CN104121440A - High-temperature pipeline connecting structure on plane - Google Patents
High-temperature pipeline connecting structure on plane Download PDFInfo
- Publication number
- CN104121440A CN104121440A CN201310152633.XA CN201310152633A CN104121440A CN 104121440 A CN104121440 A CN 104121440A CN 201310152633 A CN201310152633 A CN 201310152633A CN 104121440 A CN104121440 A CN 104121440A
- Authority
- CN
- China
- Prior art keywords
- flange plate
- joint
- spherical
- flared
- horn
- 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.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L27/00—Adjustable joints, Joints allowing movement
- F16L27/02—Universal joints, i.e. with mechanical connection allowing angular movement or adjustment of the axes of the parts in any direction
- F16L27/04—Universal joints, i.e. with mechanical connection allowing angular movement or adjustment of the axes of the parts in any direction with partly spherical engaging surfaces
- F16L27/053—Universal joints, i.e. with mechanical connection allowing angular movement or adjustment of the axes of the parts in any direction with partly spherical engaging surfaces held in place by bolts passing through flanges
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L51/00—Expansion-compensation arrangements for pipe-lines
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Joints Allowing Movement (AREA)
Abstract
The invention belongs to the technical field of aviation, and relates to a connecting structure of high-temperature pipelines. According to the structure, one end of a spherical connector (1) is welded to a left guide pipe, a spherical head part at the other end of the spherical connector (1) is arranged in a horn-opening-shaped in one end of a horn-opening-shaped connector (4), the other end of the horn-opening-shaped connector (4) is welded to a right guide pipe, a movable first flange plate (2) is installed on the spherical connector (1), and an inner ring of the first flange plate (2) is shaped like a spherical surface, is matched with the outer surface of the spherical connector (1) and can rotate; a movable second flange plate (3) is installed on the horn-opening-shaped connector (4), an inner ring of the second flange plate (3) is shaped like a horn opening and is matched with the outer surface of the horn-opening-shaped connector (4), and the first flange plate (2) and the second flange plate (3) are connected through screws (5). The connecting structure adopts a combined design, the spherical connector (1) rotates in the horn-opening-shaped connector (4), a certain inclined installation angle is permitted, construction is convenient, and the thermal expansion amount of the pipelines can be compensated for limitedly.
Description
Technical field
The invention belongs to aeronautical technology field, relate to a kind of linkage structure for high temperature conduit.
Background technique
Aircraft compared with the high temperature air delivering pipeline of Large Diameter Pipeline in, metal tubes connects conventionally employing male-female joint together with the linkage structure of High-Temperature Quick-Release Clamp, the sealing of this form in order to ensure that pipeline connects, the fit tolerance to part processing and installation coaxality are had relatively high expectations.Meanwhile, at fitting surface place protruding, female fitting, need to install graphite grazing packing ring, this packing ring is fragile in removing and returning process of assembling, need have the random spare part of some, and the maintenance difficulty of aircraft is increased, and cost improves.
Summary of the invention
The object of the invention is to propose a kind of pipeline jointing construction of simple in structure, easy for installation, good airproof performance, and can play certain pipeline temperature compensation function.
Technical solution of the present invention is that the high temperature conduit linkage structure on a kind of aircraft, comprises spherical joint 1, the first flange plate 2, the second flange plate 3, flared joint 4 and screw 5; Wherein, one end of spherical joint 1 and the welding of left conduit, the other end ball head is placed in the horn mouth of flared joint 4 one end, the other end of flared joint 4 and the welding of right conduit, the first movable flange plate 2 is installed on spherical joint 1, the first flange plate 2 inner rings are spheric, coordinate with spherical joint 1 outer surface, and rotatable, the second movable flange plate 3 is installed on flared joint 4, the second flange plate 3 inner rings are toroidal, coordinate with flared joint 4 outer surfaces, and the first flange plate 2 is connected by screw 5 with the second flange plate 3.
Further, screw 5 is connected with the tapped hole of the second flange plate 3 by the through hole on the first flange plate 2.
Described spherical joint 1 can be around 360 ° of rotations of spherical joint 1 pipeline central shaft in flared joint 4.
Described flared joint 4 can be around 360 ° of rotations of flared joint 4 pipeline central shaft on spherical joint 1.
The axis of the axis of described spherical joint 1 and flared joint 4 can be within the scope of-3 ° to+3 ° deflection.
Described spherical joint 1 is together with the first flange plate 2, and together with the symmetrical installation of the second flange plate 3, position, left and right is installed can phase double replacement with flared joint 4.
