CN210034116U - D-head bolt and aircraft engine - Google Patents
D-head bolt and aircraft engine Download PDFInfo
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- CN210034116U CN210034116U CN201920870206.8U CN201920870206U CN210034116U CN 210034116 U CN210034116 U CN 210034116U CN 201920870206 U CN201920870206 U CN 201920870206U CN 210034116 U CN210034116 U CN 210034116U
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Abstract
The utility model aims at providing a D-head bolt which is provided with a head part and a rod part; the head has an upper surface, a skirt side and a lower surface; one end of the rod part is connected to the lower surface; the rod part is provided with threads, and the side surface of the ring enclosure comprises an arc surface and a straight surface; two ends of the cambered surface are connected with two ends of the straight surface; the D-head bolt is also provided with a flange plate; the flange plate is arranged on the side surface of the ring enclosure in a protruding mode along the radial direction of the head part, and the flange plate is provided with an arc-shaped part and a straight part; the arc portion is arranged on the arc surface and is flush with the lower surface, and the straight portion is arranged on the straight surface and is flush with the lower surface. Due to the arrangement of the flange plate, the contact area of the D-head bolt and a part to be fastened is increased, and therefore the D-head bolt has high reliability. The aircraft engine comprises the D-head bolt, and therefore the aircraft engine also has high reliability.
Description
Technical Field
The utility model relates to a D head bolt and aeroengine.
Background
With the progress of science and technology, the parameters such as thrust, rotating speed, temperature and pressure of the aircraft engine are higher and higher, the requirements on the connection strength and reliability of each connection structure are higher and higher, and the conventional engine bolt is insufficient in strength and can not meet the requirements on the load of the aircraft engine gradually.
The D-head bolt is also called a D-type bolt, and the top view of the head of the D-head bolt is like an English capital letter 'D', so the D-head bolt is named. Fig. 1 shows a prior art D-head bolt 900, which has a head 1 and a shaft 2, the shaft 2 is provided with a thread 2a, the head 1 has an upper surface 10, a surrounding side surface 11 and a lower surface 12, and the surrounding side surface 11 includes an arc surface 11a and a straight surface 11 b.
The aero-engine in the prior art adopts the D-head bolt to connect structural members such as a wheel disc and a casing, but because the performance of a modern large bypass is higher and higher than that of the engine, the strength of the common D-head bolt is not enough to ensure the strength, rigidity and reliability of a connecting structure, so that the reliability of the aero-engine is not enough, and the safety and integrity of the structure are lost.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a D head bolt has the advantage that the reliability is high.
An object of the utility model is also to provide an aeroengine, include as above D head bolt.
The D-head bolt for achieving the purpose is provided with a head part and a rod part; the head has an upper surface, a skirt side, and a lower surface; one end of the rod part is connected to the lower surface; the rod part is provided with threads, and the side surface of the ring enclosure comprises an arc surface and a straight surface; two ends of the cambered surface are connected with two ends of the straight surface;
the D-head bolt is also provided with a flange plate; the flange plate is arranged on the side surface of the ring enclosure in a protruding mode along the radial direction of the head part, and the flange plate is provided with an arc-shaped part and a straight part;
the arc portion sets up in the cambered surface and with the lower surface parallel and level, straight shape portion sets up on the straight face and with the lower surface parallel and level.
The D-head bolt is further characterized by further comprising a transition part, wherein the transition part is provided with an inner wall surface and an outer wall surface;
the inner wall surface is respectively connected with the side surface of the ring enclosure and the flange plate; the outer wall surface is in an arc shape which is sunken inwards.
The D-head bolt is further characterized in that the central axis of the rod part passes through the circle center of the arc surface and the circle center of the arc part.
The D-head bolt is further characterized in that the arc-shaped part and the straight part have equal thickness in the radial direction of the head part.
The D-head bolt is further characterized in that the head part, the rod part, the flange plate and the transition part are integrally formed.
The D-head bolt is further characterized in that the head part, the rod part, the flange plate and the transition part are made of high-strength metal materials.
The D-head bolt is further characterized in that the high-strength metal material is nickel-based high-temperature alloy steel.
The D-head bolt is further characterized in that one end of the rod part is welded with the lower surface.
To achieve the purpose, the aircraft engine comprises the D-head bolt.
