CN218378284U - Aircraft fuel pipeline compensator - Google Patents
Aircraft fuel pipeline compensator Download PDFInfo
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- CN218378284U CN218378284U CN202222875592.4U CN202222875592U CN218378284U CN 218378284 U CN218378284 U CN 218378284U CN 202222875592 U CN202222875592 U CN 202222875592U CN 218378284 U CN218378284 U CN 218378284U
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- sleeve
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The utility model relates to an aircraft field provides aircraft fuel pipeline compensator. Including dabber and sleeve pipe, the one end that dabber and sleeve pipe kept away from mutually is equipped with spherical chamber respectively, and the outside cover in dabber and sheathed tube spherical chamber has the rotation casing respectively, the bottom processing of the fitting surface of first casing and second casing has annular seal groove, and the sleeve pipe comprises translation section and rotation section two parts, and translation section and rotation section junction are equipped with annular protrusion, and processing has the seal groove on the fitting surface between a pair of annular protrusion. The technical scheme is that the sealing rings made of tetrafluoroethylene materials are adopted at each sealing position, the sealing rings made of tetrafluoroethylene materials have self-lubricating effects while sealing is guaranteed, operating force of various compensations can be reduced in the rotating or sliding supplementing process, resistance in passive compensation is reduced, and effective compensation can be achieved.
Description
Technical Field
The utility model relates to an aircraft field, concretely relates to aircraft fuel pipeline compensator.
Background
The fuel pipeline compensator is used for displacement compensation during installation of a fuel pipeline of a helicopter aircraft and displacement compensation of the fuel pipeline in the flight process, and provides a fuel circulation channel. Due to the small space in the aircraft, during the installation and butt joint of the fuel system and the pipeline, due to the limitation of space positions and other reasons, the requirements of axial adjusting space and angle compensation are required between two butted fuel pipelines. The pipeline compensator is needed to meet the requirements of installation of a fuel pipeline of an aircraft and adjustment of external factors such as thermal barrier contraction, vibration impact and the like in the working process. Since fuel will pass through the compensator, the compensator must also have the ability to be sealed, explosion proof, and pressure resistant.
Patent CN112856085A discloses a high-reliability high-airtightness and high-temperature-resistance air pipeline compensator, and discloses a mechanism of the air pipeline compensator installed between an auxiliary power system of a helicopter and an air turbine starter, so that functions of axial adjustment and angle adjustment are realized. Even if a slight or minor air leak occurs at the seal, which does not affect the overall flight and safety of the aircraft, for the air line compensator, it is possible that a slight leak may cause safety problems for the fuel line compensator. Therefore, the fuel line compensator must have a wider adjustment space to cope with various external factors, and also have a better sealing performance to prevent leakage.
Disclosure of Invention
For the compensation demand that satisfies the fuel pipeline of aircraft, the utility model aims to provide an aircraft fires oil pipe way compensator.
In order to achieve the above purpose, the utility model adopts the technical proposal that:
the aircraft fuel pipeline compensator comprises a mandrel and a sleeve, wherein the mandrel and the sleeve are hollow pipelines, the sleeve is sleeved on the outer side of one end of the mandrel, the sleeve freely moves along the axis direction of the mandrel, and the ends, far away from the mandrel and the sleeve, of the mandrel and the sleeve are respectively provided with a spherical cavity; an annular sealing groove is processed at the bottom of the matching surface of the first shell and the second shell, a polytetrafluoroethylene sealing ring is installed in the sealing groove, and the sealing ring forms sealing between the rotating shell and the spherical cavity; the sleeve consists of a translation section and a rotation section, annular bulges are arranged at the joints of the translation section and the rotation section, fixed ring sleeves are sleeved outside the pair of annular bulges, and the outer side walls of the pair of annular bulges are wrapped on the two side edges of the fixed ring sleeves; a sealing groove is processed on a matching surface between the pair of annular protrusions, a polytetrafluoroethylene sealing ring is arranged in the sealing groove, and the polytetrafluoroethylene sealing ring forms sealing between the sleeve and the mandrel.
Furthermore, the outer walls of the mandrel and the sleeve are respectively provided with a limiting ring, the first shell and the second shell are distributed on two sides of the highest point of the curved surface of the corresponding spherical cavity in a normal state, and the limiting rings are in limiting fit with the corresponding second shell when the rotating shell rotates; the middle part of the outer side of the mandrel is provided with a sliding chute; the sleeve is sleeved on the end part of one end of the mandrel, and is provided with a limit ring sleeve, the end surface of the limit ring sleeve slides in the sliding groove and is limited by two ends of the sliding groove.
