CN113251000B - Locking method of aircraft engine blade - Google Patents
Locking method of aircraft engine blade Download PDFInfo
- Publication number
- CN113251000B CN113251000B CN202010090160.5A CN202010090160A CN113251000B CN 113251000 B CN113251000 B CN 113251000B CN 202010090160 A CN202010090160 A CN 202010090160A CN 113251000 B CN113251000 B CN 113251000B
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- Prior art keywords
- locking
- mortise
- locking block
- block
- workpiece
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/601—Mounting; Assembling; Disassembling specially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Plates (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a locking method of an aircraft engine blade, which comprises the following steps: s1: installing tenons of the blades in the mortises; s2: a locking block is arranged in the mortise; the locking piece penetrates through the locking block and is inserted into the mortise, and the locking piece is connected with the locking block through threads; s3: lifting the locking block to enable the periphery of the locking block to be abutted against an anti-rotation surface arranged on the circumferential side wall of the mortise close to the opening end of the mortise; s4: and rotating the locking piece to further lift the locking block until the locking block is inserted into a locking hole or a locking groove arranged on the flange plate of the blade. Before the locking piece is rotated, the locking block is lifted firstly, so that the periphery of the locking block is abutted to the anti-rotation surface arranged on the circumferential side wall of the mortise, then the locking piece is rotated, the locking block can be prevented from rotating along with the locking piece in situ in the mortise, further lifting of the locking block is facilitated, and locking of the locking block and the blade is facilitated.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a locking method of an aero-engine blade.
Background
In aircraft engine compressors (booster stages), blade locking devices are usually provided between the blades in order to prevent the rotor blades from shifting in the circumferential direction in the circumferential mortises.
Disclosure of Invention
One of the purposes of the present invention is to provide a locking method for an aircraft engine blade, which is used to alleviate the problem of inconvenient blade locking.
Some embodiments of the invention provide a method of locking an aircraft engine blade, comprising the steps of:
s1: installing tenons of the blades in the mortises;
s2: a locking block is arranged in the mortise; the locking piece penetrates through the locking block and is inserted into the mortise, and the locking piece is connected with the locking block through threads;
s3: lifting the locking block to enable the periphery of the locking block to be abutted against an anti-rotation surface arranged on the circumferential side wall of the mortise close to the opening end of the mortise; and
s4: and rotating the locking piece to further lift the locking block until the locking block is inserted into a locking hole or a locking groove arranged on the flange plate of the blade.
In some embodiments, in step S3, the first workpiece is disposed between the locking member and the locking block, and the first workpiece is connected to the locking member or the locking block through a thread, and an end of the first workpiece away from the mortise is provided with a laterally extending edge, and the locking block is lifted by lifting the edge of the first workpiece.
In some embodiments, step S5 is further included after step S4: and taking down the first workpiece.
In some embodiments, in step S4, the end of the locking member outside the mortise is provided with a recess, a second workpiece is disposed in the recess, and rotation of the locking member is achieved by rotating the second workpiece.
In some embodiments, step S6 is further included after step S4: and taking down the second workpiece.
In some embodiments, in step S2, when the locking member is inserted into the mortise through the locking block, the end of the locking member contacts the bottom of the mortise.
In some embodiments, in step S3, the locking block is lifted, and the locking block drives the locking member to lift, at which time, the end of the locking member leaves the bottom of the mortise.
In some embodiments, in step S4, when the locking block is inserted into the locking hole or the locking groove provided on the flange of the blade, the end of the locking member abuts against the bottom of the mortise.
In some embodiments, in step S2, a threaded sleeve is installed inside the locking block, and the locking member is connected to the threaded sleeve through a thread to achieve connection with the locking block.
In some embodiments, the method for locking an aircraft engine blade further comprises a step S0: an anti-rotation groove is formed in the position, close to the opening end of the mortise, of the circumferential side wall of the mortise, and an anti-rotation surface matched with the periphery of the locking block is arranged on the circumferential side wall of the anti-rotation groove; in step S2, the locking block is limited in the anti-rotation groove.
Based on the technical scheme, the invention at least has the following beneficial effects:
in some embodiments, before the locking piece is rotated, firstly, the locking block is lifted, the periphery of the locking block is abutted to the anti-rotation surface arranged on the circumferential side wall of the mortise, then, the locking piece is rotated, the locking block can be prevented from rotating along with the locking piece in the mortise in situ, further lifting of the locking block is facilitated, and locking of the locking block and the blade is facilitated.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a schematic view of a locking block and retaining member installed in a mortise provided in accordance with some embodiments of the present invention;
FIG. 2 is a schematic illustration of a first workpiece and a second workpiece provided in accordance with some embodiments of the invention after installation;
fig. 3 is a schematic view of a locking block being lifted according to some embodiments of the present invention;
FIG. 4 is a schematic view of a locking block provided according to some embodiments of the present invention after locking with a locking hole or a locking groove on a flange of a blade;
FIG. 5 is a schematic illustration of the removal of a first workpiece and a second workpiece after blade locking according to some embodiments of the present invention.
