A self-aligning hanger for use in a gas turbine engine exhaust system comprises a first bracket, a second bracket, a rod, a first ball joint and a second ball joint. The first bracket is for connecting to an exhaust duct of the gas turbine exhaust system. The second bracket is for connecting to an exhaust duct liner of the gas turbine exhaust system. The rod extends between the first bracket and the second bracket. The first ball joint connects a first end of the rod with the first bracket. The second ball joint connects a second end of the rod with the second bracket.

Self-aligning liner support hanger

A pressure balanced shaft seal assembly that allows a seal to dynamically respond to angular or radial misalignment of a shaft is disclosed. The pressure balanced shaft seal assembly includes a fixed stator, a floating stator, and a labyrinth seal. In one embodiment, the floating stator and labyrinth seal are mounted within an annular groove formed in the fixed stator such that the floating stator and labyrinth seal may move a predetermined amount in the radial direction with respect to the fixed stator. A spherical interface between the labyrinth seal and floating stator may allow the labyrinth seal to pivot with respect to the floating stator during angular misalignment of a shaft around which the pressure balanced shaft seal assembly is mounted. A pressure balancing annular channel formed in the floating stator allows pressurized seal fluid to balance the axial pressure exerted on the floating stator by the process fluid.

Pressure balanced shaft seal assembly

A landing gear for an aircraft, characterized by upper and lower pintle frame members (38, 40) being connected to a telescoping shock strut (14) in a non-rigid manner that tolerates twisting when reacting to torsional loads applied to the landing gear, and/or by a pitch trim actuator (30) that positions a landing gear truck (16) proportionally to the retraction angle of a shock strut (14) during retraction and extension.

Retractable articulated landing gear

A fastener is configured to affix a first article such as a picket to a second article such as a rail to form a railing or balustrade. The fastener includes a first engaging surface having a maximum diameter configured to engage an interior surface of an opening in the first article and a mating surface configured to mate with the second article. The first engaging surface can have shape selected from cylindrical, ellipsoidal, conical, elliptic conical frustum, pyramidal frustum, and ball and other shapes having cross-sections of rectangular, pentagonal, hexagonal, octagonal and other regular polygons having at least four sides such that good engagement is obtained and the fastener is hidden from view in the assembled railing.

Fasteners, railing system and method of assembly

A spherical slide bearing has an outer ring and an inner ring slidably held in the inner ring. In the inner ring is inserted a pin so as to be slidable in the circumferential direction of the inner ring, the pin having a grease supply flow path that passes the inside of the ring to open in the outer peripheral surface of the ring. Further provided in the inner ring is a communication flow path for allowing the gap between the inner ring and the pin and the gap between the inner ring and the outer ring to communicate with each other. The entrance of the communication path is provided at a position into which grease, flowing out from the exit of the grease supply flow path, enters after flowing through the gap between the pin and the inner ring, along substantially the entire length in the axial direction of the pin.

Spherical Slide Bearing System

A landing gear hinge shaft is installed on an aircraft structure using at least two ball joints ( 22 ), at least one of which is adjustable. The differences between the theoretical and real positions of the centers of the balls are measured, and the adjustments that have to be made to bring the centers of the balls back to their theoretical positions is deduced. This is done by making a first adjustment in the axial direction using a shim ( 30 ) and a second adjustment in the radial direction by adjusting the rotation of an inner cage ( 34 ) and an outer cage ( 36 ) of the ball joint. The inner and outer cages have eccentric axes that facilitate the adjustment.

Process for assembly of landing gear on an aircraft structure and aircraft comprising such landing gear

Lubrication device for a ball joint bearing block. The device comprises at least one reservoir grease ( 30 ), a pump ( 34 ) capable of circulating grease between the reservoir and at least one bearing block lubrication groove ( 28 ), and a system ( 36 ) designed to actuate the pump ( 34 ) at every rotation movement of a hinge pin ( 16 ) of the bearing block. Preferably, there is a first groove ( 28 ) between the cage ( 24 ) and the ball ( 22 ) of the ball joint, and a second groove between the ball ( 22 ) and the hinge pin ( 16 ). Each rotation of the hinge pin ( 16 ) thus alternately controls injection of grease into one of the two grooves. One preferred application is lubrication of the hinge pins of aircraft landing gear.

Ball joint bearing block lubrication device

Device for assembly of landing gear on an aircraft structure. The device comprises two segments ( 14 a , 14 b ) of the shaft aligned along the same center line and fixed to a fitting of the landing gear, two support devices ( 10 a, 10 b ) fixed to the aircraft structure, two ball joint balls ( 12 a, 12 b ) installed between the corresponding shaft segments and the support devices and a tension bar ( 24 ) connecting the two support devices. One ( 10 a ) of the two support devices, preferably turned towards the outside of the aircraft, is deformable by bending or articulation. Advantageously, the tension bar bears on the bearing balls ( 20 a, 20 b ) and the guide rings are placed between the bar and the shaft segments, to prevent vibrations.

Device for assembly of landing gear on an aircraft structure

A pump (34) circulates grease between a reservoir (30) and a bearing block lubricating groove (28). A reaming (26) actuates the pump at every rotation movement of the hinge pin (16) of the bearing block.

Grégory Reniau

Papers

Process for assembly of landing gear on an aircraft structure and aircraft comprising such landing gear

Ball joint bearing block lubrication device

Device for assembly of landing gear on an aircraft structure

Lubrication device for articulated bearing

Schmierungsvorrichtung für gelenklager