The pipeline connecting part comprises a horizontal butt joint part and a vertical fixing part, the butt joint part is a tubular part matched with the fuel pipeline, a sealing groove is formed in the end face of the butt joint part, and a sealing ring is installed in the sealing groove; the fixing part is positioned on the outer wall of the butt joint part and matched with the hoop.
Furthermore, the sleeve pipe cover is equipped with the round boss in the terminal surface of the one end of dabber, the inner circle of spacing ring cover be equipped with boss complex annular, be equipped with the round connecting hole on the spacing ring cover.
Furthermore, the limit ring sleeve and the fixed ring sleeve are respectively formed by connecting a pair of semicircular ring sleeves.
After taking above technical scheme, the beneficial effects of the utility model are that:
1. the axial expansion compensation of the compensator is realized through the matching of the mandrel and the sleeve, the expansion amount is determined according to the size of a sliding groove on the outer side of the mandrel, and the two ends of the sliding groove are provided with limit positions; the rotating shell is matched with the mandrel and the spherical cavity on the sleeve to realize free rotation of the rotating shell on the outer wall of the spherical cavity, and the rotating angle of the rotating shell is limited by the arrangement of the limiting ring; the arrangement of the telescopic structure and the rotating structure can meet the compensation of the fuel pipeline to the pipeline in the installation adjustment and the use process, and a series of problems of stress concentration, difficult installation in narrow space and the like are avoided.
2. The position that can lead to the fuel leakage in this technical scheme is total everywhere. The first part is an end face of the rotary shell connected with the fuel pipeline, a sealing element is arranged on the end face, and the rotary shell and the fuel pipeline are fixed by utilizing a hoop to prevent leakage; the second part is between the rotating shell and the mandrel, the rotating shell is matched with the outer wall of the spherical cavity of the mandrel, a sealing groove is processed at the bottom of the contact surface of the first shell and the second shell, a sealing ring is arranged in the sealing groove, and the sealing ring can move along with the rotation in the rotating process and prevent the fuel in the mandrel from leaking from the rotating shell; the third place is between the rotary shell and the spherical cavity of the sleeve, and the sealing mode is the same as that of the second place; and the fourth part is between the mandrel and the sleeve, the sleeve is divided into two sections, a sealing groove is processed on the combined end surface of the two sections, a sealing ring is installed on the combined end surface of the two sections, and the sealing ring is sealed between the mandrel and the sleeve and moves along with the expansion, so that the sealing stability is ensured.
3. This technical scheme all adopts the sealing washer of tetrafluoroethylene material in each sealed position, and the sealing washer of this material still possesses the effect of self-lubricating when guaranteeing to seal, can reduce the operating force of various compensations at the in-process that rotates or slide the replenishment, and the resistance when reducing the passive compensation, can effectively compensate.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Detailed Description
The following detailed description of the embodiments of the present invention is made with reference to the accompanying drawings:
as shown, the aircraft fuel line compensator, as part of the fuel communication path, is used for displacement compensation during installation of the fuel line and for displacement compensation of the fuel line under operating conditions. The displacement compensation comprises telescopic compensation along the axial direction of the fuel pipeline, angle compensation when the fuel pipeline is installed or is impacted by vibration, and angular displacement of a certain angle at a joint.
The aircraft fuel pipeline compensator consists of a mandrel 1, a sleeve 2 and a rotating shell 3 arranged on the mandrel and the sleeve. The mandrel 1 and the sleeve 2 are both hollow conduits through which fuel passes. The rotating shell 3 is composed of a first shell 31 and a second shell 32, wherein the end of the first shell 31 is a matched pipeline connecting part connected with the fuel pipeline, and the fuel pipeline and the pipeline connecting part are stably connected by using a hoop 4.
