CN201660124U - Aircraft fuel system compensator - Google Patents
Aircraft fuel system compensator Download PDFInfo
- Publication number
- CN201660124U CN201660124U CN2009202925463U CN200920292546U CN201660124U CN 201660124 U CN201660124 U CN 201660124U CN 2009202925463 U CN2009202925463 U CN 2009202925463U CN 200920292546 U CN200920292546 U CN 200920292546U CN 201660124 U CN201660124 U CN 201660124U
- Authority
- CN
- China
- Prior art keywords
- upper shell
- compensator
- seal
- aircraft fuel
- lower house
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Abstract
The utility model relates to an aircraft fuel system compensator for aircraft fuel systems. The aircraft fuel system compensator comprises a lower shell, an upper shell, universal balls, sealing assemblies, check rings, snap rings, seal holders and seal rings, the lower shell is socketed into the upper shell, one of the universal balls is arranged on the lower shell, the other universal ball is arranged on the upper shell, the upper shell and the lower shell are sealed by the two seal holders in between, the inner wall of the upper shell at the small-diameter end of the lower shell is provided with a groove, in which a seal ring and a protective ring are arranged, and the outer end surface of the upper shell is provided with a communicating hole. Since the upper shell is added with the communicating hole and a new seal, the compensator has only one acting force, consequently, the internal force is counterbalanced after pressure is applied in the compensator, additional load cannot be generated to the outside after pressure is applied in the compensator, the compensating effect is good, and meanwhile, the service life of an output shaft of a fuel feed pump is prolonged.
Description
Technical field
The utility model relates to a kind of aircraft fuel system compensator that is used for aircraft fuel system.
Background technology
The radical function of compensator is in the compensation flight course because the various pipelines that flight attitude variation and acceleration/accel produce relatively move and reverse in the aircraft fuel system, thereby plays the effect of protecting fuel oil system pipeline and annex; Simultaneously, it can also play certain supporting role to accessory product and the pipeline that links to each other.At present, on aircraft fuel system the structure of employed compensator by upper shell 8, lower house 2, multi-directional ball 1 and 20 and a plurality of seals and other component form, a multi-directional ball 1 places an end of lower house 2, the other end of lower house 2 places in the upper shell 8 and by upper shell 8 and with another multi-directional ball 20 and joins, between upper shell 8 and lower house 2, be provided with seal receptacle 11 and 14 and seal ring.All there are two opposite line pressures thereon in the compensator of this kind structure in use in the housing.Because the active area basically identical of two application forces, therefore, an application force that can't balance is just arranged in compensator, this application force will cause product when logical the pressure, to the direction motion of elongation, through calculating, when product internal work pressure is 2MPa, this application force of outwards exporting can reach 300kgf, thereby has exported a very big improper axial load to the fuel oil system pipeline under the situation of the fuel oil system pipeline not being carried out any compensation.Cause under without any the situation of external load effect, will extend automatically, and the applied loading of axial elongation can reaching 300Kgf under the product installation mode of operation.This improper load has influenced the mode of operation and the service life of balancing force two ends coupling products greatly.
The utility model content
The purpose of this utility model is to propose a kind of compensator two ends coupling mode of operation that do not influence also can director prolong the compensator aircraft fuel system compensator in service life.Technical solution of the present utility model is; the aircraft fuel system compensator; comprise lower house, upper shell, multi-directional ball, poted assemblies, back-up ring, snap ring, seal receptacle, seal ring; upper shell and lower house socket; a multi-directional ball places on the lower house; another multi-directional ball places on the upper shell; seal with two seal receptacles between upper shell and the lower house; on the upper enclosure inner wall of lower house smaller diameter end, have groove; groove is built-in with seal ring and back up ring, and the outer face of upper shell has a ditch through hole.Advantage that the utlity model has and beneficial effect, the utility model is by increasing the sealing of ditch through hole with increase on upper shell, make compensator have only an application force, thereby balanced the internal force after inner logical pressure of compensator, avoided the logical back of pressing of compensator to produce increment load to the outside, compensation effect is good, simultaneously, has prolonged the service life of oil feed pump output shaft.
