Flow body for a gas turbine, gas turbine, method for manufacturing a flow body for a gas turbine, and method for repairing a flow body of a gas turbine
US-2024376825-A1 · Nov 14, 2024 · US
US8967968B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-8967968-B2 |
| Application number | US-201213362755-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jan 31, 2012 |
| Priority date | Jun 9, 2011 |
| Publication date | Mar 3, 2015 |
| Grant date | Mar 3, 2015 |
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A concave (a relief portion) is formed along a circumferential direction of a rotor in a trailing-edge end surface of a platform. In the trailing-edge end surface disposed outside of the relief portion in the radial direction of the rotor an opening of a cooling channel is provided. The end surface is formed thicker in the radial direction of the rotor at the opening of the cooling channel than at a position corresponding to a trailing-edge end of a hub of an airfoil portion connected to the platform.
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The invention claimed is: 1. A turbine blade comprising: a base portion which is fixed to a rotor; an aerofoil portion which extends in a radial direction of the rotor and which includes a blade surface on a pressure side and a suction side, the blade surface on the pressure side and the suction side forming an aerofoil profile between a leading edge and a trailing edge; and a platform which is provided between the base portion and the aerofoil portion, and which has a concave…
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