Diffuser having blades with apertures
View Patent ↗A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank.
1. A diffuser for a mixed flow or centrifugal compressor of a gas turbine, the diffuser comprising:
a vane having a pressure side, a suction side, and a first flank,
the vane including a plurality of orifices opening out into at least one of the suction side and the pressure side and communicating with a cavity formed in the vane, the cavity extending in a transverse direction relative to the vane and opening out into the first flank,
wherein a cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank.
2. The diffuser according to claim 1 , wherein the plurality of orifices includes a first series of orifices opening out into the suction side and communicating with the cavity provided in the vane and opening out into the first flank.
3. The diffuser according to claim 2 , including a single cavity opening out into the first flank.
4. The diffuser according to claim 2 , including a plurality of cavities forming recesses opening out into the first flank.
5. The diffuser according to claim 4 , wherein each of the recesses is of frustoconical shape.
6. The diffuser according to claim 1 , wherein the plurality of orifices includes a series of orifices opening out into the pressure side and communicating with at least one other cavity provided in the vane and opening out into one of the first flank and a second flank of the vane.
7. The diffuser according to claim 6 , wherein a cross section of the at least one other cavity varies, increasing towards a first flank of the vane.
8. The diffuser according to claim 6 , wherein the series of orifices communicates with a single cavity opening out into the first flank.
9. The diffuser according to claim 6 , wherein the series of orifices communicates with a plurality of cavities forming recesses opening out into the first flank.
10. The diffuser according to claim 9 , wherein each of the recesses is of frustoconical shape.
11. The diffuser according to claim 1 , wherein the plurality of orifices are at least one of transverse holes and slots.
12. A turboengine including a diffuser according to claim 1 .
13. A diffuser for a mixed flow or centrifugal compressor of a gas turbine, the diffuser comprising:
a vane having a pressure side, a suction side, and a first flank, the vane including a plurality of orifices opening out into at least one of the suction side and the pressure side and communicating with a cavity formed in the vane, the cavity extending in a transverse direction relative to the vane and opening out into the first flank,
wherein a cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank,
wherein the plurality of orifices includes a first series of orifices opening out into the suction side and communicating with the cavity provided in the vane and opening out into the first flank, and
wherein the plurality of orifices further includes a second series of orifices opening out into the pressure side and communicating with at least one other cavity provided in the vane and opening out into one of the first flank and a second flank of the vane.
14. The diffuser according to claim 13 , wherein a cross section of the at least one other cavity varies, increasing towards a first edge of the vane, and wherein the second series of orifices communicates with a single cavity opening out into the first flank.