Flared fan hub slot
An aerodynamic element assembly is provided and includes a hub defining a slot and an aerodynamic element. The aerodynamic element includes a dovetail section receivable in the slot and an airfoil section configured to aerodynamically interact with fluid to drive hub and aerodynamic element rotations around a rotational axis. The dovetail section is deformable during operational conditions from an initial configuration to a deformed configuration and, with the dovetail section assuming the initial configuration, at least one of ends of the slot are flared and thereby configured to be spaced apart from corresponding ends of the dovetail section and ends of the dovetail section are shaved and thereby configured to be spaced apart from corresponding ends of the dovetail section.
1. An aerodynamic element assembly, comprising:
a hub defining a slot; and
an aerodynamic element comprising a dovetail section receivable in the slot and an airfoil section configured to aerodynamically interact with fluid to drive hub and aerodynamic element rotations around a rotational axis,
the dovetail section being deformable during operational conditions from an initial configuration to a deformed configuration and, with the dovetail section assuming the initial configuration, ends of each side of the slot at opposite ends thereof are flared outwardly and are thereby configured to be spaced apart from corresponding ends of pressure surfaces of the dovetail section.
2. The aerodynamic element according to claim 1 , wherein the aerodynamic element comprises a turbine blade and the hub comprises a fan hub.
3. The aerodynamic element according to claim 1 , wherein the aerodynamic element comprises a blade and the hub comprises a bladed disk.
4. The aerodynamic element according to claim 1 , wherein the slot and the dovetail section are curved.
5. The aerodynamic element according to claim 1 , wherein the slot and the dovetail section are straight.
6. The aerodynamic element according to claim 1 , wherein a cross-sectional shape of the slot comprises inwardly facing pressure surfaces and a cross-sectional shape of the dovetail section comprises outwardly facing pressure surfaces.
7. The aerodynamic element according to claim 1 , wherein the ends of each side of the slot at the opposite ends thereof are flared outwardly by about 0.005 inches.
8. The aerodynamic element according to claim 1 , wherein, with the dovetail section assuming the initial configuration, ends of each side of the dovetail section at opposite ends thereof are shaved inwardly and are thereby configured to be spaced apart from corresponding ends of pressure surfaces of the slot.
9. The aerodynamic element according to claim 8 , wherein the ends of each side of the dovetail section at the opposite ends thereof are shaved inwardly by about 0.005 inches.
10. A gas turbine engine, comprising:
a compressor section in which air is compressed;
a combustor section in which compressed air is mixed with fuel and combusted to produce a working fluid; and
a turbine section in which the working fluid is expanded,
wherein at least one of the compressor section and the turbine section comprises an aerodynamic element assembly, comprising:
a hub defining a slot; and
an aerodynamic element comprising a dovetail section receivable in the slot and an airfoil section configured to aerodynamically interact with fluid to drive hub and aerodynamic element rotations around a rotational axis,
the dovetail section being deformable during operational conditions from an initial configuration to a deformed configuration and, with the dovetail section assuming the initial configuration, ends of each side of the slot at opposite ends thereof are flared outwardly and are thereby configured to be spaced apart from corresponding ends of pressure surfaces of the dovetail section.
11. The gas turbine engine according to claim 10 , wherein the aerodynamic element comprises a turbine blade and the hub comprises a fan hub of the turbine section.
12. The gas turbine engine according to claim 10 , wherein the aerodynamic element comprises a blade and the hub comprises a bladed disk of the compressor section.
13. The gas turbine engine according to claim 10 , wherein the slot and the dovetail section are curved or straight.
14. The gas turbine engine according to claim 10 , wherein a cross-sectional shape of the slot comprises inwardly facing pressure surfaces and a cross-sectional shape of the dovetail section comprises outwardly facing pressure surfaces.
15. The gas turbine engine according to claim 10 , wherein the ends of each side of the slot at the opposite ends thereof are flared outwardly by about 0.005 inches.
16. The gas turbine engine according to claim 10 , wherein, with the dovetail section assuming the initial configuration, ends of each side of the dovetail section at opposite ends thereof are shaved inwardly and thereby configured to be spaced apart from corresponding ends of pressure surfaces of the slot.
17. The aerodynamic element according to claim 16 , wherein the ends of each side of the dovetail section at the opposite ends thereof are shaved inwardly by about 0.005 inches.