CN215057591U - Surge-resistant reinforced aircraft engine stator blade - Google Patents
Surge-resistant reinforced aircraft engine stator blade Download PDFInfo
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- CN215057591U CN215057591U CN202121268674.1U CN202121268674U CN215057591U CN 215057591 U CN215057591 U CN 215057591U CN 202121268674 U CN202121268674 U CN 202121268674U CN 215057591 U CN215057591 U CN 215057591U
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- installation semi
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Abstract
The utility model discloses a surge-resistant aircraft engine stator blade of strengthening, including installation ring and stator blade body, the inboard fixed mounting of installation ring has stator blade body, the installation ring includes first installation semi-ring and second installation semi-ring, one side of first installation semi-ring is provided with second installation semi-ring, the one end fixed surface of first installation semi-ring installs the combination fixture block. A surge-resistant aircraft engine stator blade of strengthening belongs to stator blade field, can separate first installation semi-ring and second installation semi-ring, enlarged the distance between first installation semi-ring and the second installation semi-ring, make things convenient for the stator blade body to insert the operation that the installation leads to groove and welded, reduced the assembly degree of difficulty of stator blade body, and the location slide can slide and play the guide effect inside the positioning sliding sleeve for the closed location of first installation semi-ring and second installation semi-ring is accurate, effectively saves installation time.
Description
Technical Field
The utility model relates to a stator blade field, in particular to resistant surge strengthens aeroengine stator blade.
Background
The axial-flow compressor is commonly used in an aircraft engine or a gas turbine, works on air through high-speed rotation of blades to improve air pressure, the blades are divided into rotor blades and stator blades, a row of stator blades are arranged behind each row of rotor blades, the rotor blades and the stator blades form the whole compressor, the rotor blades are fixed on a turbine shaft, and the stator blades are fixed on the inner wall of a casing through mounting rings. When the turbine shaft moves, the rotor blades rotate along with the turbine shaft, and the stator blades are static relative to the rotor blades, so that the aim of improving air pressure is fulfilled; the stator blade inserts the logical inslot of installation of collar and welded fastening, but stator blade's assembly and welding operation space are narrow and small for the installation is loaded down with trivial details, wastes time and energy.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a main aim at provides a surge-resistant aeroengine stator blade of strengthening can effectively solve the problem among the background art.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides a surge-resistant reinforced aircraft engine stator blade, includes installation ring and stator blade body, the inboard fixed mounting of installation ring has stator blade body, the installation ring includes first installation semi-ring and second installation semi-ring, one side of first installation semi-ring is provided with second installation semi-ring, the one end fixed surface of first installation semi-ring installs combination fixture block, the combination draw-in groove has been seted up to the terminal surface of second installation semi-ring, first installation semi-ring with the lower fixed surface of second installation semi-ring installs positioner.
Preferably, the positioning device comprises a positioning sliding sleeve and a positioning sliding plate, a guide sliding groove is formed in the positioning sliding sleeve, and the positioning sliding plate is movably arranged in the positioning sliding sleeve.
Preferably, the outer side surfaces of the first installation semi-ring and the second installation semi-ring are provided with annular grooves, the inner side surfaces of the first installation semi-ring and the second installation semi-ring are provided with installation through grooves, the stator blade body is embedded into the installation through grooves in the surfaces of the first installation semi-ring and the second installation semi-ring, and the stator blade body is welded with the installation through grooves.
Preferably, the surfaces of the combined fixture block and the second installation semi-ring are both provided with penetrating holes in a penetrating manner, the inner side surface of the second installation semi-ring is provided with fastening bolts in the penetrating holes in a penetrating manner, and fastening nuts are installed in the annular groove on the surface of the fastening bolts in a threaded manner.
Preferably, the positioning sliding sleeve is fixedly connected with the lower surface of the first installation semi-ring, the positioning sliding plate is fixedly connected with the lower surface of the second installation semi-ring, and the second installation semi-ring is slidably connected with the positioning sliding sleeve of the first installation semi-ring through the positioning sliding plate.
Preferably, the combined clamping block is matched with the combined clamping groove in a clamping manner, and the first installation semi-ring is closed through the combined clamping block and the combined clamping groove of the second installation semi-ring.
