Erosion-shielded turbine blades and methods of manufacturing the same
A method of manufacturing an erosion-shielded turbine blade includes providing a turbine blade for use with a rotary machine. The turbine blade includes an airfoil extending between a root and a tip. The airfoil includes a pressure side and an opposite suction side, and each of the pressure and suction sides extends between a leading edge and a trailing edge. The method also includes printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material, and sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material. The method also includes coupling the erosion shield to the leading edge of the turbine blade.
1. A method of manufacturing an erosion-shielded turbine blade, the method comprising:
providing a turbine blade for use with a rotary machine, the turbine blade including an airfoil extending between a root and a tip, the airfoil including:
a pressure side and an opposite suction side, each of the pressure and suction sides extending between a leading edge and a trailing edge, and
a recessed area formed in the leading edge proximate the tip, the recessed area having a radial length that is shorter than a radial length of the airfoil measured between the root and the tip of the airfoil;
printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material;
sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material, wherein sintering the green body part is performed at a suitable temperature and for a suitable time duration to facilitate producing the post-sintering erosion shield including the densified erosion-resistant material with an equiaxed grain structure and a relative density greater than or equal to about 92%; and
coupling the erosion shield within the recessed area formed in the leading edge of the turbine blade, the erosion shield including an outer surface that is flush with a remaining portion of the leading edge for the airfoil formed adjacent the recessed area,
wherein the erosion shield forms a continuous and smooth transition for the airfoil between the outer surface and the remaining portion of the leading edge.
2. The method in accordance with claim 1 , wherein sintering the green body part further comprises sintering the green body part at a suitable temperature and for a suitable time duration to facilitate producing the post-sintering erosion shield including the densified erosion-resistant material with a relative density greater than or equal to about 95%.
3. The method in accordance with claim 1 , wherein sintering the green body part further comprises sintering the green body part at a suitable temperature and for a suitable time duration to facilitate producing the post-sintering erosion shield including the densified erosion-resistant material with a porosity of less than or equal to about 5% by volume.
4. The method in accordance with claim 1 , further comprising sintering the green body part at a temperature greater than or equal to about 1260° C. and for a time duration of greater than or equal to about 2 hours.
5. The method in accordance with claim 1 , wherein printing the green body part further comprises selectively depositing a binder solution across a particulate cobalt-chromium alloy material.
6. The method in accordance with claim 1 , further comprising printing a green body support structure that supports the green body part during the sintering and, after sintering the green body part and the green body support structure, removing the post-sintering support structure from the post-sintering erosion shield.
7. The method in accordance with claim 1 , wherein the turbine blade includes a tip shroud fixedly coupled to the tip of the airfoil, and wherein coupling the erosion shield to the leading edge of the turbine blade further comprises coupling the erosion shield to extend substantially across an end of the tip shroud proximate to the leading edge.
8. The method in accordance with claim 1 , wherein coupling the erosion shield within the recessed area further comprises directly coupling an inner surface of the erosion shield to a recessed surface of the recessed area, the inner surface of the erosion shield formed opposite the outer surface and shaped to match a three-dimensional geometry of the recessed surface of the recessed area.
9. A method of reconditioning an erosion-shielded turbine blade, the method comprising:
providing a turbine blade for use with a rotary machine, the turbine blade including an airfoil extending between a root and a tip, the airfoil including a pressure side and an opposite suction side, each of the pressure and suction sides extending between a leading edge and a trailing edge, and a damaged region along the leading edge;
removing the damaged region from the leading edge to:
form a recessed area in the leading edge proximate the tip, the recessed area having radial length that is shorter than a radial length of the airfoil, and
define a remaining portion of the leading edge positioned radially adjacent the recessed area;
printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material;
sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material, wherein sintering the green body part is performed at a suitable temperature and for a suitable time duration to facilitate producing the post-sintering erosion shield including the densified erosion-resistant material with an equiaxed grain structure and a relative density greater than or equal to about 92%; and
coupling the post-sintering erosion shield within the recessed area formed in the leading edge of the turbine blade after removing the damaged region, the post-sintering erosion shield including an outer surface that is flush with the defined, remaining portion of the leading edge for the airfoil formed radially adjacent the recessed area,
wherein the post-sintering erosion shield forms a continuous and smooth transition for the airfoil between the outer surface and the remaining portion of the leading edge.
