CN216408059U

CN216408059U - Clamping and pressing type special alloy stainless steel flange for manufacturing aircraft

Info

Publication number: CN216408059U
Application number: CN202123141645.1U
Authority: CN
Inventors: 苏同卫
Original assignee: Taizhou Jiale Metal Products Co ltd
Current assignee: Taizhou Jiale Metal Products Co ltd
Priority date: 2021-12-14
Filing date: 2021-12-14
Publication date: 2022-04-29
Anticipated expiration: 2031-12-14

Abstract

The utility model discloses a clamping and pressing type special alloy stainless steel flange for manufacturing an aircraft, which comprises an outer flange clamping sleeve, an upper ear clamping buckle, an inner closed pipeline ring, a lower pipeline clamping hook and a lower ear clamping buckle, wherein the outer flange clamping sleeve is divided into a left clamping part and a right clamping part, the upper ear clamping buckle is arranged above each part, and the lower ear clamping buckle is arranged below each part.

Description

Clamping and pressing type special alloy stainless steel flange for manufacturing aircraft

Technical Field

The utility model relates to the technical field of stainless steel flanges, in particular to a clamping and pressing type special alloy stainless steel flange for manufacturing an aircraft.

Background

The flange connection is that two pipelines, pipe fittings or equipment are respectively fixed on a flange plate, a flange pad is added between the two flange plates and fastened together by bolts, and the connection is completed. Some pipe fittings and equipment are provided with flanges, and the flange connection is also the object of flange connection. The flange connection is an important connection mode for pipeline construction. The flange connection is convenient to use and can bear larger pressure.

The utility model provides a clamping and pressing type special alloy stainless steel flange for manufacturing an aircraft, which is used for solving the problems that the existing flange for manufacturing the aircraft has the problems of complicated connection between the flange and an aircraft pipeline and untight clamping and pressing.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a clamping and pressing type special alloy stainless steel flange for manufacturing an aircraft, which aims to solve the problems in the background technology.

In order to achieve the purpose, the utility model provides the following technical scheme: the clamping and pressing type special alloy stainless steel flange for manufacturing the aircraft comprises an outer flange clamping sleeve, an upper lug buckle, an inner closed pipeline ring, a lower pipeline clamping hook and a lower lug buckle, wherein the upper part of the outer flange clamping sleeve is welded with the upper lug buckle, the upper lug buckle is in threaded connection with a fixing bolt, the lower part of the outer flange clamping sleeve is welded with the lower lug buckle, the lower lug buckle is in threaded connection with the fixing bolt, the inner surface of the outer flange clamping sleeve is fixedly connected with the outer surface of the inner closed pipeline ring, and the inner part of the inner closed pipeline ring is connected with the aviation pipeline clamping hook.

Preferably, both ends of the fixing bolt are in threaded connection with the fixing nut, and the upper lug buckle and the lower lug buckle are located on the same axis.

Preferably, the material of upper ear buckle is metal stainless steel, two part clearance departments fill rubber seal on the left and right sides of flange outer cutting ferrule.

Preferably, the inner surface of the flange outer cutting sleeve is provided with a clamping groove, and the outer surface of the inner closed pipeline ring is fixedly connected with the gear bulge.

Preferably, the outer surface of the aviation pipeline is provided with an upper pipeline clamping hook, and the interior of the aviation pipeline is glued with the pipeline oxidation resistant film.

Preferably, the upper pipeline hook is connected with the inner surface hook of the flange outer cutting sleeve, and the lower pipeline hook is arranged below the upper pipeline hook.

Preferably, the inner closed pipeline ring, the aviation pipeline and the flange outer clamping sleeve are positioned on the same axis, and the lower pipeline clamping hook is of an inverted T-shaped structure.

