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US 10,472,970 B2Granted
Gas turbine engine component having contoured rib end
AssigneeUnited Technologies Corporation
InventorsAlex J. Simpson, David A. Niezelski
Life of this patent
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Abstract
A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and at least one rib that protrudes from the wall and extends to a rib end, the rib end having a curved transition portion near a location where the at least one rib meets the wall.
Claims16
A component, comprising:
- a wall defining a portion of an interior cavity of a cooling circuit of said component;
- at least one rib that protrudes from said wall and extends to a rib end, said rib end having a curved transition portion near a location where said at least one rib meets said wall, said rib end terminates prior to a platform of said component to form a flow passage connected to said interior cavity;
- a first fillet extending from said curved transition portion, said first fillet defining a first fillet concave portion decreasing in thickness as said first fillet concave portion extends from curved transition portion toward said platform;
- and
- a second fillet extending from said curved transition portion, said second fillet having a second fillet concave portion decreasing in thickness as said second fillet concave portion extends from said curved transition portion toward said platform, wherein said curved transition portion defines a concave surface extending from said first fillet concave portion to said second fillet concave portion, and at least a portion of said curved transition portion includes a continuously varied curvature.
2 more elements
A gas turbine engine, comprising:
- a core flow path that defines a gas path of said gas turbine engine;
- and
- a component that extends into said core flow path, said component including:
- a first wall;
- a second wall;
- a rib extending between said first wall and said second wall, said rib including a curved transition portion extending into a body of said rib, the curved transition portion terminates prior to a platform of the component;
- a first fillet extending from said curved transition portion, said first fillet defining a first fillet concave portion decreasing in thickness as said first fillet concave portion extends from said curved transition portion toward said platform;
- and
- a second fillet extending from said curved transition portion, said second fillet having a second fillet concave portion decreasing in thickness as said second fillet concave portion extends from said curved transition portion toward said platform, wherein said curved transition portion defines a concave surface extending from said first fillet concave portion to said second fillet concave portion, and at least a portion of said curved transition portion includes a continuously varied curvature.
6 more elements
A method of reducing stress concentrations in a gas turbine engine component, comprising:
- defining a curved transition portion at a rib end of a rib disposed inside of the component to reduce stress concentrations at a location where the rib meets a wall of the component, the rib end terminates prior to a platform of the component to form a flow passage;
- and
- defining a first fillet extending from the wall to the curved transition portion, said first fillet defining a first fillet concave portion decreasing in thickness as said first fillet concave portion extends from said curved transition portion toward said platform;
- and
- defining a second fillet extending from a second wall of the component to the curved transition portion, said second fillet having a second fillet concave portion decreasing in thickness as said second fillet concave portion extends from said curved transition portion toward said platform, wherein said curved transition portion defines a concave surface extending from said first fillet concave portion to said second fillet concave portion, and at least a portion of said curved transition portion includes a continuously varied curvature.
2 more elements
Dependencies are inferred from the claim text.