Local stiffening for gas turbine engine casing
A gas turbine engine under this disclosure could be said to include a compressor section, a combustor and a turbine section. At least one casing surrounds at least one of the compressor and turbine section. The at least one casing is formed of sheet metal, and has at least one potential peak displacement point due to vibration across a speed range of the at least one of the compressor and turbine section. A stiffening element is fixed to a wall of the casing at the at least one potential peak displacement point. A method is also disclosed.
1. A gas turbine engine comprising:
a compressor section, a combustor and a turbine section;
at least one casing surrounding at least one of the compressor and turbine section, the at least one casing formed of sheet metal, and the at least one casing having at least one peak displacement point due to vibration across a speed range of the at least one of the compressor and turbine section; and
a stiffening element fixed to a wall of the casing at the at least one peak displacement point wherein the at least one stiffening element is H-shaped and has a pair of legs attached by a connector, and the pair of legs and the connector are all affixed to the wall of the casing, wherein the legs are parallel to an axis of the turbine engine.
2. The gas turbine engine as set forth in claim 1 , wherein there are a plurality of peak displacement points at distinct locations and a plurality of the stiffening elements.
3. The gas turbine engine as set forth in claim 1 , wherein the wall is an outer wall of the casing.
4. The gas turbine engine as set forth in claim 1 , wherein the wall is an inner wall of the casing.
5. The gas turbine engine as set forth in claim 1 , wherein there is at least one accessory mounted to a wall of the casing and impacting on the at least one peak displacement points.
6. The gas turbine engine as set forth in claim 1 , wherein there is a cutout through the wall of the casing and the at least one peak displacement point is adjacent one wall of the cutout.
7. The gas turbine engine as set forth in claim 1 , wherein the at least one stiffening element is bar shaped.
8. The gas turbine engine as set forth in claim 1 , wherein the at least one stiffening element is a dimple formed in the wall.
9. The gas turbine engine as set forth in claim 1 , wherein the stiffening element is formed of sheet metal.