Description of drawings
Fig. 1 is the utility model prior art structural representation;
Fig. 2 is the utility model structural representation.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is elaborated.The aircraft fuel system compensator, comprise in lower house 2, upper shell 8, multi-directional ball 1 and 20, poted assemblies 5, back-up ring 3, snap ring 4, the seal receptacle 11 seal ring 9 and 12 are set, the seal ring 12 outer back up rings 13 that are provided with, seal receptacle 11 other lower house 2 one sides of leaning on are provided with circlip for shaft 10; 15 of seal ring 7 is set in the seal receptacle 14, is provided with big back up ring 16 outside the seal ring 15, seal receptacle 14 other upper shell 8 one sides of leaning on are provided with back-up ring 6; Upper shell 8 and lower house 2 sockets, a multi-directional ball 1 places on the lower house 2, and another multi-directional ball 20 places on the upper shell 8, and is fixing with snap ring 4 and back-up ring 3 after multi-directional ball 1 places in the lower house, and seals with poted assemblies 5; Multi-directional ball 20 is identical with being connected of lower house 1 with multi-directional ball 1 with the connection of upper shell 8; With two seal receptacles 11 and 14 sealings, have groove 21 on upper shell 8 inwalls of lower house 2 smaller diameter end between upper shell 8 and the lower house 1, groove 21 is built-in with seal ring 17 and back up ring 18, and the outer face of upper shell 8 has a ditch through hole 19.
The aircraft fuel system compensator is assembled by metal parts, with two links realize respectively in the fuel line axially and the compensation of radial displacement.After upper shell 8 and lower house 2 sockets, come the deflection of compensation conduit and reverse with the multi-directional ball 1 and 20 that is installed in two ends; The axial stretching structure that ditch through hole 19 that increases on the upper shell 8 and seal ring 17 make compensator has only an application force to come flexible extruding in the compensation conduit.And since compensator this as a metal assembly, it self rigidity can also absorb relative higher vibration with those frequencies of filter fuel pipeline by the normal deformation of self beyond the supporting role of playing the two ends connecting pipeline.Make the high-frequency vibration of these fuel lines no longer continue to transmit backward always and fuel oil system pipeline and attaching parts generation are destroyed along fuel line.
Claims (1)
1. aircraft fuel system compensator; comprise lower house (2); upper shell (8); multi-directional ball (1 and 20); poted assemblies (5); back-up ring (3); snap ring (4); seal receptacle (11 and 14); seal ring (7; 12; 15; 16 and 17); upper shell (8) and lower house (2) socket; a multi-directional ball (1) places on the lower house (2); another multi-directional ball (20) places on the upper shell (8); seal with two seal receptacles (11 and 14) between upper shell (8) and the lower house (1); it is characterized in that; on upper shell (8) inwall of lower house (2) smaller diameter end, have groove (21); groove (21) is built-in with seal ring (17) and back up ring (18), and the outer face of upper shell (8) has a ditch through hole (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202925463U CN201660124U (en) | 2009-12-11 | 2009-12-11 | Aircraft fuel system compensator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202925463U CN201660124U (en) | 2009-12-11 | 2009-12-11 | Aircraft fuel system compensator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201660124U true CN201660124U (en) | 2010-12-01 |
Family
ID=43230537
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202925463U Expired - Lifetime CN201660124U (en) | 2009-12-11 | 2009-12-11 | Aircraft fuel system compensator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201660124U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102588649A (en) * | 2011-12-27 | 2012-07-18 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Servo valve and zero compensation method for same |
-
2009
- 2009-12-11 CN CN2009202925463U patent/CN201660124U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102588649A (en) * | 2011-12-27 | 2012-07-18 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Servo valve and zero compensation method for same |
| CN102588649B (en) * | 2011-12-27 | 2014-09-17 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Servo valve and zero compensation method for same |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20101201 |