Abstract: A propeller blade mounting system includes a mounting system (4) on rolling bearings between a propeller hub (3) and a propeller blade (2), wherein: at least one bearing outer ring (9) is connected in rotationally fixed manner to the propeller blade (2); at least one bearing inner ring (15, 16, 17) is mounted on the propeller hub (3); a sleeve-shaped central section (13) connected to the propeller blade (2) is disposed radially inside the bearing inner ring (15, 16, 17); and a lubricant chamber (18) is formed between the bearing outer ring (9) and the central section (13) in the radial direction, relative to the rotational axis (R) of the propeller hub (3), and is closed towards the exterior.

Abstract: A rolling bearing assembly, comprising at least a rolling bearing outer ring (4) of a rolling bearing, an intermediate element that surrounds the rolling bearing outer ring (4), and a housing part, into which the intermediate element (9) is inserted. The outer ring (4) is rotatably arranged in the intermediate element (9) and has a circumferential oil catching strip (6) at one of the end faces thereof, which oil catching strip is designed to convey oil into a contact zone formed between the outer ring (4) and the intermediate ring (9). A damping system having a damping recess is formed between the housing and the intermediate element (9).

Abstract: A propeller blade mounting system includes a mounting system (4) on rolling bearings between a propeller hub (3) and a propeller blade (2), wherein: at least one bearing outer ring (9) is connected in rotationally fixed manner to the propeller blade (2); at least one bearing inner ring (15, 16, 17) is mounted on the propeller hub (3); a sleeve-shaped central section (13) connected to the propeller blade (2) is disposed radially inside the bearing inner ring (15, 16, 17); and a lubricant chamber (18) is formed between the bearing outer ring (9) and the central section (13) in the radial direction, relative to the rotational axis (R) of the propeller hub (3), and is closed towards the exterior.

Abstract: A rolling bearing for a radial bearing, in particular a cylindrical roller bearing, including a number of cage pockets (8), each intended for receiving a rolling element (6), circumferential edge strips (10, 11) which are connected to each other by webs (12, 13) to form the cage pockets (8), wherein at least one of the edge strips (10) has an end-face section of reduced wall thickness designed as an oil-collecting ring (9), a first type of oil-guiding grooves (14, 15) running parallel to the webs (12, 13) at the inner circumference of at least one edge strip (10, 11), from which grooves a respective radial bore (17) extends to the outer circumference of the edge strip (10, 11), and a second type of oil-guiding grooves (16) running at the inner circumference of at least one edge strip (10, 11), which each extend from the oil-collecting ring (9) to a cage pocket (8).

Abstract: A wheel bearing for aircraft, that has a long service life and is reliable. The wheel bearing has a small number of individual parts and components that are simple to handle, to mount or to dismount. The wheel bearing of an aircraft landing gear has a wheel rim that is rotationally mounted about an axis over two roller bearings of a bearing arrangement. The external rings of the roller bearings are received together in a single-piece external ring bearing housing. The wheel rim can be detachably connected to the bearing arrangement in such a manner that it can be mounted or dismounted independently from the bearing arrangement.

Abstract: A rolling bearing assembly, comprising at least a rolling bearing outer ring (4) of a rolling bearing, an intermediate element that surrounds the rolling bearing outer ring (4), and a housing part, into which the intermediate element (9) is inserted. The outer ring (4) is rotatably arranged in the intermediate element (9) and has a circumferential oil catching strip (6) at one of the end faces thereof, which oil catching strip is designed to convey oil into a contact zone formed between the outer ring (4) and the intermediate ring (9). A damping system having a damping recess is formed between the housing and the intermediate element (9).

Abstract: A hearing arrangement which has a double-row rolling-body bearing, in particular an angular ball bearing for a turbocharger. The rolling-body bearing has at least one outer ring and at least one inner ring between which an intermediate space for two rows of rolling bodies is formed. For reliable and disruption-free lubrication, the rolling-body bearing has a central feed opening formed on the outer ring, and at least one outlet opening, lying opposite the central feed opening, on the inner ring for a lubricant. In the vicinity of each of the rows of rolling bodies, at least one feed opening is provided on the inner ring for feeding the lubricant to the rolling bodies so that the lubricant is injected via the inner ring, and the centrifugal force during the operation of the bearing is utilized.

Abstract: A seal arrangement, in particular for sealing a thin section bearing. Specifically, the invention relates to a seal of a thin section bearing such as may be used for mounting a swashplate of a helicopter. According to the invention, this seal arrangement has at least two elastomer bodies, each of which form one radial sealing lip. A support body is arranged axially between the at least two elastomer bodies.

