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US 2014/0271171 A1Published application
Compressor airfoil
AssigneesEdward Len Miller, Richard Orsatti
InventorsRICHARD ORSATTI, EDWARD LEN MILLER
Life of this patent
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Abstract
Aspects of the present invention relate to systems and methods of a vane design utilizing welding techniques. The present invention concerns a method for preventing cracking within a vane assembly utilizing full penetration welding. Additional embodiments concern a vane design that, when assembled with another vane, comprises an axial slot that prevents cracking within a vane assembly.
Claims20
A vane assembly for use in a welded vane assembly comprising:
- an inner shroud having a first inner sidewall, an opposing second inner sidewall, an inner radial thickness, an inner length, and an inner gas path surface, the first inner sidewall having a first inner groove and a second inner sidewall having a second inner groove;
- an airfoil extending radially outward from the inner gas path surface;
- and
- an outer shroud coupled to the airfoil and having a first outer sidewall, an opposing second outer sidewall, an outer radial thickness, an outer length, and has an outer gas path surface, the first outer sidewall having a first outer groove and a second outer sidewall having a second outer groove;
- wherein the first and second inner grooves and first and second outer grooves are positioned a distance along the inner and outer radial thicknesses, respectively.
2 more elements
A welded vane assembly comprising:
- a first vane assembly having:
- a first inner shroud having a first inner sidewall, an opposing second inner sidewall, an inner radial thickness, an inner length, and an inner gas path surface, the first inner sidewall having a first inner groove and a second inner sidewall having a second inner groove;
- a first airfoil extending radially outward from the inner gas path surface;
- and
- a first outer shroud coupled to the airfoil and having a first outer sidewall, an opposing second outer sidewall, an outer radial thickness, an outer length, and has an outer gas path surface, the first outer sidewall having a first outer groove and a second outer sidewall having a second outer groove;
- a second vane assembly having:
- a second inner shroud having a first inner sidewall, an opposing second inner sidewall, an inner radial thickness, an inner length, and an inner gas path surface, the first inner sidewall having a first inner groove and a second inner sidewall having a second inner groove;
- a second airfoil extending radially outward from the inner gas path surface;
- and
- a second outer shroud coupled to the airfoil and having a first outer sidewall, an opposing second outer sidewall, an outer radial thickness, an outer length, and has an outer gas path surface, the first outer sidewall having a first outer groove and a second outer sidewall having a second outer groove;
- wherein the inner sidewall of the first vane assembly contacts the inner sidewall of the second vane assembly and the outer sidewall of the first vane assembly contacts the outer sidewall of the second vane assembly such that the inner grooves of the inner sidewalls form an inner channel and the outer grooves of the outer sidewalls form an outer channel and the first vane assembly is welded to the second vane assembly.
8 more elements
A method of reducing cracks in a welded vane assembly comprising:
- Providing a first vane assembly having:
- a first inner shroud having a first inner sidewall, an opposing second inner sidewall, an inner radial thickness, an inner length, and an inner gas path surface, the first inner sidewall having a first inner groove and a second inner sidewall having a second inner groove;
- a first airfoil extending radially outward from the inner gas path surface;
- and
- a first outer shroud coupled to the airfoil and having a first outer sidewall, an opposing second outer sidewall, an outer radial thickness, an outer length, and has an outer gas path surface, the first outer sidewall having a first outer groove and a second outer sidewall having a second outer groove;
- Providing a second vane assembly having:
- a second inner shroud having a first inner sidewall, an opposing second inner sidewall, an inner radial thickness, an inner length, and an inner gas path surface, the first inner sidewall having a first inner groove and a second inner sidewall having a second inner groove;
- a second airfoil extending radially outward from the inner gas path surface;
- and
- a second outer shroud coupled to the airfoil and having a first outer sidewall, an opposing second outer sidewall, an outer radial thickness, an outer length, and has an outer gas path surface, the first outer sidewall having a first outer groove and a second outer sidewall having a second outer groove;
- positioning the first vane assembly adjacent the second vane assembly such that the first inner sidewall of the first vane assembly contacts the second inner sidewall of the second vane assembly and the first outer sidewall of the first vane assembly contacts the second outer sidewall of the second vane assembly;
- and,
- securing the first vane assembly to the second vane assembly along an interface region of the first and second inner shrouds and the first and second outer shrouds.
10 more elements
Dependencies are inferred from the claim text.