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An aerospace bearing component

A technology of bearings and components, applied in the direction of bearing components, rigid supports of bearing components, shafts and bearings, which can solve problems such as limiting pressure

Active Publication Date: 2009-09-23
MINEBEA CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This depth of penetration limits the amount of pressure the bearing can withstand
For example, an aerospace bearing with a nitrogen diffusion zone can only withstand a maximum pressure of 80MPa (MPa)

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0088] Example 1: TPO using a constant oxygen flow: the effect of temperature on the process

[0089] The implemented three-pole plasma oxidation process (TPO) is to perform 240 minutes on the Ti-6Al-4V test plate (purchased from Titanium International, UK) at three different temperatures (600℃, 650℃ and 700℃) Hardening. During the ongoing process, the oxygen flow remains constant. Ti-6Al-4V test disc in annealed state (384±20HK 0.1 The thickness under) is 3mm, the diameter is 30mm, and after ultrasonic cleaning in alkaline solution, it is polished to a surface roughness of Ra=0.040±0.007μm, and then placed in the processing chamber (purchased from Tecvac Limited) IP 70 chamber).

[0090] Reducing the final pressure to less than 5×10 -3 After Pa, argon gas is introduced into the above-mentioned chamber to make the pressure reach 2.0 Pa for the splash cleaning step. A bias voltage of -1000V was applied to the above-mentioned workpiece (test disc), and splash cleaning was performe...

Embodiment 2

[0101] Example 2: TPO using pulsed oxygen flow to heat the plasma in an inert gas, or Inert gas and nitrogen heat to suppress the top oxide layer

[0102] In order to show the effect of this pulse / plasma heating condition, the surface hardness after annealing is 384±20HK 0.1 The Ti-6Al-4V test disc with surface roughness Ra=0.040±0.007μm was tested in four rounds at 700℃. The parameters of each round of test discharge (bias voltage and current density of the workpiece and resistance wire) are set to be the same as in Example 1 (respectively -200V, -200V and 1.5mA / cm 2 ). The total pressure in the TPO process is 0.4 Pa, and the partial pressures of argon and oxygen are 0.28 and 0.12 Pa, respectively. As explained in Example 1, before pulse TPO, splash cleaning and plasma heating were also performed. The oxygen flow in this embodiment is not kept constant during the entire treatment process, but is periodically pulsed, but the argon flow remains constant. The duration of this pu...

Embodiment 3

[0110] Example 3: Coating with three-pole plasma oxidation followed by spraying

[0111] As explained in Example 2, the emission of pulsed TPO followed by a plasma heating step in an inert gas or inert gas and nitrogen can produce several TPO layers with oxygen diffusion zones without any top Oxide layer. If the object is to be covered with several types of PVD or CVD films (for example, nitrides, carbides and carbonitrides), this structure is likely to be required, because when this type of film is attached to the oxidized When it is on the substrate (that is, there is a very thin oxide layer on their surface), it limits the adhesion of the coating.

[0112] To illustrate the advantages of TPO and sputtering, four pulse TPO treatments were performed on several samples of Ti-6Al-4V coated with PVD TiN with a thickness of 1.6μm, and then as described in Example 2. Plasma heating was performed at 700°C for a total time of 240 minutes. This treatment is realized in a two-cycle proce...

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Abstract

The present invention relates to an aerospace bearing component, and an aerospace bearing component of a substantially non-ferrous metal, wherein the component comprising an oxygen diffusion zone near its surface to provide a bearing surface. The aerospace bearing component can bear the pressure higher than the prior aerospace bearing.

Description

Technical field [0001] The invention relates to an aviation bearing element, in particular to an aviation bearing. Background technique [0002] Metal-to-metal (metal-to-metal) spherical bearings are used in the aerospace and aerospace industries, especially in the bearings of aircraft landing gear. Generally, the material used to manufacture the metal-to-metal bearing of the landing gear is stainless steel and copper alloy to make the inner and outer rings of the bearing (or to make the balls and the outer shell). These materials are used because their surfaces are not easy to wear without lubricants. However, these materials are relatively heavy materials, and therefore, have been looking for solutions that use lighter materials that are more suitable for the aviation and aerospace industries. In terms of strength, titanium alloy bearings can be used to replace these heavier metals. Components made of the same titanium alloy material are about 40% lighter than stainless steel a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16C33/10F16C33/12
CPCC23C28/048F16C23/04C23C28/042F16C33/12C23C8/10C23C28/044C23C28/04C23C8/34F16C2326/43F16C33/124F16C33/44F16C35/00
Inventor 保罗·雷蒙德·史密斯朱尼亚·克里斯蒂娜·艾薇克拉·巴蒂斯塔·威尔逊埃利奥特·艾希礼·菲尔丁·斯贝里乔纳森·豪斯登艾伦·马修斯艾德里安·利兰
Owner MINEBEA CO LTD
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