The advantage that the present invention has and beneficial effect are:
1. adopt Combination Design, spherical joint 1, in the interior rotation of flared joint 4, has allowed a certain amount of inclined installation angle, easy construction, and can limited compensation conduit heat expansion amount of deformation;
2. joint is round wire sealing, good airproof performance;
3. adopt metal joint, long service life;
4. simple in structure, while production in a large number, characteristic variations is little.
Brief description of the drawings
Fig. 1 is connection diagram of the present invention, in figure: spherical joint 1, the first flange plate 2, the second flange plate 3, flared joint 4, screw 5;
Fig. 2 is scheme of installation of the present invention, in figure: left conduit 6, right conduit 7
Embodiment
Below in conjunction with accompanying drawing, the present invention is elaborated.
The welding of the left end of spherical joint 1 and left conduit, right-hand member ball head is placed in the horn mouth of flared joint 4 left ends, and the right-hand member of flared joint 4 welds with right conduit.The first movable flange plate 2 is installed on spherical joint 1, and its inner ring is spheric, fully suits with spherical joint 1 outer surface, and rotatable, the second movable flange plate 3 is installed on flared joint 4, and its inner ring is toroidal, fully suits with flared joint 4 outer surfaces.The screw 5 of border passes through the through hole of the first flange plate 2, and is connected with the tapped hole of the second flange plate 3.
The first flange plate 2 and the second flange plate 3 are under the screwing force effect of screw 5, screwing force is delivered to the outer surface of spherical joint 1 and flared joint 4, then make ball head divide outer surface and horn mouth internal surface closely to suit, the sealing of formation round wire, thus prevent from managing interior high-temperature gas to external leakage.
Embodiment
The left end of spherical joint 1 and left conduit 6 weld, right-hand member ball head is placed in the horn mouth of flared joint 4 left ends, the right-hand member of flared joint 4 and right conduit 7 weld, the first movable flange plate 2 is installed on spherical joint 1, the second movable flange plate 3 is installed on flared joint 4, after connecting by screw 5 between the first flange plate 2 and the second flange plate 3, bulb outer surface and horn mouth internal surface are closely suited, thereby left conduit 6 and right conduit 7 are connected together.
When the right-hand member bulb part of spherical joint 1 is rotated in the horn mouth of flared joint 4 left ends, both axis are within the scope of-3 ° to+3 ° when deflection, can ensure that contacting point forms round wire sealing, simultaneously, if while there is left conduit 6 and right conduit 7 heat expansion phenomenon, joint is by absorbing angular displacement, and the left conduit 6 of effective compensation and right conduit 7 linear displacement, avoid conduit to be destroyed to a certain extent.
Claims (5)
1. the high temperature conduit linkage structure on aircraft, is characterized in that, this structure comprises spherical joint (1), the first flange plate (2), the second flange plate (3), flared joint (4) and screw (5), wherein, one end of spherical joint (1) and the welding of left conduit, the other end ball head is placed in the horn mouth of flared joint (4) one end, the other end of flared joint (4) and the welding of right conduit, movable the first flange plate (2) is installed on spherical joint (1), the first flange plate (2) inner ring is spheric, coordinate with spherical joint (1) outer surface, and rotatable, movable the second flange plate (3) is installed on flared joint (4), the second flange plate (3) inner ring is toroidal, coordinate with flared joint (4) outer surface, the first flange plate (2) is connected by screw (5) with the second flange plate (3).
2. the high temperature conduit linkage structure on a kind of aircraft as described in claim (1), is characterized in that, screw (5) is connected with the tapped hole of the second flange plate (3) by the through hole on the first flange plate (2).
3. the high temperature conduit linkage structure on a kind of aircraft as described in claim (1), is characterized in that, described spherical joint (1) can be around 360 ° of rotations of spherical joint (1) pipeline central shaft in flared joint (4).
4. the high temperature conduit linkage structure on a kind of aircraft as described in claim (1), is characterized in that, described flared joint (4) can be upper around 360 ° of rotations of flared joint (4) pipeline central shaft at spherical joint (1).
