Radial CMC wall thickness variation for stress response
AssigneeGeneral Electric Company
InventorsRobert Charles Groves, II, Kirk Douglas Gallier, Ronald Scott Bunker
Life of this patent
Estimating the term…
Abstract
An airfoil having a radial direction extending away from an engine axis is provided. The airfoil includes an airfoil wall having an airfoil outer surface and an airfoil inner surface, with the airfoil extending radially from a first end to a second end. The airfoil defines a cooling channel interior to the inner surface with a thickness being defined between the airfoil outer surface and the airfoil inner surface. The thickness varies in the radial direction from the first end to the second end along at least one radial cross-section of the airfoil. A turbine nozzle of a turbine engine is also provided, which may include an outer band, an inner band, and the airfoil.
Claims20
An airfoil of a turbine engine having a radial direction extending away from an engine axis, comprising:
- an airfoil wall having an airfoil outer surface and an airfoil inner surface, the airfoil extending radially from a first end to a second end, wherein the airfoil outer surface has at least one locally heated portion defined by a peak of a temperature gradient, wherein the airfoil defines a cooling channel interior to the inner surface, wherein a thickness is defined between the airfoil outer surface and the airfoil inner surface, with the thickness varying in the radial direction from the first end to the second end along at least one radial cross-section of the airfoil, wherein the airfoil wall has at least one thicker portion positioned in alignment with the peak of the temperature gradient, the thicker portion being thicker than a surrounding area of the airfoil wall and configured to provide a local reduction in a thermal-mechanical stress associated with the peak of the temperature gradient, and wherein the thicker portion defines a contour on the airfoil inner surface.
A turbine nozzle of a turbine engine, comprising:
- an outer band;
- an inner band;
- and
- an airfoil extending from the outer band to the inner band;
- wherein the airfoil comprises an airfoil wall having an airfoil outer surface and an airfoil inner surface, the airfoil outer surface having at least one locally heated portion defined by a peak of a temperature gradient, and wherein a thickness is defined between the airfoil outer surface and the airfoil inner surface, with the thickness varying along at least one radial cross-section of the airfoil in a radial direction defined from the outer band to the inner band, wherein the airfoil wall has at least one thicker portion positioned in alignment with the peak of the temperature gradient, the thicker portion being thicker than a surrounding area of the airfoil wall and configured to provide a local reduction in a thermal-mechanical stress associated with the peak of the temperature gradient, wherein the thicker portion defines a contour on the airfoil inner surface.
Dependencies are inferred from the claim text.