CN208561433U - A kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc - Google Patents

Abstract

The utility model provides a kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc, it includes disc, it is offered on disc and the body concentric circular hole of disk, glue-line is coated on disc, two cutting line components being oppositely arranged are provided on disc, cutting line component includes two the first cutting lines in splayed arrangement, first cutting line is radially extended along disc, one end of first cutting line extends to the hole Yan Chu of circular hole, the other end of first cutting line connects the second cutting line, the free end of second cutting line extends to the edge of disc, angle is formed between second cutting line and the first cutting line.The utility model can effectively improve fixing when calvus crawl axial workpiece compared to the prior art.

Description

A kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc

Technical field

The utility model relates to a kind of aircraft engine axial workpiece lifting devices, send out in particular to a kind of aircraft The encapsulated pawl mounting structure of motivation axial workpiece arc.

Background technique

When for the processing of axial workpiece used in aircraft engine, need to complete lifting operation using suspender. Traditional suspender is mainly made of multiple calvus, is usually that two arc calvus are formed, and this kind of calvus also need into The encapsulated processing of row.

It is complex-shaped and irregular due to calvus in traditional technology, it will cause the encapsulated uneven of calvus often, be easy Lead to that complete circle can not be formed between two encapsulated pawls of arc, so that occurring when calvus crawl axial workpiece unstable Phenomenon.

Utility model content

Calvus can be made to grab a kind of more firm aircraft of axial workpiece in consideration of it, the utility model provides one kind The encapsulated pawl mounting structure of engine axial workpiece arc.

For this purpose, the utility model provides a kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc, packet Include disc, offered on disc with the body concentric circular hole of disk, be coated with glue-line on disc, be provided with phase on disc To two cutting line components of setting, cutting line component includes two the first cutting lines in splayed arrangement, the first cutting line edge Radially extending for disc, one end of the first cutting line extend to the hole Yan Chu of circular hole, the other end connection of the first cutting line Second cutting line, the free end of the second cutting line extend to the edge of disc, shape between the second cutting line and the first cutting line At angle.

Further, the encapsulated pawl of arc is formed between above-mentioned two second adjacent cutting lines.

Further, the shape of end matching the first cutting line and the second cutting line of the encapsulated pawl of above-mentioned arc.

Further, multiple connecting holes are offered on the encapsulated pawl of above-mentioned arc.

Further, the hole Yan Chu of above-mentioned circular hole offer multiple radial directions along disc extend into disc it is recessed Slot.

Further, the end of above-mentioned first cutting line extends to the slot bottom of groove.

The encapsulated pawl mounting structure of a kind of aircraft engine axial workpiece arc provided by the utility model, compared to The prior art mainly has the advantage that by the way that encapsulated layer is arranged on disk, and multiple cutting lines are arranged, thus can be with So that disk may be implemented to be attached with the devices such as support rod and calvus fixing seat, then disk is cut again, is made It obtains calvus and completes installation after dicing, so that calvus is encapsulated more uniform, so that can between two encapsulated pawls of arc To form complete circle, fixing when calvus crawl axial workpiece is effectively improved.

Detailed description of the invention

By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as practical to this Novel limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:

Fig. 1 is a kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc provided by the embodiment of the utility model Structural schematic diagram；

Fig. 2 is a kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc provided by the embodiment of the utility model Scheme of installation.

Specific embodiment

Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure It is fully disclosed to those skilled in the art.

Embodiment one:

Referring to Fig. 1 to Fig. 2, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment one is shown in figure With the encapsulated pawl mounting structure of arc comprising disc 1 offers the circular hole 11 concentric with disc 1, disk on disc 1 It is coated with glue-line 12 on body 1, two cutting line components 13 being oppositely arranged are provided on disc 1, cutting line component 13 includes two Item is in the first cutting line 131 of splayed arrangement, the first radially extending along disc 1 of cutting line 131, the first cutting line 131 one end extends to the hole of circular hole 11 at 111, the other end the second cutting line 132 of connection of the first cutting line 131, and second The free end of cutting line 132 extends to the edge 14 of disc 1, and folder is formed between the second cutting line 132 and the first cutting line 131 Angle A.Wherein, the encapsulated pawl 15 of arc is formed between two second adjacent cutting lines 132；The end matching first of the encapsulated pawl 15 of arc The shape of cutting line 131 and the second cutting line 132.

A kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc provided by the present embodiment, compared to existing There is technology mainly to have the advantage that by the way that encapsulated layer is arranged on disk, and multiple cutting lines are set, can thus make Obtaining disk may be implemented to be attached with the devices such as support rod and calvus fixing seat, then cut again to disk, so that Calvus completes installation after dicing so that calvus it is encapsulated more uniformly so that can be between two encapsulated pawls of arc Complete circle is formed, fixing when calvus crawl axial workpiece is effectively improved.

Embodiment two:

Referring to Fig. 1 to Fig. 2, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment two is shown in figure With the encapsulated pawl mounting structure of arc, the present embodiment is also further made that following as improvement on the basis of the above embodiments Technical solution: offer multiple connecting holes 151 on the encapsulated pawl 15 of arc.Improvement through the above technical solution, may be implemented The quick connection of the encapsulated pawl of arc.

Embodiment three:

Referring to Fig. 1 to Fig. 2, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment three is shown in figure With the encapsulated pawl mounting structure of arc, the present embodiment is also further made that following as improvement on the basis of the above embodiments Technical solution: the hole of circular hole 11 offers the groove that multiple radial directions along disc 1 extend into disc 1 at 111 The end of 112: the first cutting lines 131 extends to the slot bottom of groove 112.Improvement through the above technical solution, can be in order to right Disc carries out cutting operation.

Obviously, it is practical without departing from this can to carry out various modification and variations to the utility model by those skilled in the art Novel spirit and scope.If in this way, these modifications and variations of the present invention belong to the utility model claims and Within the scope of its equivalent technologies, then the utility model is also intended to include these modifications and variations.

Claims (6)

1. a kind of encapsulated pawl mounting structure of aircraft engine axial workpiece arc, which is characterized in that including disc (1), institute It states and offers the circular hole (11) concentric with the disc (1) on disc (1), be coated with glue-line on the disc (1) (12), two cutting line components (13) being oppositely arranged are provided on the disc (1), the cutting line component (13) includes two Item is in the first cutting line (131) of splayed arrangement, and first cutting line (131) is prolonged along the radial direction of the disc (1) It stretches, one end of first cutting line (131) extends to the hole of the circular hole (11) at (111), first cutting line (131) the other end connects the second cutting line (132), and the free end of second cutting line (132) extends to the disc (1) edge (14) forms angle (A) between second cutting line (132) and first cutting line (131).

2. the encapsulated pawl mounting structure of a kind of aircraft engine axial workpiece arc according to claim 1, feature exist In the formation encapsulated pawl of arc (15) between second cutting line (132) of adjacent two.

3. the encapsulated pawl mounting structure of a kind of aircraft engine axial workpiece arc according to claim 2, feature exist In the end of the encapsulated pawl of arc (15) matches the shape of first cutting line (131) and second cutting line (132) Shape.

4. the encapsulated pawl mounting structure of a kind of aircraft engine axial workpiece arc according to claim 3, feature exist In offering multiple connecting holes (151) on the encapsulated pawl of arc (15).

5. the encapsulated pawl mounting structure of a kind of aircraft engine axial workpiece arc according to claim 1, feature exist In the hole of the circular hole (11) offers multiple along the radial to the disc of the disc (1) at (111) (1) groove (112) extended in.

6. the encapsulated pawl mounting structure of a kind of aircraft engine axial workpiece arc according to claim 5, feature exist In the end of first cutting line (131) extends to the slot bottom of the groove (112).