Compressor casing with optimized cavities
View Patent ↗The invention relates to a compressor for a turbine engine including a casing ( 4 ), at least one compressor stage consisting of a stationary blade ( 2 ) impeller and a mobile blade ( 1 ) impeller positioned upstream from said stationary blade ( 2 ) impeller, and cavities ( 5 ) made in said casing opposite the through-path of the mobile blades ( 1 ), said cavities having a length L 2 measured axially and being shifted upstream relative to the blades ( 1 ) so as to generate an overlap with a length L 1 , characterized in that the lengths L 1 and L 2 are respectively between 35% and 50% and between 80% and 90% of the axial chord C ax measured at the outer end of the blades ( 1 ), and in that the cavities ( 5 ) do not in communication with one another.
1. A compressor for a turbine engine comprising:
a casing;
at least one compressor stage including a fixed blade impeller and a mobile blade impeller that includes mobile blades that are forward swept, and the mobile blade impeller is positioned downstream of said fixed blade impeller; and
cavities hollowed-out in said casing opposite a through-path of the mobile blades, said cavities having a length L 2 measured axially and being offset upstream relative to the mobile blades so as to generate an overlap having a length L 1 ,
wherein the lengths L 1 and L 2 are respectively between 35% and 50% and between 80% and 90% of an axial cord C ax measured at an outer end of the mobile blades and in that the cavities do not communicate with one another, and wherein
an upstream end of the cavities forms in a plane of symmetry of a cavity an angle φ for reinjection of air, equal to 90°, plus or minus 5°, with a part of the casing located upstream of said cavity.
2. The compressor as claimed in claim 1 , wherein a downstream end of the cavities has a circular-arc profile, of which a radius is substantially equal to a depth of said cavity.
3. The compressor as claimed in claim 1 , wherein a number of cavities on a circumference of the casing, relative to a number of mobile blades of the corresponding impeller, is between 2 and 4.
4. The compressor as claimed in claim 1 , wherein the cavities are hollowed-out in the casing with an inclination relative to a plane tangent to a flow passage of between 45° and 60° in a direction of rotation of the blades.
5. The compressor as claimed in claim 1 , wherein the cavities are distributed uniformly over a circumference of the casing.
6. The compressor as claimed in claim 1 , wherein the cavities are distributed non-uniformly over a circumference of the casing.
7. The compressor as claimed in claim 1 , wherein the casing comprises a local set-back region of a flow passage opposite the mobile blade impeller.
8. The compressor as claimed in claim 7 , wherein an upstream end of the set-back region of the flow passage is located in a region of the upstream end of the cavity.
9. The compressor as claimed in claim 7 , wherein a downstream end of the set-back region of the flow passage is located in a region of, or slightly downstream of, a trailing edge of the mobile blades.
10. The compressor as claimed in claim 1 , wherein the cavities are formed directly in the casing.
11. The compressor as claimed in claim 1 , wherein the cavities are formed in an attached part, fixed to said casing.
12. A turbine engine comprising a compressor as claimed in claim 1 .
13. A compressor for a turbine engine comprising:
a casing;
at least one compressor stage including a fixed blade impeller and a mobile blade impeller positioned downstream of said fixed blade impeller; and
cavities hollowed-out in said casing opposite a through-path of mobile blades, said cavities having a length L 2 measured axially and being offset upstream relative to the mobile blades so as to generate an overlap having a length L 1 ,
wherein the lengths L 1 and L 2 are respectively between 35% and 50% and between 80% and 90% of an axial cord C ax measured at an outer end of the mobile blades and the cavities do not communicate with one another, and
wherein the casing comprises a local set-back region of a flow passage opposite the mobile blade impeller.
14. The compressor as claimed in claim 13 , wherein an upstream end of the set-back region of the flow passage is located in a region of the upstream end of the cavity.
15. The compressor as claimed in claim 13 , wherein a downstream end of the set-back region of the flow passage is located in a region of, or slightly downstream of, a trailing edge of the mobile blades.