Aircraft turbine engine mechanical reduction gear
View Patent ↗A turbine engine mechanical reduction gear, for example, of an aircraft, the reduction gear comprising: a sun gear having an axis of rotation; a ring gear which extends around the sun gear and which is configured to be immobile in rotation about the axis; planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about the axis; at least one lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of the planetary carrier; and an annular oil deflector which is integral with the ring gear, wherein the stator portion of the distributor is integral with the deflector.
1. A turbine engine mechanical reduction gear for an aircraft, the reduction gear comprising:
a sun gear having an axis of rotation;
a ring gear which extends around the sun gear and which is configured to be immobile in rotation about said axis;
planetary gears which are meshed with the sun gear and the ring gear and which are supported by a planetary carrier which is configured to be mobile in rotation about said axis;
a lubrication oil distributor which comprises a stator portion immobile in rotation and a rotating integral rotor portion of said planetary carrier; and
at least one annular oil deflector which is integral with the ring gear,
wherein said stator portion of the distributor is integral with said deflector.
2. The mechanical reduction gear according to claim 1 , wherein the deflector comprises an annular flange for mounting to an annular flange of the ring gear.
3. The mechanical reduction gear according to claim 2 , wherein the ring gear comprises two half-ring gears each comprising a rim equipped with a gearing and a mounting half-flange, the mounting half-flanges being fixed together and to the flange of the deflector.
4. The mechanical reduction gear according to claim 3 , wherein the deflector comprises an outer peripheral portion extending around a half-ring gear.
5. The mechanical reduction gear according to claim 1 , wherein the ring gear comprises two half-ring gears each comprising a rim equipped with a gearing and a mounting half-flange, the deflector being fixed to the rim of one of the half-ring gears or being formed as a single part with one of the half-ring gears.
6. The mechanical reduction gear according to claim 1 , wherein the deflector comprises an inner peripheral portion extending generally radially to said axis.
7. The mechanical reduction gear according to claim 1 , wherein the deflector comprises an annular row of through holes.
8. The mechanical reduction gear according to claim 7 , wherein the deflector comprises a truncated portion wherein said holes are formed.
9. The mechanical reduction gear according to claim 1 , wherein said stator portion of the distributor comprises:
an outer cylindrical surface comprising oil outlet orifices and configured to engage in a sealing manner with said rotor portion of the distributor; and
an inner oil circuit comprising an annular cavity connected, on the one hand, to lines extending generally axially and connecting said cavity to said orifices, and on the other hand, to at least one supply channel extending generally radially from said cavity.
10. A turbine engine for an aircraft, comprising the mechanical reduction gear according to claim 1 .
11. The mechanical reduction gear according to claim 1 , wherein the deflector is presented in the form of a thin annular ferrule comprising a radially outer peripheral edge which is fixed to the ring gear.
12. The mechanical reduction gear according to claim 1 , wherein the deflector extends from the ring gear to the stator portion.