CN113983256A - Multi-degree-of-freedom sealing pipeline joint of aircraft engine - Google Patents
Multi-degree-of-freedom sealing pipeline joint of aircraft engine Download PDFInfo
- Publication number
- CN113983256A CN113983256A CN202111212945.6A CN202111212945A CN113983256A CN 113983256 A CN113983256 A CN 113983256A CN 202111212945 A CN202111212945 A CN 202111212945A CN 113983256 A CN113983256 A CN 113983256A
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- China
- Prior art keywords
- spherical surface
- sealing
- pipe joint
- fastening block
- pipe
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- 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
- 238000007789 sealing Methods 0.000 title claims abstract description 55
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
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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
Abstract
The invention relates to a multi-degree-of-freedom sealing pipeline joint of an aircraft engine, which comprises a flat nozzle, a full-spherical pipe joint, a flat nozzle fastening block and an additional nut; the pipe joint is full spherical, the front end of the pipe joint is provided with a bell mouth, and the spherical surface of the pipe joint is a sealing surface; the fastening block is spherical and is provided with an inner mounting edge spherical surface; the sealing pipe joint arranged at the front end of the flat pipe nozzle is hemispherical, the inner spherical surface of the sealing pipe joint is a concentric sealing surface, and the outer spherical surface is matched with the concentric spherical surface of the fastening block; the fastening block is sleeved on the outer spherical surface of the sealing pipe joint of the flat pipe nozzle, and the spherical surface on the front side of the pipe joint is matched with the inner spherical surface of the flat pipe nozzle to form a spherical sealing strip; the external nut is sleeved on the fastening block and the pipe joint, the rear spherical surface of the pipe joint is matched with the inner spherical surface at the upper end of the external nut, and the inner spherical surface at the lower end of the external nut is matched with the outer spherical surface of the fastening block, so that the screwing torque is converted into the concentric force. The invention can reduce the assembly stress of the conduit to the minimum, thereby reducing the dynamic stress level of the pipeline and ensuring the safe and reliable work of the pipeline.
Description
Technical Field
The invention relates to the technical field of aeroengine pipeline joints, in particular to a multi-degree-of-freedom sealing pipeline joint of an aeroengine.
Background
Aeroengine pipe joint is generally by bayonet structure, awl to ball joint and awl to the awl structure, and current pipe joint structure all needs the pipe joint both ends to have higher axiality, and then can realize the assembly, guarantees sealed effect. However, once a certain deviation exists at the two ends of the pipeline joint, such as the axial size deviation or the angular deviation of the pipe joint, the pipeline cannot be assembled, the engine guide pipe needs to be taken down and corrected, the assembly time of the engine is prolonged, meanwhile, the sealing performance of the pipeline cannot be guaranteed, and the problem of pipeline sealing failure can occur with a high probability.
Disclosure of Invention
The invention aims to provide a multi-degree-of-freedom sealing pipeline joint of an aircraft engine, which has the following specific scheme:
a multi-degree-of-freedom sealing pipeline joint of an aircraft engine comprises a flat nozzle, a pipe joint, a fastening block and an additional nut;
the pipe joint is of a full-spherical shape, the front end of the pipe joint is provided with a bell mouth, and the spherical surface of the pipe joint is a sealing surface;
the fastening block is spherical and is provided with an inner mounting edge spherical surface;
the sealing pipe joint arranged at the front end of the flat pipe nozzle is hemispherical, the inner spherical surface of the sealing pipe joint is a concentric sealing surface, and the outer spherical surface is matched with the concentric spherical surface of the fastening block;
the fastening block is sleeved on the outer spherical surface of the sealing pipe connector of the flat pipe nozzle, and the spherical surface on the front side of the pipe connector is matched with the inner spherical surface of the flat pipe nozzle to form a spherical sealing strip;
the external nut is sleeved on the fastening block and the pipe joint, the rear spherical surface of the pipe joint is matched with the inner spherical surface at the upper end of the external nut, and the inner spherical surface at the lower end of the external nut is matched with the outer spherical surface of the fastening block, so that the screwing torque is converted into the concentric force.
The optimized scheme of the multi-degree-of-freedom sealing pipeline joint for the aircraft engine is that the spherical size of the sealing pipe joint is longer than that of the mounting edge in the fastening block.