The utility model discloses an actively advance the effect and lie in: the D-head bolt is provided with a head part and a rod part; the head has an upper surface, a skirt side and a lower surface; one end of the rod part is connected to the lower surface; the rod part is provided with threads, and the side surface of the ring enclosure comprises an arc surface and a straight surface; two ends of the cambered surface are connected with two ends of the straight surface; the D-head bolt is also provided with a flange plate; the flange plate is arranged on the side surface of the ring enclosure in a protruding mode along the radial direction of the head part, and the flange plate is provided with an arc-shaped part and a straight part; the arc portion is arranged on the arc surface and is flush with the lower surface, and the straight portion is arranged on the straight surface and is flush with the lower surface.
Due to the arrangement of the flange plate, the contact area of the D-head bolt and a part to be fastened is increased, and therefore the D-head bolt has high reliability. The aircraft engine comprises the D-head bolt, and therefore the aircraft engine also has high reliability.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of a prior art D-head bolt;
fig. 2 is a side view of a D-head bolt according to an embodiment of the present invention;
fig. 3 is a schematic view of a D-head bolt according to an embodiment of the present invention.
Detailed Description
The present invention will be further described with reference to the following embodiments and drawings, and more details will be set forth in the following description in order to provide a thorough understanding of the present invention, but it is obvious that the present invention can be implemented in various other ways different from those described herein, and those skilled in the art can make similar generalizations and deductions according to the actual application without departing from the spirit of the present invention, and therefore, the scope of the present invention should not be limited by the contents of the embodiments.
The following discloses embodiments or examples of various implementations of the subject technology. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
It should be noted that fig. 1-3 are only examples, are not drawn to scale, and should not be taken as limiting the scope of the invention.
The D-head bolt is also called a D-type bolt, and the top view of the head of the D-head bolt is like an English capital letter 'D', so the D-head bolt is named. Fig. 1 shows a prior art D-head bolt 900, which has a head 1 and a shaft 2, the shaft 2 is provided with a thread 2a, the head 1 has an upper surface 10, a surrounding side surface 11 and a lower surface 12, and the surrounding side surface 11 includes an arc surface 11a and a straight surface 11 b.
The aero-engine in the prior art adopts the D-head bolt to connect structural members such as a wheel disc and a casing, but because the performance of a modern large bypass is higher and higher than that of the engine, the strength of the common D-head bolt is not enough to ensure the strength, rigidity and reliability of a connecting structure, so that the reliability of the aero-engine is not enough, and the safety and integrity of the structure are lost. The D-shaped sleeve can be used for realizing the installation process of the D-head bolt.
For the reliability that improves D head bolt, the embodiment of the utility model provides a D head bolt. For the same structure and components, the D-head bolt in the embodiment of the present invention is denoted by the same reference numerals as the D-head bolt 900 in fig. 1.
As shown in fig. 2 and 3, the D-head bolt has a head portion 1 and a shank portion 2; the head 1 has an upper surface 10, a bounding side 11 and a lower surface 12; one end of the rod part 2 is connected to the lower surface 12; the rod part 2 is provided with a thread 2a, and the ring side surface 11 comprises an arc surface 11a and a straight surface 11 b; two ends of the cambered surface 11a are connected with two ends of the straight surface 11 b; the D-head bolt is also provided with a flange 3; the flange 3 is arranged on the surrounding side surface 11 in a protruding way along the radial direction of the head part 1, wherein the flange 3 is provided with an arc-shaped part 3a and a straight part 3 b; the arc-shaped portion 3a is disposed on the arc surface 11a and flush with the lower surface 12, and the straight portion 3b is disposed on the straight surface 11b and flush with the lower surface 12.
The position of the encircling side 11 is shown in fig. 2 by dashed lines due to occlusion.
Due to the arrangement of the flange plate 3, the contact area of the D-head bolt and a part to be fastened is increased, and therefore the D-head bolt has high reliability. The aircraft engine comprises the D-head bolt, and therefore the aircraft engine also has high reliability.
With continued reference to fig. 2 and 3, the D-head bolt also has a transition portion 4, the transition portion 4 having an inner wall surface and an outer wall surface 4 a; the inner wall surface is respectively connected with the surrounding side surface 11 and the flange plate 3; the outer wall surface 4a is shaped like an arc which is recessed inward. This arrangement reduces stress concentration at the junction of the skirt side 11 and the flange 3.