Abstract: The invention relates to a propeller blade bearing, for the propeller blades of aircraft propellers that can be adjusted along their longitudinal axis, a plurality of propeller blades being individually fastened on a propeller hub in a corresponding number of blade seats. Every propeller blade, at its blade base, has a primary adjustable bearing and a secondary adjustable bearing and is received so as to be rotatable along its longitudinal axis inside a blade seat. The primary and the secondary adjustable bearing are configured as angular contact ball bearings that have respective upper bearing races and lower bearing races and rolling bodies interposed between said bearing races. A lubricating oil reservoir is arranged in the propeller hub and supplies the primary and the secondary adjustable bearing with lubricating oil when the propeller rotates. Every propeller blade is configured as a completely pre-assembled unit with the primary adjusting bearing and the secondary adjusting bearing.

Abstract: A bearing arrangement which has a double-row rolling-body bearing, in particular an angular ball bearing for a turbocharger. The rolling-body bearing has at least one outer ring and at least one inner ring between which an intermediate space for two rows of rolling bodies is formed. For reliable and disruption-free lubrication, the rolling-body bearing has a central feed opening formed on the outer ring and at least one outlet opening, lying opposite the central feed opening, on the inner ring for a lubricant. In the vicinity of each of the rows of rolling bodies, at least one feed opening is provided on the inner ring for feeding the lubricant to the rolling bodies so that the lubricant is injected via the inner ring and the centrifugal force during the operation of the bearing is utilized.

Abstract: A wheel bearing for aircraft, that has a long service life and is reliable. The wheel bearing has a small number of individual parts and components that are simple to handle, to mount or to dismount. The wheel bearing of an aircraft landing gear has a wheel rim that is rotationally mounted about an axis over two roller bearings of a bearing arrangement. The external rings of the roller bearings are received together in a single-piece external ring bearing housing. The wheel rim can be detachably connected to the bearing arrangement in such a manner that it can be mounted or dismounted independently from the bearing arrangement.

Abstract: The invention relates to a propeller blade bearing, for the propeller blades of aircraft propellers that can be adjusted along their longitudinal axis, a plurality of propeller blades being individually fastened on a propeller hub in a corresponding number of blade seats. Every propeller blade, at its blade base, has a primary adjustable bearing and a secondary adjustable bearing and is received so as to be rotatable along its longitudinal axis inside a blade seat. The primary and the secondary adjustable bearing are configured as angular contact ball bearings that have respective upper bearing races and lower bearing races and rolling bodies interposed between said bearing races. A lubricating oil reservoir is arranged in the propeller hub and supplies the primary and the secondary adjustable bearing with lubricating oil when the propeller rotates. Every propeller blade is configured as a completely pre-assembled unit with the primary adjusting bearing and the secondary adjusting bearing.

Abstract: A single-row or multi-row rolling bearing comprising thin-walled bearing races which are made of a martensitic, through hardened steel and have the following characteristics: a surface hardness of ?613 HV (56 HRC) in the area of the bearing face; a core hardness of ?285 HV (28 HRC); a difference of ?150 HV (9 HRc) between the surface hardness and the core hardness. The core hardness is reached at a depth ranging between 8 percent of the diameter of the rolling elements and 90 percent of the wall thickness on the bottom of the track. There is a ratio of ?20 between the diameter of a pitch circle Tk and the diameter of a rolling element DW.

Abstract: A single-row or multi-row rolling bearing comprising thin-walled bearing races which are made of a martensitic, through hardened steel and have the following characteristics: a surface hardness of ?613 HV (56 HRC) in the area of the bearing face; a core hardness of ?285 HV (28 HRC); a difference of ?150 HV (9 HRc) between the surface hardness and the core hardness. The core hardness is reached at a depth ranging between 8 percent of the diameter of the rolling elements and 90 percent of the wall thickness on the bottom of the track. There is a ratio of ?20 between the diameter of a pitch circle Tk and the diameter of a rolling element DW.

Abstract: A seal for a track roller bearing, the bearing including an outer ring an inner ring and a bearing arrangement of rolling bodies or of a sliding body between the bearing rings. A respective thrust washer at each lateral side of the outer ring and extending radially past the bearing arrangement. A circumferential groove around the periphery of the thrust washers. A respective seal between the outer ring and each thrust washer, the seal including a first axially extending leg with a shoulder in the groove in the thrust washer and including a second obliquely radially and axially outwardly extending leg terminating in a sealing lip which is received in a recess in the outer ring. An annular shoulder defines the axial outside of the recess and the inner surface of the shoulder is gap spaced from the lip enabling the oblique arm to deflect outwardly upon over pressure of the bearing.

Abstract: The invention enables reliable feeding of lubricant for the rotor mounting of an exhaust turbocharger, wherein the rotary shaft is supported in a two row antifriction bearing, so that the lubricant is uniformly distributed to each of the rows of rolling bodies although the lubricant is supplied from one axial side of the bearing. The bearing inner ring is separated into two rings. A first inner ring is below and defines the inner race for one row of rolling bodies. Below the other row of rolling bodies is a second inner race comprised of two inner ring parts. The inner ring for the first row of rolling bodies extends radially inwardly and axially past the second inner ring parts for the second row of rolling bodies. An annular channel in the axially inner, first ring part of the second inner ring is connected with an axially extending passage that transmits lubricant to the annular channel.