Back to results
US 10,895,200 B2Granted
Aircraft turbine engine with improved mechanical power takeoff
AssigneeSafran Aircraft Engines
InventorsNathalie Nowakowski, Thomas Alain Christian Vincent
Life of this patent
Estimating the term…
Abstract
An aircraft turbine engine includes a fan and a reduction gear including a plurality of rotary elements and driving the fan. The turbine engine further includes a gearbox and a mechanical power takeoff box driving the gearbox. The turbine engine includes a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and meshing with the first toothed wheel.
Claims19
A front part of an aircraft bypass turbine engine comprising:
- a roller bearing bracket delimiting, on either side thereof, a radially inner space and a radially outer space;
- a fan casing;
- a reduction gear;
- a fan surrounded by the fan casing, the reduction gear driving said fan;
- an accessory gearbox;
- a mechanical power takeoff box housed in the radially inner space and driving the accessory gearbox;
- a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and driven by said first toothed wheel, the second toothed wheel being housed in the radially inner space;
- a hub of the fan;
- a plurality of items of equipment, including an item of equipment for supplying the reduction gear with lubricant;
- a cover positioned in an opening of the roller bearing bracket that separates the radially inner space from the radially outer space to form a sealed connection with the roller bearing bracket;
- and
- means for mounting the mechanical power takeoff box on the cover positioned in the opening of the bearing bracket, and being configured so as to allow the introduction of said takeoff box in said radially inner space when the cover is positioned in the opening,
- wherein said first toothed wheel is constrained to rotate with the hub of the fan,
- wherein each of the items of equipment is driven by the accessory gearbox, and
- wherein said plurality of items of equipment, and the accessory gearbox, are arranged in an inter-duct compartment of the turbine engine.
12 more elements
A front part of an aircraft bypass turbine engine comprising:
- a roller bearing bracket delimiting, on either side thereof, a radially inner space and a radially outer space;
- a fan casing;
- a reduction gear;
- a fan surrounded by the fan casing, the reduction gear driving said fan;
- an accessory gearbox;
- a mechanical power takeoff box housed in the radially inner space and driving the accessory gearbox;
- a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and driven by said first toothed wheel, the second toothed wheel being housed in the radially inner space;
- a hub of the fan;
- a plurality of items of equipment, including an item of equipment for supplying the reduction gear with lubricant;
- a cover positioned in an opening of the roller bearing bracket that separates the radially inner space from the radially outer space to form a sealed connection with the roller bearing bracket;
- and
- means for mounting the mechanical power takeoff box on the cover positioned in the opening of the bearing bracket, and being configured so as to allow the introduction of said takeoff box in said radially inner space when the cover is positioned in the opening,
- wherein said first toothed wheel is constrained to rotate with the hub of the fan,
- wherein each of the items of equipment is driven by the accessory gearbox,
- wherein said plurality of items of equipment, and the accessory gearbox, are arranged in an inter-duct compartment of the turbine engine, and
- wherein the reduction gear is supplied with lubricant via a lubrication conduit extending from the item of equipment for supplying lubricant to the reduction gear.
13 more elements
A front part of an aircraft bypass turbine engine comprising:
- a roller bearing bracket delimiting, on either side thereof, a radially inner space and a radially outer space,
- a fan casing;
- a reduction gear;
- a fan surrounded by the fan casing, the reduction gear driving said fan;
- an accessory gearbox;
- a mechanical power takeoff box housed in the radially inner space and driving the accessory gearbox;
- a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and driven by said first toothed wheel;
- a hub of the fan;
- a plurality of items of equipment, including an item of equipment for supplying the reduction gear with lubricant;
- a cover positioned in an opening of the roller bearing bracket to form a sealed connection with the roller bearing bracket;
- and
- plates connected to the cover at a first end and a second end of the plates is secured to a fixed body of the mechanical power takeoff box, and the second toothed wheel is housed in the fixed body;
- wherein said first toothed wheel is constrained to rotate with the hub of the fan,
- wherein each of the items of equipment is driven by the accessory gearbox, and
- wherein said plurality of items of equipment, and the accessory gearbox, are arranged in an inter-duct compartment of the turbine engine.
12 more elements
Dependencies are inferred from the claim text.