Annular flange for fastening a rotor or stator element in a turbomachine
View Patent ↗A radial annular flange including in inner or outer periphery alternating solid portions including orifices for passing fastener bolts, and hollow portions having bottoms that are substantially flat. The bottom of at least one keying hollow portion is situated radially inside, or outside, respectively, a circle centered on the axis of the flange and externally, or respectively internally, tangential to the orifices. Two hollow portions are situated on either side of the keying hollow portion having bottoms of concave curved shapes situated radially on the outside, or respectively on the inside, relative to the flat bottoms of the other hollow portions.
1. A radial annular flange of a turbomachine turbine, the flange having an axis around which axis the flange extends and comprising: at an inner periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts, the hollow portions comprising a first hollow portion, a second hollow portion, and third hollow portions, each of the hollow portions having a bottom, the bottoms of first and second hollow portions being substantially flat, wherein the second hollow portion comprises a keying system formed by its flat bottom that is situated radially on the inside of a circle centered on the axis of the flange and externally tangential to the orifices in the solid portions, wherein the third hollow portions are situated on either side of said second hollow portion and present bottoms of concave curved shapes situated radially on the outside relative to the bottoms of the first and second hollow portions, and wherein the bottom of the first hollow portion is situated radially on the outside relative to the circle externally tangential to the orifices of the solid portions.
2. A radial annular flange of a turbomachine turbine, the flange having an axis around which axis the flange extends and comprising: at an outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts, the hollow portions comprising a first hollow portion, a second hollow portion, and third hollow portions, each of the hollow portions having a bottom, the bottoms of first and second hollow portions being substantially flat, wherein the second hollow portion comprises a keying system formed by its flat bottom that is situated radially on the outside of a circle centered on the axis of the flange and internally tangential to the orifices in the solid portions, wherein the third hollow portions are situated on either side of said second hollow portion and present bottoms of concave curved shapes situated radially on the inside relative to the bottoms of the first and second hollow portions.
3. A flange according to claim 2 , wherein the bottom of the first hollow portion is situated radially on the inside relative to the circle internally tangential to the orifices of the solid portions.
4. A flange according to claim 1 or claim 3 , wherein the concave curved bottoms of the third hollow portions are in a form of circular arcs of radius R 2 .
5. A flange according to claim 4 , wherein the concave curved bottoms of the third hollow portions are connected to the adjacent solid portions by circular arcs of radius R 1 .
6. A flange according to claim 5 , wherein the radius R 2 of the concave curved bottoms of the third hollow portions is greater than the radius R 1 of the connections to the adjacent solid portions.
7. A flange according to claim 6 , wherein the radius R 2 of the concave curved bottoms of the third hollow portions is greater than or equal to three times the radius R 1 of the connections of the adjacent solid portions.
8. A flange according to claim 5 , wherein the radius R 1 of the connections is in a range of 4 mm to 6 mm.
9. A flange according to claim 4 , wherein the concave curved bottoms of the third hollow portions have a radius of about 18 mm.
10. A low pressure turbine for a turbomachine, the turbine comprising at least one annular flange according to claim 1 or claim 2 .
11. A turbomachine, a turbojet, or a turboprop, comprising a low pressure turbine according to claim 10 .