The compensation of the telescoping is achieved by axial movement between the mandrel 1 and the sleeve 2. Sleeve pipe 2 overlaps in the one end of dabber 1, processing has one section spout 11 on the outer wall at dabber 1 middle part, spout 11 is the continuous groove of stepping down, sleeve pipe 2 overlaps and is equipped with round boss 21 on the one end terminal surface of dabber 1, overlap in round spacing ring cover 5 in the outside of boss 21, this spacing ring cover 5 comprises two semicircle ring covers through the screw connection, the inside of spacing ring cover 5 be equipped with boss complex annular, the annular ring of the outside lateral wall of spacing ring cover 5 overlaps in the outer lane of spout 11, the annular ring of the inboard lateral wall of spacing ring cover 5 overlaps in sleeve pipe 2. When the sleeve 2 is displaced relative to the mandrel 1, the outer side wall of the spacing ring sleeve 5 moves in the sliding groove 11 and is limited with two ends of the sliding groove 11 to limit the stroke of telescopic compensation.
Because the mandrel 1 and the sleeve 2 are in sliding fit, when fuel is introduced, the fuel can flow out from a gap between the outer wall of the mandrel 1 and the inner wall of the sleeve 2, and leakage is caused. In order to avoid leakage, the technical scheme divides the sleeve 2 into two sections, annular protrusions 22 extend outwards from the joint end surfaces of the two sections respectively, a sealing groove 23 is machined at the bottom of one of the annular protrusions, a polytetrafluoroethylene sealing ring 24 is installed in the sealing groove, the sealing ring 24 is extruded between the joint surfaces of the two sections and the outer side surface of the sleeve 2, when expansion compensation occurs, the sealing ring 24 moves along with the outer side surface of the mandrel 1, and meanwhile, in the moving stroke range, the sealing ring 24 is always kept on the outer surface of the mandrel 1. The outer sides of the pair of annular protrusions 22 are sleeved with fixing ring sleeves 25, and the two side edges of the fixing ring sleeves 25 are wrapped on the outer sides of the pair of annular protrusions 22 to fix the two sections of the sleeve. The fixed ring sleeve 25 is formed by fixing two semicircular rings through screws to form a whole.
The angle compensation is realized by matching the rotating shell 3 with the corresponding spherical cavity 6, and the angle compensation is arranged at both ends of the aircraft fuel pipeline compensator. That is to say, spherical cavities 6 are respectively arranged at the ends, far away from the mandrel 1 and the sleeve 2, the outer side surfaces of the spherical cavities 6 are partial spherical surfaces, and the rotating shell 3 is arranged at the outer side of each spherical cavity 6. The form of the fit of the swivel housing 3 with the spherical cavity 6 is similar to a ball joint. The end faces of the first housing 31 and the second housing 32, which are matched with each other, extend outward to form flanges, and the first housing and the second housing are fixed by the flanges and bolts to form an integral rotary housing 3. The inner spherical surface of the first shell 31 and the inner spherical surface of the second shell 32 are spliced to form a curved surface matched with the outer wall of the corresponding spherical cavity. In the state of no adjustment, the spherical surface of the first shell 31 and the spherical surface of the second shell 32 are distributed on two sides of the highest point of the outer spherical surface of the spherical cavity, which ensures that the rotating shell 3 cannot fall off the mandrel. The rotating shell 3 can rotate 360 degrees around the axis of the mandrel, and can also be subjected to offset adjustment, namely the axis of the rotating shell 3 forms an included angle with the axis of the mandrel 1 at a certain angle and rotates randomly within the included angle. The mandrel 1 or the sleeve 2 is provided with a limit ring 12, the limit ring 12 is located at the transition connection part of the outer side surface of the spherical cavity 6 and the mandrel 1 or the sleeve 2 and is close to the corresponding second shell 32, and in the rotating process of the rotating shell 3, the edge of the second shell 32 is matched with the corresponding limit ring 12 for limiting, so that the rotating range of the second shell is limited.
Because the fuel enters the mandrel 1 through the pipeline connecting part of the rotating shell 3, in the rotation compensation process, the fuel easily flows out from the gap between the rotating shell 3 and the mandrel 1 or the sleeve 2 to cause leakage, so that effective sealing needs to be formed between the rotating shell and the corresponding spherical cavity. According to the technical scheme, the circle of sealing groove 33 is processed at the bottom of the end face, matched with the first shell 31 and the second shell 32, of the first shell, the sealing ring 34 is installed in the sealing groove 33, the sealing ring 34 is squeezed between the first shell 31 and the second shell 32 and the outer wall of the spherical cavity 6, and is adjusted to rotate at any time to rotate, so that leakage is effectively prevented. The pipeline connecting portion comprises horizontally butt joint portion 35 and vertical fixed part 36, butt joint portion 35 for with the tubulose portion of burning oil pipeline complex, be equipped with the seal groove at the terminal surface of butt joint portion 35, install sealing washer 37 in the seal groove, with burn oil pipeline between form sealed, fixed part 36 on the outer wall of butt joint portion 35 and staple bolt 4 cooperation simultaneously will burn oil pipeline and pipeline connecting portion locking, avoid the butt joint department to take place to leak.
