Arrangement of a rotor and at least a blade
View Patent ↗It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root. The root has side walls which complement side walls of the seat and axial walls between the side walls. A chamber is provided between the root and the rotor. A shank cavity is provided between the root and the platform. A lock plate facing at least an axial wall is connected to the rotor and the blade. The lock plate has at least a slot on a side facing the root.
1. An arrangement of a rotor and at least a blade, comprising:
a blade which includes a root, a platform and an airfoil; and
a rotor which includes a seat for the root, the root having side walls which complement side walls of the seat, and having axial walls between the side walls;
a chamber between the root and the rotor;
a shank cavity between the root and the platform; and
a lock plate facing one axial wall of the axial walls and being connected to the rotor and the blade, wherein the lock plate has a plurality of slots on a side facing the root wherein at least some of the plurality of slots are connected together via a cut out configured to feed cooling air to the slots.
2. The arrangement of claim 1 , wherein the plurality of slots extend in a substantially radial direction of the turbine.
3. The arrangement of claim 1 , wherein the cut out at least partly faces the chamber.
4. The arrangement of claim 1 , comprising:
ribs defined between the slots.
5. The arrangement of claim 1 , wherein the root comprises:
a protrusion that protrudes into the chamber radially.
6. The arrangement of claim 5 , wherein the root comprises:
a second protrusion that protrudes into the chamber radially.
7. The arrangement of claim 1 , wherein at least one slot of the plurality of slots comprises:
a local restriction for reducing air flow that passes the restriction.
8. A lock plate comprising:
borders and opposite sides, arranged and configured for fixing an axial position of a blade on a rotor of a gas turbine engine wherein at least one side of the lock plate has a plurality of slots on a side configured to face a root of a blade wherein at least some of the plurality of slots are connected together via a cut out configured to feed cooling air to the slots.
9. The lock plate of claim 8 , wherein at least one slot of the plurality of slots comprises:
a local restriction for reducing air flow that passes the restriction.