Corrosion-resistant turbine blades and method for producing them

• US 4,036,601 A
• Filed: 03/26/1975
• Issued: 07/19/1977
• Est. Priority Date: 03/26/1974
• Status: Expired due to Term

• Current Assignee: Gesellschaft Fur Kernforschung mbH
• Original Assignee: Gesellschaft FUER Kernforschung
• Inventors: Bauer, Franz, Weimar, Peter
• Primary Examiner(s): Rutledge, L. Dewayne
• Assistant Examiner(s): Weise, E. L.
• Application Number:
  US05/562,158
• Time in Patent Office: 846 Days
• Field of Search: 29/198, 29/194, 29/191, 29/191.4
• US Class Current: 428/663
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: Y10T 428/12826 Group VIB metal-base component
• CPC Class Codes: Y10T 428/12986 Adjacent functionally defined components

Abstract

A turbine blade includes a core made of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto the core. The cover forms a gas-tight metallurgical bond with the core and has great strength, high ductility and a uniform layer thickness. The process includes the steps of preshaping a core of highly heat-resistant material and fitting the preshaped core into a substantially preshaped, corrosion-resistant and highly heat-resistant cover. The cover is welded to the core at a point which during later use is subjected only to little stress to form a vacuum-tight seal and workpiece. The workpiece is heated in a pressure vessel to a temperature of at least 1000° C, and the cover of the heated workpiece is heat-welded to the core by isotactic hot-pressing without the formation of pores.

Claims

1. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the core is made of a molybdenum-rhenium alloy having a rhenium content of from 30 to 50 weight percent, the remainder molybdenum, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

2. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the core is made of a niobium-molybdenum alloy having a molybdenum content of 5 to 20 percent by weight, the remainder niobium, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

3. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the core is made of a niobium-tungsten alloy having a tungsten content of from 5 to 10 percent by weight, the remainder niobium, and the protective cover is made from a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

4. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the core is made of a vanadium-titanium-niobium alloy having a titanium content of from 1 to 10 percent by weight, a niobium content of from 5 to 20 percent by weight, the remainder vanadium, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

5. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the core is made of a vanadium-titanium-silicon alloy of the formula V-3Ti-1Si and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and a resistance to oxidation in air at temperatures of about 1200°

C.

6. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the core is made of an alloy consisting essentially of Mo-Ti-Zr, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

7. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the core is made of an alloy consisting essentially of Ta-8W-HfC, and the protective cover is made of metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

8. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the alloy consists essentially of W-3Re-2ThO₂, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

9. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the alloy consists essentially of Co-27Cr-5Mo, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

10. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the alloy consists essentially of Co-22Cr-10W-9Ta, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

11. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the alloy consists essentially of Ni-15Cr-7Fe-2.5Ti, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.

12. Turbine blade comprising a core of a highly heat-resistant alloy and a highly heat-resistant, nonporous, corrosion-resistant, metallic protective cover fitted onto said core and forming a gas-tight metallurgical bond therewith, said protective cover having great strength, high ductility and a uniform layer thickness, wherein the alloy consists essentially of Ni-19Cr-18Fe-5Nb-3Mo, and the protective cover is made of a metal selected from the group consisting of rhenium, rhodium, iridium, and platinum, said metal having a high melting point and being resistant to oxidation in air at temperatures of about 1200°

C.