Because this technical scheme's replenisher is passive compensation in the use, takes place the compensation when receiving external force, so the control force or the resistance that the compensation action takes place to should be enough little just can satisfy more sensitive compensation function, consequently the sealing washer of selecting among this technical scheme makes for the tetrafluoroethylene material, still possesses self-lubricating effect when guaranteeing sealed, has reduced the control force greatly.
Claims (5)
1. The aircraft fuel pipeline compensator comprises a mandrel and a sleeve, wherein the mandrel and the sleeve are hollow pipelines, the sleeve is sleeved on the outer side of one end of the mandrel, the sleeve freely moves along the axis direction of the mandrel, and the ends, far away from the mandrel and the sleeve, of the mandrel and the sleeve are respectively provided with a spherical cavity; an annular sealing groove is processed at the bottom of the matching surface of the first shell and the second shell, a polytetrafluoroethylene sealing ring is installed in the sealing groove, and the sealing ring forms sealing between the rotating shell and the spherical cavity; the sleeve consists of a translation section and a rotation section, annular bulges are arranged at the joints of the translation section and the rotation section, fixed ring sleeves are sleeved outside the pair of annular bulges, and the outer side walls of the pair of annular bulges are wrapped on the two side edges of the fixed ring sleeves; a sealing groove is processed on a matching surface between the pair of annular protrusions, a polytetrafluoroethylene sealing ring is arranged in the sealing groove, and the polytetrafluoroethylene sealing ring forms sealing between the sleeve and the mandrel.
2. The aircraft fuel pipeline compensator of claim 1, wherein the outer walls of the mandrel and the sleeve are provided with limiting rings, the first shell and the second shell are distributed on two sides of the highest point of the curved surface of the corresponding spherical cavity in a normal state, and the limiting rings are in limiting fit with the corresponding second shell when the rotating shell rotates; the middle part of the outer side of the mandrel is provided with a sliding chute; the end part of the sleeve sleeved at one end of the mandrel is provided with a limit ring sleeve, and the end surface of the limit ring sleeve slides in the sliding groove and is limited by two ends of the sliding groove.
3. The aircraft fuel pipeline compensator of claim 1, wherein the pipeline connecting part comprises a horizontal butt joint part and a vertical fixing part, the butt joint part is a tubular part matched with the fuel pipeline, a sealing groove is formed in the end face of the butt joint part, and a sealing ring is installed in the sealing groove; the fixing part is positioned on the outer wall of the butt joint part and matched with the hoop.
4. The aircraft fuel pipeline compensator of claim 1, wherein the end surface of the sleeve at one end of the mandrel is provided with a circle of boss, the inner ring of the position-limiting ring sleeve is provided with a ring groove matched with the boss, and the position-limiting ring sleeve is provided with a circle of connecting hole.
5. The aircraft fuel line compensator of claim 4, wherein the spacing collar and the fixed collar are each comprised of a pair of half-collar couplings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222875592.4U CN218378284U (en) | 2022-10-31 | 2022-10-31 | Aircraft fuel pipeline compensator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222875592.4U CN218378284U (en) | 2022-10-31 | 2022-10-31 | Aircraft fuel pipeline compensator |
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| Publication Number | Publication Date |
|---|---|
| CN218378284U true CN218378284U (en) | 2023-01-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202222875592.4U Active CN218378284U (en) | 2022-10-31 | 2022-10-31 | Aircraft fuel pipeline compensator |
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| CN (1) | CN218378284U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116447422A (en) * | 2023-06-19 | 2023-07-18 | 江苏晟楠电子科技股份有限公司 | Fuel pipeline compensator |
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2022
- 2022-10-31 CN CN202222875592.4U patent/CN218378284U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116447422A (en) * | 2023-06-19 | 2023-07-18 | 江苏晟楠电子科技股份有限公司 | Fuel pipeline compensator |
| CN116447422B (en) * | 2023-06-19 | 2023-08-29 | 江苏晟楠电子科技股份有限公司 | Fuel pipeline compensator |
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