One-block bladed disk provided with blades with adapted foot profile
View Patent ↗A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.
1. A one-block bladed disk comprising:
a hub; and
blades connected in one-piece to the hub;
wherein the blades, in a foot area adjacent to the hub and extending over about 20% to 30% of a height of the blade, have a dihedral angle and a sweep angle having values increasing continuously both by at least 10° upon approaching the hub.
2. The one-block bladed disk according to claim 1 , wherein the sweep angle and the dihedral angle have values decreasing continuously in a median area of the blade, adjacent to the foot area, upon approaching the hub.
3. The one-block bladed disk according to claim 1 , wherein the dihedral angle is always negative, except at a portion of the foot area which is closest to the hub.
4. The one-block bladed disk according to claim 1 , wherein the sweep angle has positive values in a median area of the blade, and has greater values than all those of the median area in a portion of the foot area which is closest to the hub.
5. The one-block bladed disk according to claim 4 , wherein the sweep angle has a maximum value of at least twice a value the sweep angle has outside the foot area.
6. The one-block bladed disk according to claim 5 , wherein the maximum value is at least 20° .
7. The one-block bladed disk according to claim 3 , wherein the portion of the foot area extends over 5% to 10% of the height of the blade.
8. The one-block bladed disk according to claim 4 , wherein the portion of the foot area extends over 10% to 20% of the height of the blade.
9. A turbine engine, comprising a one-block bladed disk according to claim 1 .
10. The turbine engine according to claim 9 , wherein the one-block bladed disk forms a compressor fan fnlly upstream from a gas flow through the turbine engine.