Rotor blade for a turbomachine

1. A rotor blade for arrangement in a gas duct of a turbomachine, wherein the rotor blade comprises a rotor blade airfoil which, when viewed in a tangential section, has a blade airfoil profile comprising

a front edge radius R VK , and

a blade airfoil thickness d,

the blade airfoil profile being thickened at least in sections, and the blade airfoil thickness d being set with respect to the front edge radius R VK such that at least at a spacing A of 1 mm or 0.5 mm, measured along a skeletal line of the blade airfoil from the front edge thereof,

(2× d/R VK 2 )− d≤ 5.5

and wherein:

i) the blade airfoil thickness d in a front edge region at the spacing A is from 0.5 mm to 5 mm; and/or

(ii) in terms of a chord length l measured on the blade airfoil profile, the blade airfoil thickness d is set at a ratio to the front edge radius R VK and the chord length l such that 4.0≤d/(R VK ×1)≤7.0; and/or

iii) in terms of the chord length 1 measured on the blade airfoil profile, at least at the spacing A between 1.0 mm and 2.0 mm that is measured along the skeletal line of the blade airfoil profile from the front edge thereof, the blade airfoil thickness d is set with respect to the front edge radius R VK and the chord length 1 such that d/(R VK ×1)≤7.2; and/or

iv) the blade airfoil thickness d is set with respect to the front edge radius R VK such that 0.6≤(2×d/R VK 2 )−d≤4.0.

2. The rotor blade of claim 1 , wherein the front edge radius R VK ranges from 0.2 mm to 1.8 mm.

3. The rotor blade of claim 1 , wherein the front edge radius R VK ranges from 0.6 mm to 1.4 mm.

4. The rotor blade of claim 1 , wherein the front edge radius R VK ranges from 0.7 mm to 1.4 mm.

5. The rotor blade of claim 1 , wherein the blade airfoil thickness d in the front edge region at the spacing A is from 0.5 mm to 5 mm.

6. The rotor blade of claim 1 , wherein the blade airfoil thickness d in the front edge region at the spacing A is from 1.5 mm to 4 mm.

7. The rotor blade of claim 1 , wherein the blade airfoil thickness d in the front edge region at the spacing A is from 2 mm to 2.5 mm.

8. The rotor blade of claim 1 , wherein, in terms of a rotor blade airfoil height H measured from radially inside to radially outside of the rotor blade airfoil, the blade airfoil profile is thickened at radial positions of at least from 60% to 90% of the rotor blade airfoil height H.

9. The rotor blade of claim 1 , wherein the blade airfoil thickness d is set at the ratio to the front edge radius R VK and the chord length 1 such that 4.0≤d/(R VK ×1)≤7.0.

10. The rotor blade of claim 1 , wherein at least at the spacing A between 1.0 mm and 2.0 mm that is measured along the skeletal line of the blade airfoil profile from the front edge thereof, the blade airfoil thickness d is set with respect to the front edge radius R VK and the chord length l such that d/(R VK ×1)≤7.2.

11. The rotor blade of claim 1 , wherein at least the rotor blade airfoil is made from a brittle material which has a maximum total elongation of less than 6%.

12. The rotor blade of claim 1 , wherein at least the rotor blade airfoil is made from a high-temperature-resistant material which is suitable for use in temperatures of up to at least 700° C.

13. The rotor blade of claim 1 , wherein the rotor blade airfoil is a solid profile.

14. A turbine module for an aircraft engine, wherein the module comprises the rotor blade of claim 1 .

15. An aircraft engine, wherein the aircraft engine comprises the turbine module of claim 14 .

16. The rotor blade of claim 1 , wherein the blade airfoil thickness d is set with respect to the front edge radius R VK such that

0.6≤(2× d/R VK 2 )− d≤ 4.0.

17. A rotor blade for arrangement in a gas duct of a turbomachine, wherein the rotor blade comprises a rotor blade airfoil which, when viewed in a tangential section, has a blade airfoil profile comprising

a front edge radius R VK , and

a blade airfoil thickness d,

the blade airfoil profile being thickened at least in sections, and the blade airfoil thickness d being set with respect to the front edge radius R VK such that

(2× d/R VK 2 )− d≤ 5.5

and wherein, in terms of a chord length l measured on the blade airfoil profile, the blade airfoil thickness d is set with respect to the front edge radius R VK and the chord length 1 such that

4.0≤ d /( R VK ×1)≤7.2.