Blade for a high-speed turbine stage having a single sealing element
Described is a blade for a high-speed turbine stage of an aircraft gas turbine, in particular of an aircraft engine, the blade including a radially inner blade root, a radially outer shroud, and an airfoil extending between the blade root and the shroud. It is provided that the outer shroud have only a single sealing element, which projects radially from the shroud, in particular only a single sealing fin.
1. A blade for a high-speed turbine stage of an aircraft gas turbine, the blade comprising:
a radially inner blade root;
a radially outer shroud; and
an airfoil extending between the blade root and the shroud;
the outer shroud having only a single sealing element projecting radially from the shroud, the shroud being made of a brittle material and having a weight of less than 7 grams.
2. The blade as recited in claim 1 wherein the single sealing element is a single sealing fin.
3. The blade as recited in claim 1 wherein the blade is designed or suitable for an An 2 of ≥4000 m 2 /s 2 at the ADP of the aircraft gas turbine.
4. The blade as recited in claim 1 wherein the blade is designed or suitable for an An 2 of ≥4500 m 2 /s 2 at the ADP of the aircraft gas turbine.
5. The blade as recited in claim 1 wherein the blade is designed or suitable for an An 2 of ≥5000 m 2 /s 2 at the ADP of the aircraft gas turbine.
6. The blade as recited in claim 1 wherein the airfoil has a radially inner chord length at least 1.1 times to 1.4 times a radially outer chord length, the inner chord length being measured at the airfoil directly above the blade root, and the outer chord length being measured at the airfoil directly below the shroud.
7. The blade as recited in claim 1 wherein an entirety of the blade is made of the brittle material.
8. The blade as recited in claim 7 wherein the brittle material is a titanium aluminide alloy.
9. The blade as recited in claim 7 wherein the blade is made by casting, forging or additive manufacturing.
10. The blade as recited in claim 1 wherein the airfoil is provided with material thickenings on at least a locally thickened leading edge.
11. The blade as recited in claim 1 wherein the airfoil or the sealing element has a hardfacing formed thereon, at least in some regions, the hardfacing being made from a material different from the material of the blade.
12. The blade as recited in claim 11 wherein the hardfacing is made from a ceramic material or a Ni-based material.
13. A turbine stage for a gas turbine comprising a plurality of blades as recited in claim 1 and arranged adjacent one another in the circumferential direction.
14. The turbine stage as recited in claim 13 wherein cooling is provided for the shroud.
15. The turbine stage as recited in claim 13 wherein the blades arranged adjacent one another in the circumferential direction are configured to have different natural frequencies.
16. The turbine stage as recited in claim 15 wherein blades arranged adjacent one another in the circumferential direction differ in a geometry of the airfoil or of the shroud.
17. The turbine stage as recited in claim 14 wherein cooling fluid is supplied as the cooling in the shroud of the blades of the turbine stage from a region upstream thereof.
18. The turbine stage as recited in claim 13 wherein at least one blade of the blades has disposed thereon a blade shroud weight configured such that a static mean stress of less than 150 MPa is obtained in all sections of the blade profile.
19. An aircraft engine comprising the high-speed turbine stage as recited in claim 13 and a fan, wherein during operation of the aircraft engine, the turbine stage rotates faster than the fan.