The optimized scheme of the aircraft engine multi-degree-of-freedom sealed pipeline joint is that a gap is formed between the sealed pipe joint and the fastening block before fastening, so that the whole structure can rotate around the circle center in a small range, and the angle deviation of one side of the flat pipe joint is adapted.
The preferable scheme of the aircraft engine multi-degree-of-freedom sealing pipeline joint is that the outer spherical surface of the sealing pipe joint of the plain pipe nozzle, the inner spherical surface of the sealing pipe joint of the plain pipe nozzle, the spherical surface of the pipe joint and the spherical surface of the mounting edge in the fastening block are concentric sealing surfaces and are used for ensuring that the tightening torque forms axial force along the radius direction.
Compared with the prior art, the invention has the beneficial effects that:
the pipeline joint structure designed by the invention can contain the radial deviation and the axial angle deviation of the guide pipe, can ensure the sealing performance, and can reduce the assembly stress of the guide pipe to the minimum, thereby reducing the dynamic stress level of the pipeline, ensuring the safe and reliable work of the pipeline, and meeting the assembly requirement of the external pipeline of the aircraft engine. Meanwhile, by adopting the structure of the invention, one line or surface of the original structure can be sealed, and the sealing is increased to three lines or surfaces, so that the sealing reliability of the pipe joint is improved.
Drawings
FIG. 1 is a schematic view of a joint structure of a common pipeline of an aircraft engine;
FIG. 2 is a schematic diagram of the sealing positioning of the conventional pipe joint of FIG. 1;
FIG. 3 is a schematic view of an angular deviation of a conventional pipe joint;
FIG. 4 is a schematic structural view of the present invention;
FIG. 5 is a schematic view of a full spherical pipe joint with a bell mouth according to the present invention;
FIG. 6 is a schematic view of the seal positioning of the line connection of the present invention;
FIG. 7 is a schematic diagram of angular deflection of one side of a double spherical flat nozzle in an application example;
FIG. 8 is a schematic view of one side angular misalignment of a receptacle for a flared, fully spherical pipe joint in an example application;
FIG. 9 is a schematic view of angular misalignment of a female two-sided pipe joint in an example application.
In the figure, 1-flat nozzle, 2-pipe joint, 3-fastening block, 4-additional nut, 5-bell mouth, 6-internal installation edge spherical surface, 7-internal spherical surface, 8-external spherical surface, 9-sealing pipe nozzle, 10-concentric force, 11-gap and 12-axial force.
Detailed Description
The technical solutions in the present invention will be described clearly and completely with reference to the accompanying drawings, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The specific implementation mode is as follows:
a multi-degree-of-freedom sealing pipeline joint of an aircraft engine comprises a flat nozzle 1, a pipe joint 2, a fastening block 3 and an additional nut 4;
the pipe joint 2 is of a full-spherical shape, the front end of the pipe joint is provided with a bell mouth 5, and the spherical surface of the pipe joint is a sealing surface;
the fastening block 3 is spherical and is provided with an inner mounting edge spherical surface 6;
a sealing pipe joint nozzle 9 arranged at the front end of the flat pipe nozzle 1 is hemispherical, the inner spherical surface 7 of the sealing pipe joint nozzle is a concentric sealing surface, and an outer spherical surface 8 is matched with the concentric spherical surface of the fastening block;
the fastening block 3 is sleeved on an outer spherical surface 8 of a sealing pipe joint nozzle 9 of the flat pipe nozzle 1, and a spherical surface on the front side of the pipe joint 2 is matched with an inner spherical surface 7 of the flat pipe nozzle to form a spherical surface sealing strip;
the external nut 4 is sleeved on the fastening block 3 and the pipe joint 2, the rear spherical surface of the pipe joint is matched with the inner spherical surface at the upper end of the external nut 4, and the inner spherical surface at the lower end of the external nut 4 is matched with the outer spherical surface of the fastening block 3, so that the screwing torque is converted into the concentric force 10.
The spherical surface size of the sealing pipe connector 9 is longer than that of the mounting side spherical surface 6 in the fastening block.
The sealing pipe nozzle 9 and the fastening block 3 are provided with a gap 11 before fastening, so that the whole structure can rotate around the circle center in a small range, and the sealing pipe nozzle is suitable for angular deviation on one side of the flat pipe nozzle 1.
