Patent classifications
F16H1/2809
Equidirectional transfer universal transmission
The present invention relates to an equidirectional transfer universal transmission formed by connecting an equidirectional transfer case, a commutator, and an actuator. One of five types of planetary gear trains is used for the equidirectional transfer case, the component corresponding to a term having a maximum absolute value of a coefficient in a motion characteristic equation is used as an input end, and the other two components are respectively used as an inner output end and an outer output end. The commutator includes fourth types of quill shaft commutators and a non-quill shaft commutator, which are set by respective methods. One of two types of single-layer planetary gear trains is used for the actuator. The present invention includes methods for setting respective components of the equidirectional transfer case and the actuator, and includes a connection method. According to the present invention, an output shaft is controlled to revolve around an actuator shaft by inputting a revolving speed, a forward moment and a reverse moment are balanced during revolving, the output shaft has no unidirectional bearing moment, and a revolving control device has a simple structure.
Pivot for a plain bearing and gearset with reduced thermal stress
The invention relates to a pivot pin (5) for an epicyclic gear train sliding bearing, the pivot pin having axially opposed, laterally open circumferential grooves (25a), providing flexibility to the pivot pin and which radially separate two axially opposite lateral end portions of a central shank from two lateral cantilevered portions (27a,27b) of the pivot pin. At least one of the cantilevered lateral portions is hollowed out by at least one recess (65a).
RELIABLE GEARBOX FOR GAS TURBINE ENGINE
An engine core including a turbine, compressor, and a core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from the core shaft and to output drive to the fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and includes a sun gear, a plurality of planet gears, ring gear, and planet carrier to the mounted planet gears. The planet carrier has an effective linear torsional stiffness and the gearbox has a gear mesh stiffness between the planet gears and the ring gear. A carrier to ring mesh ratio of:
AIRCRAFT ENGINE
A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.
Fan drive gear system with improved misalignment capability
An epicyclic gear assembly includes a carrier that includes a first plate axially spaced from a second plate by a connector. A first epicyclic gear set is supported adjacent the first plate and includes a first set of circumferentially offset intermediate gears meshing with a first sun gear and a first ring gear. A second epicyclic gear set is axially spaced from the first epicyclic gear set and supported adjacent the second plate and includes a second set of circumferentially offset intermediate gears meshing with a second sun gear and a second ring gear. The first epicyclic gear is set and the second epicyclic gear set maintain relative intermeshing alignment during flexure-induced deformation of the carrier. The first ring gear includes a first set of teeth that extends from a first flexible flange and the second ring gear includes a second set of teeth that extends from a second flexible flange.
EPICYCLIC GEAR SYSTEM HAVING TORSIONAL FUSE, TORSIONAL FUSE IN DRIVETRAIN SYSTEM, AND METHOD OF OPERATING DRIVETRAIN SYSTEM
A torsional fuse in a drivetrain system, an epicyclic gear system, and a method of operating a drivetrain system are provided. The epicyclic gear system includes a housing, a shaft configured to rotate relative to the housing, a sun gear being disposed concentric to the shaft, a plurality of planet gears disposed around the sun gear, a ring gear disposed around the plurality of planet gears, a carrier connecting the plurality of planet gears, and a torsional fuse defined by an interface between a first torsional fuse portion and a second torsional fuse portion, the torsional fuse being configured to allow rotation between the first torsional fuse portion and the second torsional fuse portion upon application of a threshold torque at the torsional fuse.
Gear assembly mount for gas turbine engine
A gas turbine engine including a first frame including a first mount member defining a stiffness K.sub.1; a second frame including a second mount member defining a stiffness K.sub.2 and a third mount member defining a stiffness K.sub.3; and a gear assembly. The gear assembly includes a first rotatable component, a second rotatable component, and a torque transfer component. The first mount member is coupled to the first rotatable component. The second mount member is coupled to the second rotatable component. The third mount member is coupled to the torque transfer component. The stiffness K.sub.1 is less than or equal to 10% of the stiffness K.sub.3.
Precision planetary gear
A precision planetary gear comprising: a pinion; a movable annular gear; a fixed annular gear; one or more planet gears; wherein each planet gear simultaneously meshes with the pinion, the fixed annular gear and the movable annular gear; the pinion comprising a gear with a beveloid toothing; each planet gear comprising a gear with a beveloid toothing; wherein a beveloid toothing has a correction, which linearly varies along the longitudinal direction of the tooth; wherein each tooth of the beveloid toothing has a thickness and a height which increase moving from the apex of said beveloid gear along the longitudinal direction of the tooth.
Gas turbine engine having flight cycle ratio
A gas turbine engine for an aircraft including: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan including a plurality of fan blades; a gearbox that can receive an input from the core shaft and output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft; and a gearbox support arranged to at least partially support the gearbox within the engine. A flight cycle ratio of:
Geared gas turbine engine
An engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; a fan shaft; a gearbox that receives an input from the core shaft and outputs drive to the fan via the fan shaft so as to drive the fan at a lower rotational speed than the core shaft, the gearbox being an epicyclic gearbox having a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted; and a gearbox support arranged to mount the gearbox within the engine. The fan shaft, core shaft, gearbox and the gearbox support together may form a transmission.