using the preform, the preform and the abradable seal component are subjected to a brazing process. 3. The method of claim 2, wherein the preform comprises a multilayer stack having a first layer and a second layer; the first layer being operative to bond the multilayer stack to the structural substrate, the first layer comprising structural material corresponding to material of the structural substrate and braze material compatible with the structural material;the second layer comprising abradable material operative to form a replacement abradable layer. 4. The method of claim 3, further comprising forming the preform. 5. The method of claim 3, wherein the structural material of the first layer comprises cobalt. 6. The method of claim 3, wherein: wherein the structural material of the first layer comprises a cobalt alloy; andthe braze material of the first layer comprises a cobalt-based, silicon-depressed braze alloy. 7. The method of claim 6, wherein the first layer comprises a cobalt- based, silicon-depressed braze alloy. 8. A method for repairing an abradable seal of a gas turbine engine comprising: providing an abradable seal component of a gas turbine engine, the seal component having a structural substrate;providing a first preform to restore the structural substrate;providing a second preform to form an abradable layer of the component andbrazing the component with the first preform and the second preform such that the first preform restores the structural substrate and the second preform forms the abradable layer wherein, during the brazing, the first preform is bonded to the component during a first brazing process and the second preform is bonded to the first preform during a second brazing process.