10. The method in accordance with claim 9 , wherein the damaged region along the leading edge is a first erosion shield coupled to the leading edge, and removing the damaged region comprises removing the first erosion shield from the leading edge.
11. The method in accordance with claim 9 , wherein sintering the green body part further comprises sintering the green body part at a suitable temperature and for a suitable time duration to facilitate producing the post-sintering erosion shield including the densified erosion-resistant material with the equiaxed grain structure and a relative density greater than or equal to 95%.
12. The method in accordance with claim 9 , further comprising sintering the green body part at a temperature greater than or equal to about 1260° C. and for a time duration of greater than or equal to about 2 hours.
13. The method in accordance with claim 9 , wherein printing the green body part further comprises selectively depositing a binder solution across a particulate cobalt-chromium alloy material.
14. The method in accordance with claim 9 , further comprising printing a green body support structure that supports the green body part during the sintering and, after sintering the green body part and the green body support structure, removing the post-sintering support structure from the post-sintering erosion shield.
15. The method in accordance with claim 9 , wherein the turbine blade includes a tip shroud fixedly coupled to the tip of the airfoil, and wherein coupling the post-sintering erosion shield to the leading edge of the turbine blade further comprises coupling the post-sintering erosion shield to extend substantially across an end of the tip shroud proximate to the leading edge.
16. The method in accordance with claim 9 , wherein coupling the post-sintering erosion shield within the recessed area formed in the leading edge of the turbine blade further comprises directly coupling an inner surface of the post-sintering erosion shield to a recessed surface of the recessed area, the inner surface of the post-sintering erosion shield formed opposite the outer surface and shaped to match a three-dimensional geometry of the recessed surface of the recessed area.
17. A method of manufacturing an erosion-shielded turbine blade, the method comprising:
providing a turbine blade for use with a rotary machine, the turbine blade including an airfoil extending between a root and a tip, the airfoil including:
a pressure side and an opposite suction side, each of the pressure and suction sides extending between a leading edge and a trailing edge,
a recessed area formed in the leading edge proximate the tip, the recessed area having a radial length that is shorter than a radial length of the airfoil, and
a tip shroud fixedly coupled to the tip;
printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material;
sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material, wherein sintering the green body part is performed at a suitable temperature and for a suitable time duration to facilitate producing the post-sintering erosion shield including the densified erosion-resistant material with an equiaxed grain structure and a relative density greater than or equal to about 92%; and
coupling the erosion shield within the recessed area formed in the leading edge of the turbine blade and to an end of the tip shroud proximate to the leading edge such that the erosion shield extends substantially across the end of the tip shroud,
wherein the erosion shield includes an outer surface that is flush with a remaining portion of the leading edge for the airfoil formed adjacent the recessed area, and the erosion shield forms a continuous and smooth transition for the airfoil between the outer surface and the remaining portion of the leading edge.
18. The method in accordance with claim 17 , wherein sintering the green body part further comprises sintering the green body part at a suitable temperature and for a suitable time duration to facilitate producing the post-sintering erosion shield including the densified erosion-resistant material with an equiaxed grain structure and a relative density greater than or equal to 95%.
19. The method in accordance with claim 17 , further comprising sintering the green body part at a temperature greater than or equal to about 1260° C. and for a time duration of greater than or equal to about 2 hours.
20. The method in accordance with claim 17 , wherein printing the green body part further comprises selectively depositing a binder solution across a particulate cobalt-chromium alloy material.