Compared with the prior art, the utility model has the beneficial effects that:

1. the device comprises an outer flange clamping sleeve, an upper ear clamping buckle, a fixing bolt, an inner closed pipeline ring, an aviation pipeline, a lower ear clamping buckle, a threaded through hole, a rubber sealing gasket and a fixing nut, wherein the outer flange clamping sleeve is divided into a left clamping part and a right clamping part;

2. according to the utility model, the pipeline oxidation-resistant film is attached to the interior of the aircraft pipeline through the mutual matching of the pipeline oxidation-resistant film and the aircraft pipeline, so that the internal oxidation corrosion of the aircraft pipeline is effectively prevented, and the service life of the aircraft pipeline of the device is prolonged;

3. the utility model is characterized in that the gear bulge, the upper pipeline hook, the lower pipeline hook, the inner closed pipeline ring and the aviation pipeline are mutually matched, and the connection mode between the inner closed pipeline ring and the aviation pipeline is as follows: be equipped with upper pipe pothook and lower pipeline pothook on the aircraft duct surface, be equipped with the draw-in groove that corresponds in the inside of interior closed pipe ring, on the basis of veneer between interior closed pipe ring and the aircraft duct, the mutual pothook of rethread upper pipe pothook, lower pipeline pothook is connected, improves the compactness that two parts are connected, improves device stability.

Drawings

FIG. 1 is a schematic perspective view of a flange according to the present invention;

FIG. 2 is a sectional view of the internal structure of the flange of the present invention;

fig. 3 is a cross-sectional view of a flange of the present invention.

In the figure: the flange outer cutting ferrule 1, the upper ear buckle 2, the fixing bolt 3, the inner closed pipeline ring 4, the aviation pipeline 5, the gear bulge 6, the upper pipeline buckle 7, the lower pipeline hook 8, the lower ear buckle 9, the thread through hole 10, the rubber sealing gasket 11, the pipeline antioxidant film 12 and the fixing nut 13.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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.

Referring to fig. 1-3, the present invention provides a technical solution: the utility model provides a special alloy stainless steel flange of card pressure formula for aircraft manufacturing, including flange outer cutting ferrule 1, go up ear buckle 2, interior closed pipeline ring 4 and lower pipeline pothook 8, lower ear buckle 9, the top and the last ear buckle 2 welding of flange outer cutting ferrule 1, go up

ear buckle

2 and 3 threaded connection of fixing bolt, the below and the lower ear buckle 9 welding of flange outer cutting ferrule 1, lower ear buckle 9 and 3 threaded connection of fixing bolt, the internal surface of flange outer cutting ferrule 1 and the surface fixed connection of interior closed pipeline ring 4, the inside and the 5 pothooks of aviation pipeline of interior closed pipeline ring 4 are connected.

Furthermore, the two ends of the fixing bolt 3 are in threaded connection with the fixing nut 13, the upper lug fastener 2 and the lower lug fastener 9 are located on the same axis, the upper lug fastener 2 and the lower lug fastener 9 are arranged above and below the two parts of clamping pieces of the flange outer clamping sleeve 1, and the flange outer clamping sleeve 1 achieves clamping and pressing type locking on the internal aerial pipeline 5 through the two parts of clamping pieces.

Furthermore, the upper lug buckle 2 is made of stainless steel, and the rubber sealing gasket 11 is filled in the gap between the left part and the right part of the flange outer clamping sleeve 1, so that the shock absorption performance of the flange of the device is improved, and the tightness of the device is improved.

Furthermore, the inner surface of the flange outer cutting sleeve 1 is provided with a clamping groove, the outer surface of the inner closed pipeline ring 4 is fixedly connected with the gear bulge 6, and the outer surface of the inner closed pipeline ring 4 is meshed with the flange outer cutting sleeve 1 through the gear bulge 6, so that the stability is improved.

Further, the surface of aviation pipeline 5 is equipped with pipeline pothook 7, and the inside of aviation pipeline 5 glues with pipeline oxidation-resistant membrane 12, and the inside laminating of aviation pipeline 5 has pipeline oxidation-resistant membrane 12, and the effectual inside oxidation that prevents aviation pipeline 5 corrodes, improves device aviation pipeline 5's life.

Further, go up pipeline pothook 7 and flange outer cutting ferrule 1's internal surface pothook and be connected, go up pipeline pothook 8 under the below installation of pipeline pothook 7, on the basis of veneer between interior closed pipeline ring 4 and the aviation pipeline 5, pipeline pothook 7, the mutual pothook connection of lower pipeline pothook are gone up to the rethread, improve the compactness that two parts are connected.

