Contouring of an airfoil array platform
Disclosed is an airfoil array segment ( 110, 120, 130, 140, 150 ) of an airfoil array for a turbomachine, the airfoil array segment including a platform ( 10 ) having a platform surface, as well as at least two airfoils ( 20, 30 ). The platform surface has a depression ( 111, 121, 131, 141, 151 ) which extends up to the first airfoil and contacts the pressure side ( 21 ) of the first airfoil downstream of 80% of the axial chord (g) downstream of the leading edges ( 23, 33 ) and which contacts the pressure side ( 21 ) of the first airfoil downstream up to no more than 80% of the axial chord (g) downstream of the leading edges ( 23, 33 ). At least one lowest point ( 112, 122 ) of the depression is located at least 90% of the axial chord (g) downstream of the leading edges ( 23, 33 ). Also disclosed are an airfoil array, an airfoil passage, a platform, a turbomachine, and an aircraft engine.
1. An airfoil array segment of an airfoil array for a turbomachine, the airfoil array segment comprising:
a platform having a platform surface, a first airfoil and a second airfoil, the first and second airfoil defining, on the platform surface, axial chords of the first airfoil and the second airfoil between respective leading and trailing edges, and defining an inter-airfoil strip between the pressure side of the first airfoil and the suction side of the second airfoil;
wherein the platform surface has a depression extending up to the first airfoil, the depression having at least one lowest point located at least 90% of the axial chord of the first airfoil downstream of the leading edges, and the depression contacting the pressure side of the first airfoil downstream of 80% of the axial chord of the first airfoil downstream of the leading edges and contacting the pressure side of the first airfoil downstream up to no more than 80% of the axial chord of the first airfoil downstream of the leading edges.
2. The airfoil array segment as recited in claim 1 wherein the depression is located entirely downstream of 80% of the axial chord of the first airfoil downstream of the leading edges.
3. The airfoil array segment as recited in claim 1 wherein a portion of the first airfoil is rooted on its suction side in the depression.
4. The airfoil array segment as recited in claim 1 wherein the depression has a region located downstream of the trailing edges of the first and second airfoils.
5. The airfoil array segment as recited in claim 1 wherein the depression extends from the pressure side of the first airfoil toward the suction side of the second airfoil.
6. The airfoil array segment as recited in claim 5 wherein the depression extends no more than 60% or no more than 50% of a pitch spacing of the airfoil array segment in the circumferential direction.
7. The airfoil array segment as recited in claim 1 wherein the platform surface has at least one elevation entirely or partially located upstream of the depression.
8. The airfoil array segment as recited in claim 7 wherein a portion of the first airfoil is rooted on its pressure side to the elevation.
9. The airfoil array segment as recited in claim 1 wherein the depression is a first depression and the platform surface has at least one second depression entirely or partially located upstream of the first depression.
10. The airfoil array segment as recited in claim 9 wherein a portion of the second airfoil is rooted on its suction side in the second depression.
11. An airfoil array for a turbomachine, the airfoil array comprising at least one airfoil array segment as recited in claim 1 .
12. An airfoil passage of a turbomachine, comprising the airfoil array segment as recited in claim 1 and an endwall located opposite the platform of the airfoil array segment, the airfoil passage being bounded by the airfoil array segment and and by the endwall.
13. A platform for an airfoil array segment as recited in claim 1 wherein the platform is adapted to adjoin the first and second airfoils in the circumferential direction.
14. A turbomachine comprising at least one airfoil array as recited in claim 11 .
15. An aircraft engine comprising the turbomachine as recited in claim 13 .