5. the high temperature conduit linkage structure on a kind of aircraft as described in one of claim (1)-(4), is characterized in that, the axis of the axis of described spherical joint (1) and flared joint (4) can be within the scope of-3 ° to+3 ° deflection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310152633.XA CN104121440A (en) | 2013-04-27 | 2013-04-27 | High-temperature pipeline connecting structure on plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310152633.XA CN104121440A (en) | 2013-04-27 | 2013-04-27 | High-temperature pipeline connecting structure on plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104121440A true CN104121440A (en) | 2014-10-29 |
Family
ID=51766980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310152633.XA Pending CN104121440A (en) | 2013-04-27 | 2013-04-27 | High-temperature pipeline connecting structure on plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104121440A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105135110A (en) * | 2015-08-12 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Flexible compensation pipeline connecting device |
| CN106090511A (en) * | 2016-08-05 | 2016-11-09 | 洛阳双瑞特种装备有限公司 | A kind of clamped-in style attachment structure for titanium bellows expansion joint |
| CN106439294A (en) * | 2016-10-13 | 2017-02-22 | 新昌县开铭制冷配件有限公司 | Adapter seat for air conditioner cooling pipes |
| CN110153381A (en) * | 2019-06-14 | 2019-08-23 | 上海交通大学 | Variable-angle tubular type molten aluminum conveying device |
| CN111237083A (en) * | 2018-11-28 | 2020-06-05 | 海鹰航空通用装备有限责任公司 | Combined spray pipe structure and airplane with same |
| CN112178320A (en) * | 2020-10-17 | 2021-01-05 | 泉州台商投资区双霞机械设计服务中心 | Corrugated pipe and connecting structure |
| CN113108135A (en) * | 2021-03-26 | 2021-07-13 | 陕西飞机工业有限责任公司 | Arc-shaped butt joint vent conduit for airplane and manufacturing method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB457357A (en) * | 1935-09-10 | 1936-11-26 | Bromford Tube Company Ltd | Improvements relating to pipe joints |
| DE2655473A1 (en) * | 1976-12-08 | 1978-06-22 | Jenaer Glaswerk Schott & Gen | Variable angle flanged pipe coupling - has one flange with two concentric cone faces acting against convex one |
| US4519639A (en) * | 1983-07-01 | 1985-05-28 | Nickson Industries, Inc. | Hinged flange for tailpipes and the like |
| EP0717225A1 (en) * | 1994-12-14 | 1996-06-19 | Mercedes-Benz Ag | Coupling device for two tubular elements |
| DE19608870C1 (en) * | 1996-03-07 | 1997-10-23 | Daimler Benz Ag | Vehicle internal combustion engine exhaust gas conduit insert |
| CN101576185A (en) * | 2009-05-27 | 2009-11-11 | 嘉利特荏原泵业有限公司 | Universal rotating fluid pipeline |
| CN103201550A (en) * | 2010-11-08 | 2013-07-10 | 德地氏加工***有限公司 | Pipeline, sealing element and pipe connection |
-
2013
- 2013-04-27 CN CN201310152633.XA patent/CN104121440A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB457357A (en) * | 1935-09-10 | 1936-11-26 | Bromford Tube Company Ltd | Improvements relating to pipe joints |
| DE2655473A1 (en) * | 1976-12-08 | 1978-06-22 | Jenaer Glaswerk Schott & Gen | Variable angle flanged pipe coupling - has one flange with two concentric cone faces acting against convex one |
| US4519639A (en) * | 1983-07-01 | 1985-05-28 | Nickson Industries, Inc. | Hinged flange for tailpipes and the like |
| EP0717225A1 (en) * | 1994-12-14 | 1996-06-19 | Mercedes-Benz Ag | Coupling device for two tubular elements |
| DE19608870C1 (en) * | 1996-03-07 | 1997-10-23 | Daimler Benz Ag | Vehicle internal combustion engine exhaust gas conduit insert |
| CN101576185A (en) * | 2009-05-27 | 2009-11-11 | 嘉利特荏原泵业有限公司 | Universal rotating fluid pipeline |
| CN103201550A (en) * | 2010-11-08 | 2013-07-10 | 德地氏加工***有限公司 | Pipeline, sealing element and pipe connection |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105135110A (en) * | 2015-08-12 | 2015-12-09 | 中国航空工业集团公司西安飞机设计研究所 | Flexible compensation pipeline connecting device |
| CN106090511A (en) * | 2016-08-05 | 2016-11-09 | 洛阳双瑞特种装备有限公司 | A kind of clamped-in style attachment structure for titanium bellows expansion joint |
| CN106439294A (en) * | 2016-10-13 | 2017-02-22 | 新昌县开铭制冷配件有限公司 | Adapter seat for air conditioner cooling pipes |
| CN111237083A (en) * | 2018-11-28 | 2020-06-05 | 海鹰航空通用装备有限责任公司 | Combined spray pipe structure and airplane with same |
| CN110153381A (en) * | 2019-06-14 | 2019-08-23 | 上海交通大学 | Variable-angle tubular type molten aluminum conveying device |
| CN112178320A (en) * | 2020-10-17 | 2021-01-05 | 泉州台商投资区双霞机械设计服务中心 | Corrugated pipe and connecting structure |
| CN113108135A (en) * | 2021-03-26 | 2021-07-13 | 陕西飞机工业有限责任公司 | Arc-shaped butt joint vent conduit for airplane and manufacturing method thereof |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20141029 |