In one embodiment, the central axis of the rod portion 2 passes through the center of the arc surface 11a and the center of the arc portion 3 a. According to the scheme, the D-head bolt is easy to implement when being screwed by the D-head sleeve, and deflection torque is not generated.
In one embodiment, the arcuate portion 3a and the straight portion 3b are equal in thickness in the radial direction of the head 1. This solution makes the flange 3 easy to manufacture.
In one embodiment, the head portion 1, stem portion 2, flange 3 and transition portion 4 are integrally formed. This arrangement makes the D-head bolt easy to manufacture and has greater strength.
In one embodiment, the head portion 1, stem portion 2, flange 3 and transition portion 4 are made of a high strength metallic material. More specifically, the high-strength metallic material is high-strength alloy steel. More specifically, the high strength alloy steel is a nickel-based high temperature alloy steel.
In one embodiment, one end of the stem 2 is welded to the lower surface 12.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention, and any modifications, equivalent changes and modifications made to the above embodiments by the technical spirit of the present invention fall within the scope of protection defined by the claims of the present invention.
Claims (10)
1. A D-head bolt has a head (1) and a shank (2); the head (1) has an upper surface (10), a skirt side (11) and a lower surface (12); one end of the rod part (2) is connected to the lower surface (12); the rod part (2) is provided with a thread (2a), and the ring side surface (11) comprises an arc surface (11a) and a straight surface (11 b); the two ends of the cambered surface (11a) are connected with the two ends of the straight surface (11 b);
the D-head bolt is characterized by also comprising a flange plate (3); the flange plate (3) is arranged on the surrounding side surface (11) in a protruding mode along the radial direction of the head part (1), wherein the flange plate (3) is provided with an arc-shaped part (3a) and a straight part (3 b);
arc portion (3a) set up arc face (11a) on and with lower surface (12) parallel and level, straight shape portion (3b) set up straight face (11b) on and with lower surface (12) parallel and level.
2. A D-head bolt according to claim 1, characterised in that it further has a transition portion (4), said transition portion (4) having an inner wall surface and an outer wall surface (4 a);
the inner wall surface is respectively connected with the surrounding side surface (11) and the flange plate (3); the outer wall surface (4a) is in the shape of an inwardly concave arc.
3. A D-head bolt according to claim 1, characterised in that the centre axis of the shank (2) passes through the centre of the arc (11a) and the centre of the arc (3 a).
4. A D-head bolt according to claim 1 characterised in that the arcuate portion (3a) and the straight portion (3b) are of equal thickness in the radial direction of the head (1).
5. A D-head bolt according to claim 2 characterised in that the head (1), the shank (2), the flange (3) and the transition portion (4) are integrally formed.
6. A D-head bolt according to claim 5 characterised in that the head (1), the shank (2), the flange (3) and the transition portion (4) are made of a high strength metal material.
7. A D-head bolt according to claim 6, characterised in that the high strength metallic material is a high strength alloy steel.
8. The D-head bolt according to claim 7, wherein the high-strength alloy steel is a nickel-based high-temperature alloy steel.
9. A D-head bolt according to claim 1 characterised in that one end of the shank (2) is welded to the lower face (12).
10. An aircraft engine, characterized in that it comprises a D-head bolt according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920870206.8U CN210034116U (en) | 2019-06-11 | 2019-06-11 | D-head bolt and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920870206.8U CN210034116U (en) | 2019-06-11 | 2019-06-11 | D-head bolt and aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210034116U true CN210034116U (en) | 2020-02-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920870206.8U Active CN210034116U (en) | 2019-06-11 | 2019-06-11 | D-head bolt and aircraft engine |
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| CN (1) | CN210034116U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114909381A (en) * | 2021-02-07 | 2022-08-16 | 中国航发商用航空发动机有限责任公司 | Bolt rotation-proof assembly structure and aircraft engine adopting same |
-
2019
- 2019-06-11 CN CN201920870206.8U patent/CN210034116U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114909381A (en) * | 2021-02-07 | 2022-08-16 | 中国航发商用航空发动机有限责任公司 | Bolt rotation-proof assembly structure and aircraft engine adopting same |
| CN114909381B (en) * | 2021-02-07 | 2023-11-03 | 中国航发商用航空发动机有限责任公司 | Bolt anti-rotation assembly structure and aeroengine adopting same |
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