Further, interior closed pipeline ring 4, aviation pipeline 5 and flange outer cutting ferrule 1 are in same axis, and lower pipeline pothook 8 is the type of falling T structure, be favorable to lower pipeline pothook 8 better with the inside block of aviation pipeline 5.

The working principle is as follows: firstly, a flange outer cutting sleeve 1 is divided into a left clamping part and a right clamping part, an upper ear buckle 2 is arranged above each part, and a lower ear buckle 9 is arranged below each part, the device is used for clamping an inner closed pipeline ring 4 inside the flange outer cutting sleeve 1, the two upper ear buckles 2 are connected through a fixing bolt 3, similarly, the two lower ear buckles 9 are also connected through the fixing bolt 3, after the flange outer cutting sleeve 1 locks the inner closed pipeline ring 4, an aviation pipeline 5 is arranged inside the inner closed pipeline ring 4, and the flange outer cutting sleeve 1 realizes the clamping and pressing type locking of the inner aviation pipeline 5 through the two clamping parts, so that the practicability of the device is improved; secondly, the utility model is characterized in that the gear bulge 6, the upper pipeline hook 7, the lower pipeline hook 8, the inner closed pipeline ring 4 and the aviation pipeline 5 are mutually matched, and the connection mode between the inner closed pipeline ring 4 and the aviation pipeline 5 is as follows: be equipped with upper pipe pothook 7 and lower pipe pothook 8 on the surface of aircraft duct 5, be equipped with the draw-in groove that corresponds in the inside of interior closed pipe ring 4, on the basis of veneer between interior closed pipe ring 4 and the aircraft duct 5, the mutual pothook of rethread upper pipe pothook 7, lower pipe pothook 8 is connected, improves the compactness that two parts are connected, improves device stability.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a special alloy stainless steel flange of card pressure formula for aircraft manufacturing, includes flange outer cutting ferrule (1), upper ear buckle (2), interior closed pipeline ring (4) and lower pipeline pothook (8), lower ear buckle (9), characterized in that, the top and the upper ear buckle (2) welding of flange outer cutting ferrule (1), upper ear buckle (2) and fixing bolt (3) threaded connection, the below and the lower ear buckle (9) welding of flange outer cutting ferrule (1), lower ear buckle (9) and fixing bolt (3) threaded connection, the internal surface and the outer surface fixed connection of interior closed pipeline ring (4) of flange outer cutting ferrule (1), the inside and the aviation pipeline (5) pothook of interior closed pipeline ring (4) are connected.

2. The aircraft manufacturing special alloy stainless steel clamping-pressing flange according to claim 1, is characterized in that: the two ends of the fixing bolt (3) are in threaded connection with the fixing nut (13), and the upper lug buckle (2) and the lower lug buckle (9) are located on the same axis.

3. The aircraft manufacturing special alloy stainless steel clamping-pressing flange according to claim 1, is characterized in that: go up the material of ear buckle (2) and be metal stainless steel, two part clearance departments fill rubber packing pad (11) about flange outer cutting ferrule (1).

4. The aircraft manufacturing special alloy stainless steel clamping-pressing flange according to claim 1, is characterized in that: the inner surface of the flange outer cutting sleeve (1) is provided with a clamping groove, and the outer surface of the inner closed pipeline ring (4) is fixedly connected with the gear bulge (6).

5. The aircraft manufacturing special alloy stainless steel clamping-pressing flange according to claim 1, is characterized in that: the outer surface of the aviation pipeline (5) is provided with an upper pipeline clamping hook (7), and the interior of the aviation pipeline (5) is glued with the pipeline anti-oxidation film (12).

6. The aircraft manufacturing special alloy stainless steel clamping-pressing flange according to claim 5, is characterized in that: the upper pipeline clamping hook (7) is connected with the inner surface clamping hook of the flange outer clamping sleeve (1), and the lower pipeline clamping hook (8) is installed below the upper pipeline clamping hook (7).

7. The aircraft manufacturing special alloy stainless steel clamping-pressing flange according to claim 1, is characterized in that: the inner closed pipeline ring (4), the aviation pipeline (5) and the flange outer clamping sleeve (1) are located on the same axis, and the lower pipeline clamping hook (8) is of an inverted T-shaped structure.