The outer spherical surface 8 of the sealing pipe nozzle 9 of the flat pipe nozzle 1, the inner spherical surface 7 of the sealing pipe nozzle 9 of the flat pipe nozzle 1, the spherical surface of the pipe joint 2 and the spherical surface 6 of the inner mounting edge of the fastening block 3 are concentric sealing surfaces and are used for ensuring that the tightening torque forms axial force 12 along the radius direction.
Claims (4)
1. The utility model provides an aeroengine multi freedom sealed pipeline connects which characterized in that: comprises a flat nozzle, a pipe joint, a flat nozzle fastening block and an additional nut;
the pipe joint is of a full-spherical shape, the front end of the pipe joint is provided with a bell mouth, and the spherical surface of the pipe joint is a sealing surface;
the fastening block is spherical and is provided with an inner mounting edge spherical surface;
the sealing pipe joint arranged at the front end of the flat pipe nozzle is hemispherical, the inner spherical surface of the sealing pipe joint is a concentric sealing surface, and the outer spherical surface is matched with the concentric spherical surface of the fastening block;
the fastening block is sleeved on the outer spherical surface of the sealing pipe connector of the flat pipe nozzle, and the spherical surface on the front side of the pipe connector is matched with the inner spherical surface of the flat pipe nozzle to form a spherical sealing strip;
the external nut is sleeved on the fastening block and the pipe joint, the rear spherical surface of the pipe joint is matched with the inner spherical surface at the upper end of the external nut, and the inner spherical surface at the lower end of the external nut is matched with the outer spherical surface of the fastening block, so that the screwing torque is converted into the concentric force.
2. The aircraft engine multi-degree-of-freedom sealed pipeline joint as claimed in claim 1, wherein: the spherical size of the sealing pipe joint is longer than that of the mounting edge in the fastening block.
3. The aircraft engine multi-degree-of-freedom sealed pipeline joint as claimed in claim 1, wherein: a gap is formed between the sealing pipe nozzle and the fastening block before fastening, so that the integral structure can rotate around the circle center in a small range, and the angular deviation of one side of the flat pipe nozzle is adapted.
4. The aircraft engine multi-degree-of-freedom sealed pipeline joint as claimed in claim 1, wherein: the outer spherical surface of the sealing pipe connector of the flat pipe nozzle, the inner spherical surface of the sealing pipe connector of the flat pipe nozzle, the spherical surface of the pipe connector and the spherical surface of the mounting edge in the fastening block are concentric sealing surfaces and are used for ensuring that the tightening torque forms axial force along the radius direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111212945.6A CN113983256A (en) | 2021-10-18 | 2021-10-18 | Multi-degree-of-freedom sealing pipeline joint of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111212945.6A CN113983256A (en) | 2021-10-18 | 2021-10-18 | Multi-degree-of-freedom sealing pipeline joint of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113983256A true CN113983256A (en) | 2022-01-28 |
Family
ID=79739188
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111212945.6A Pending CN113983256A (en) | 2021-10-18 | 2021-10-18 | Multi-degree-of-freedom sealing pipeline joint of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113983256A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE821890C (en) * | 1949-04-26 | 1951-11-22 | Karl Peter May | Pipe joint |
| CN202001754U (en) * | 2011-04-07 | 2011-10-05 | 河南大指造纸装备集成工程有限公司 | Double-spherical-surface pipe joint |
| CN210318954U (en) * | 2019-06-25 | 2020-04-14 | 山东康格能源科技有限公司 | Pipeline turns to connecting device |
| CN113374960A (en) * | 2021-06-18 | 2021-09-10 | 中国航发沈阳发动机研究所 | Pipeline connecting structure with angle compensation |
-
2021
- 2021-10-18 CN CN202111212945.6A patent/CN113983256A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE821890C (en) * | 1949-04-26 | 1951-11-22 | Karl Peter May | Pipe joint |
| CN202001754U (en) * | 2011-04-07 | 2011-10-05 | 河南大指造纸装备集成工程有限公司 | Double-spherical-surface pipe joint |
| CN210318954U (en) * | 2019-06-25 | 2020-04-14 | 山东康格能源科技有限公司 | Pipeline turns to connecting device |
| CN113374960A (en) * | 2021-06-18 | 2021-09-10 | 中国航发沈阳发动机研究所 | Pipeline connecting structure with angle compensation |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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Application publication date: 20220128 |