Gearbox of aircraft turbine engine
AssigneeSafran Aircraft Engines
InventorJean-Baptiste Etienne Bernard Lepretre
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AssigneeSafran Aircraft Engines
InventorJean-Baptiste Etienne Bernard Lepretre
Estimating the term…
A gearbox for an aircraft turbine engine has a casing defining an enclosure for housing rotating elements lubricated by oil. At least one tubular sleeve is coupled to the rotating elements and configured to rotate a shaft. The sleeve includes splines configured to cooperate with complementary splines of said shaft. The gearbox further includes means for recovering lubricating oil from the rotating elements and conveying the recovered oil by streaming to the splines to lubricate the splines.
A gearbox for an aircraft turbine engine, comprising a casing defining an enclosure for housing rotating elements lubricated by oil, and at least one tubular sleeve coupled to the rotating elements and configured to rotate a shaft, the sleeve including splines configured to cooperate with complementary splines of said shaft, the gearbox further comprising means for recovering lubricating oil from the rotating elements and conveying recovered oil by streaming to the splines to lubricate the splines, said recovery and conveying means comprising at least one inner wall collecting oil from said casing, the gearbox being configured to cause the oil to stream over said at least one collecting inner wall during the operation of the turbine engine, wherein said recovery and conveying means comprise a channeling member that extends at least partially inside said sleeve, and at least one gutter configured to convey the oil that streams over said at least one collecting inner wall to the channeling member, in which said channeling member and said at least one gutter are supported by or formed with a flange of the casing, the flange defining said at least one collecting inner wall and supporting a rolling bearing of the sleeve, the flange including at least one radial opening allowing oil flowing on said collecting inner wall to reach said channeling member.
Dependencies are inferred from the claim text.
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Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby: combinations with mechanical gearing
Component parts, details, or accessories, not provided for in, or of interest apart from, other groups: arrangement of bearings; Supporting or…
Component parts, details, or accessories, not provided for in, or of interest apart from, other groups: lubricating arrangements
Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for…:…
About 8 years 7 months of term left · ends 22 May 2035 (estimated)
The present invention relates to a gearbox for an aircraft turbine engine.
The state of the art in particular comprises document EP-A1-2,711,505, U.S. Pat. No. 3,621,937 and GB-A-2,488,142.
A gearbox for an aircraft turbine engine, in particular for an airplane or helicopter turbojet engine or turboprop, may consist of an accessory gearbox (AGB), which is used to drive equipment of the turbine engine, such as pumps, electricity generators, etc. The accessory gearbox transmits mechanical power originating from the turbine engine to the equipment via a kinematic chain made up of rotating elements such as pinions or rolling bearings. A gearbox for an aircraft turbine engine may also consist of a transfer gearbox (TGB), for example to kinematically connect an accessory gearbox to a turbine shaft of the turbine engine by using two transfer shafts optionally forming an angle and connected to one another by the transfer gearbox.
The invention will be better understood and other details, features and advantages thereof will appear upon reading the following description, provided solely as a non-limiting example in reference to the appended drawings, in which:
FIG. 1 is a diagrammatic perspective view of one example of an accessory gearbox of a turbine engine;
FIG. 2 is a very diagrammatic sectional view of an accessory gearbox according to the invention;
Reference will first be made to FIG. 1, which shows an example of an accessory gearbox 10 for driving equipment 12 of a turbine engine, such as an aircraft turbojet engine or turboprop. Such an accessory gearbox is in particular described in document FR-A1-2,941,744.
This gearbox 10 is intended to withdraw mechanical power originating from the turbine engine and transmit it to the pieces of equipment, which are pumps, electricity generators, etc. The transmission is done by a kinematic chain made up of rotating elements meshing with one another to form lines of gears or accessories.
The accessory gearbox 10 comprises a casing 14 defining an enclosure housing rotating elements that for example comprise pinions and rolling bearings. The kinematic chain is connected to a driveshaft 16 that is a radial shaft of the turbine engine or an intermediate shaft, the chain also being connected to movement shafts 18 of the pieces of equipment. The accessory gearbox 10 is fastened to the turbine engine and the pieces of equipment are generally in turn fastened to the accessory gearbox 10.