Compared with the prior art, the utility model discloses following beneficial effect has:
the utility model discloses in, through the first installation semi-ring that sets up, second installation semi-ring and positioner, can separate first installation semi-ring and second installation semi-ring, enlarged the distance between first installation semi-ring and the second installation semi-ring, make things convenient for the stator blade body to insert installation logical groove and welded operation, reduced the assembly degree of difficulty of stator blade body, and the location slide can be inside to slide and play the guide effect in the sliding sleeve of location for the closed location of first installation semi-ring and second installation semi-ring is accurate, effectively saves installation time.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the installation ring structure of the present invention;
FIG. 3 is a schematic view of the mounting ring of the present invention;
fig. 4 is a sectional view of the positioning sliding sleeve of the present invention.
In the figure: 1. installing a circular ring; 2. a stator blade body; 3. a positioning device; 4. an annular groove; 5. a first mounting half ring; 6. a second mounting half ring; 7. installing a through groove; 8. fastening a bolt; 9. fastening a nut; 10. combining the fixture blocks; 11. a through hole; 12. a combined clamping groove; 13. positioning the sliding sleeve; 14. positioning the sliding plate; 15. a guide chute.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
As shown in fig. 1-4, a surge-resistant reinforced aircraft engine stator blade comprises a mounting ring 1 and a stator blade body 2, the stator blade body 2 is fixedly mounted on the inner side of the mounting ring 1, the mounting ring 1 comprises a first mounting half ring 5 and a second mounting half ring 6, the second mounting half ring 6 is arranged on one side of the first mounting half ring 5, a combined fixture block 10 is fixedly mounted on the surface of one end of the first mounting half ring 5, a combined clamping groove 12 is formed in the end surface of the second mounting half ring 6, and a positioning device 3 is fixedly mounted on the lower surfaces of the first mounting half ring 5 and the second mounting half ring 6.
In this embodiment, the positioning device 3 includes a positioning sliding sleeve 13 and a positioning sliding plate 14, a guiding sliding slot 15 is formed inside the positioning sliding sleeve 13, a positioning sliding plate 14 is movably installed inside the positioning sliding sleeve 13, after the stator blade body 2 is assembled, the first half installation ring 5 is embedded inside the combined clamping groove 12 through the combined clamping block 10 and is closed with the second half installation ring 6, finally, the first half installation ring 5 and the second half installation ring 6 are locked and fixed through the fastening bolt 8 and the fastening nut 9, in the process of closing the first half installation ring 5 and the second half installation ring 6, the positioning sliding plate 14 slides inside the positioning sliding sleeve 13 and plays a guiding role, the first half installation ring 5 and the second half installation ring 6 are accurately positioned in a closed mode, and the installation time is effectively saved.
Annular groove 4 has been seted up on the outside surface of first installation semi-ring 5 and second installation semi-ring 6, and the logical groove 7 of installation has all been seted up on the inside surface of first installation semi-ring 5 and second installation semi-ring 6, and inside the logical groove 7 of installation on first installation semi-ring 5 of stator blade body 2 embedding and second installation semi-ring 6 surface, stator blade body 2 and the logical groove 7 welding of installation.
In this embodiment, the surface of the combined fixture block 10 and the surface of the second installation semi-ring 6 are all penetrated and provided with the penetrating hole 11, the fastening bolt 8 is penetrated and provided on the inner side surface of the second installation semi-ring 6 inside the penetrating hole 11, the fastening nut 9 is installed on the surface thread of the fastening bolt 8 inside the annular groove 4, the first installation semi-ring 5 and the second installation semi-ring 6 can be separated, the distance between the first installation semi-ring 5 and the second installation semi-ring 6 is enlarged, the stator blade body 2 is convenient to insert into the installation through groove 7 and weld, and the assembling difficulty of the stator blade body 2 is reduced.
The positioning sliding sleeve 13 is fixedly connected with the lower surface of the first half installation ring 5, the positioning sliding plate 14 is fixedly connected with the lower surface of the second half installation ring 6, and the second half installation ring 6 is in sliding connection with the positioning sliding sleeve 13 of the first half installation ring 5 through the positioning sliding plate 14.
The combined fixture block 10 is matched with the combined slot 12 in a clamping manner, and the first half installation ring 5 is closed through the combined fixture block 10 and the combined slot 12 of the second half installation ring 6.
It should be noted that, the utility model relates to a surge-resistant reinforced aero-engine stator blade, before the stator blade body 2 and the installation ring 1 are installed, the closed fastening bolt 8 and the fastening nut 9 are taken down inside the annular groove 4, and the installation ring 1 is pulled in the opposite direction, so that the second installation semi-ring 6 slides inside the positioning sliding sleeve 13 on the surface of the first installation semi-ring 5 through the positioning sliding plate 14, thereby separating the first installation semi-ring 5 from the second installation semi-ring 6, enlarging the distance between the first installation semi-ring 5 and the second installation semi-ring 6, facilitating the operation of inserting the stator blade body 2 into the installation through groove 7 and welding, reducing the assembly difficulty of the stator blade body 2, after the stator blade body 2 is assembled, the first installation semi-ring 5 is embedded inside the combination clamping groove 12 through the combination clamping block 10 and is closed with the second installation semi-ring 6, and finally, the first half installation ring 5 and the second half installation ring 6 are locked and fixed through the fastening bolt 8 and the fastening nut 9, and in the process of closing the first half installation ring 5 and the second half installation ring 6, the positioning sliding plate 14 slides in the positioning sliding sleeve 13 and plays a role in guiding, so that the first half installation ring 5 and the second half installation ring 6 are accurately positioned in a closed mode, and the installation time is effectively saved.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. Although embodiments of the present invention have been shown and described, it is not intended to limit the scope of the invention, which is defined by the appended claims and their equivalents, and all changes in equivalent structure or equivalent flow process that can be made by using the contents of the specification and drawings or applied directly or indirectly to other related technical fields are intended to be embraced therein by the scope of the invention.
Claims (6)
1. The utility model provides a surge-resistant aeroengine stator blade of strengthening which characterized in that: including installation ring (1) and stator blade body (2), the inboard fixed mounting of installation ring (1) has stator blade body (2), installation ring (1) is including first installation semi-ring (5) and second installation semi-ring (6), one side of first installation semi-ring (5) is provided with second installation semi-ring (6), the one end fixed surface of first installation semi-ring (5) installs combination fixture block (10), combination draw-in groove (12) have been seted up to the terminal surface of second installation semi-ring (6), first installation semi-ring (5) with the lower fixed surface of second installation semi-ring (6) installs positioner (3).
2. The surge-resistant reinforced aircraft engine stator vane of claim 1, wherein: the positioning device (3) comprises a positioning sliding sleeve (13) and a positioning sliding plate (14), a guide sliding groove (15) is formed in the positioning sliding sleeve (13), and the positioning sliding plate (14) is movably arranged in the positioning sliding sleeve (13).
3. A surge-resistant reinforced aircraft engine stator vane as claimed in claim 2, wherein: annular grooves (4) are formed in the outer side surfaces of the first installation semi-ring (5) and the second installation semi-ring (6), installation through grooves (7) are formed in the inner side surfaces of the first installation semi-ring (5) and the second installation semi-ring (6), the stator blade body (2) is embedded into the installation through grooves (7) in the surfaces of the first installation semi-ring (5) and the second installation semi-ring (6), and the stator blade body (2) is welded with the installation through grooves (7).
4. A surge-resistant reinforced aircraft engine stator vane as claimed in claim 3, wherein: the combined fixture block (10) and the surface of the second installation semi-ring (6) are provided with penetrating holes (11) in a penetrating mode, fastening bolts (8) penetrate through the inner side surface of the second installation semi-ring (6) and are located in the penetrating holes (11), and fastening nuts (9) are installed on the surface of the annular groove (4) which is located in the fastening bolts (8) in a threaded mode.
5. The surge-resistant reinforced aircraft engine stator vane of claim 4, wherein: the positioning sliding sleeve (13) is fixedly connected with the lower surface of the first installation semi-ring (5), the positioning sliding plate (14) is fixedly connected with the lower surface of the second installation semi-ring (6), and the second installation semi-ring (6) is slidably connected with the positioning sliding sleeve (13) of the first installation semi-ring (5) through the positioning sliding plate (14).
6. The surge-resistant reinforced aircraft engine stator vane of claim 5, wherein: the combined clamping block (10) is matched with the combined clamping groove (12) in a clamping mode, and the first installation semi-ring (5) is closed through the combined clamping block (10) and the combined clamping groove (12) of the second installation semi-ring (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121268674.1U CN215057591U (en) | 2021-06-07 | 2021-06-07 | Surge-resistant reinforced aircraft engine stator blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121268674.1U CN215057591U (en) | 2021-06-07 | 2021-06-07 | Surge-resistant reinforced aircraft engine stator blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215057591U true CN215057591U (en) | 2021-12-07 |
Family
ID=79204317
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121268674.1U Active CN215057591U (en) | 2021-06-07 | 2021-06-07 | Surge-resistant reinforced aircraft engine stator blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215057591U (en) |
-
2021
- 2021-06-07 CN CN202121268674.1U patent/CN215057591U/en active Active
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