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. It should be apparent that the described embodiments are only some 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 of the present invention without any inventive step, are within the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.
A blade 1 of an aircraft engine generally comprises a tenon, a body and a platform. The blade body is the pneumatic working surface of the blade 1, and the tenon plays a role in connection and force transmission and is fixed and transmitted to the rotor disc. In order to prevent the tenon of the blade 1 from being installed in the circumferential mortise 2 to generate circumferential movement, the blade 1 is locked with the mortise 2 through a locking device.
Locking device includes latch segment 3 and retaining member 4, and latch segment 3 and retaining member 4 all locate in tongue-and-groove 2. The blade 1 is installed in a circle of mortise 2 (circumferential mortise 2), and the installation groove is an entrance and an exit of the blade 1 entering the mortise 2. Blade 1 gets into tongue-and-groove 2 through the mounting groove, and after 2 circumferential motion of edge tongue-and-groove confirmed position, if not locking, can produce the removal along 2 circumferential of tongue-and-groove, at this moment, need the fixed blade 1 of latch segment 3, prevent 1 circumferential motion of blade. The latch segment 3 is located between the adjacent blade 1, and latch segment 3 both cooperates with tongue-and-groove 2, cooperates with blade 1 again, and like this, tongue-and-groove 2 fixes latch segment 3, and latch segment 3 fixes blade 1, avoids blade 1 to follow 2 circumferential shifting of tongue-and-groove.
The mortise slot 2 comprises oppositely arranged slot bottom and open end. The side wall of the mortise 2 close to the open end thereof is dug to the direction of keeping away from the central axis of the mortise 2, and the anti-rotation groove 5 is an annular groove, and the radial dimension of the anti-rotation groove 5 gradually decreases along the direction from the bottom of the mortise 2 to the open end of the mortise 2. The side wall of the anti-rotation groove 5 is set as an anti-rotation surface for preventing the locking block 3 from rotating, and the anti-rotation surface is an arc surface.
The locking block 4 comprises a first portion and a second portion, the radial dimension of the first portion is larger than that of the second portion, and the first portion is close to the bottom of the mortise 2 relative to the second portion. The end of the cross section of the first part of the locking block 3 is conical. The second part of the locking block 3 is cylindrical.
Under the state that the blade 1 is not locked by the locking block 3, the first part of the locking block 4 is limited in the anti-rotation groove 5, and the end part of the second part of the locking block 4 extends out of the mortise 2 through the opening end of the mortise 2. In a state that the blade 1 is locked by the locking block 3, the end of the second portion of the locking block 3 is inserted into the locking hole or locking groove 10 of the flange of the blade 1.
Some embodiments provide a method of locking an aircraft engine blade, comprising the steps of:
s1: the tenon of the blade 1 is mounted in the mortise 2.
S2: as shown in fig. 1, a locking block 3 is disposed in the mortise 2, and the locking block 3 is located between tenons of two adjacent blades 1. Retaining member 4 passes latch segment 3 and inserts in tongue-and-groove 2, and retaining member 4 is connected with latch segment 3 through the screw thread. The first end of retaining member 4 is inserted into mortise 2 and contacts the bottom of the mortise 2, and the second end of retaining member 4 extends out of the mortise 2 through the open end of the mortise 2.
S3: as shown in fig. 3, the locking block 3 is lifted towards the opening end of the mortise 2, so that the periphery of the first part of the locking block 3 is abutted against the anti-rotation surface arranged on the circumferential side wall of the mortise 2 close to the opening end of the mortise, and the locking block 3 is limited by the anti-rotation surface, so that the locking block 3 is prevented from rotating in situ.
S4: as shown in fig. 4, the locking piece 4 is rotated to further lift the locking block 3 until the end of the locking block 3 that penetrates out of the open end of the mortise 2 (the end of the second portion of the locking block 3) is inserted into the locking hole or locking groove 10 provided in the flange of the blade 1.
In the above embodiment, before rotatory latch segment 4, at first promote latch segment 3, make the periphery of the first position of latch segment 3 and the face butt that prevents changeing that 2 circumference lateral walls of tongue-and-groove set up, then rotatory latch segment 4 can prevent that latch segment 3 from being rotatory along with latch segment 4 normal position in tongue-and-groove 2, and then do benefit to further promotion of latch segment 3, do benefit to the locking of latch segment 3 and blade 1. The latch segment 3 both had been cooperated with the anti-rotation slot 5 on the tongue-and-groove 2, and again cooperated with the flange of blade 1, like this, the anti-rotation slot 5 on the tongue-and-groove 2 restricts latch segment 3, and latch segment 3 restricts blade 1 to make blade 1 can not circumferential direction move.
Optionally, the retaining member 4 comprises a retaining screw.
In some embodiments, in step S3, as shown in fig. 2, the first workpiece 6 is disposed between the locking member 4 and the locking block 3, and the first workpiece 6 is connected to the locking member 4 or the locking block 3 by a thread, and the end of the first workpiece 6 away from the mortise 2 is provided with a laterally extending edge, and the locking block 3 is lifted by lifting the edge of the first workpiece 6.
Alternatively, the first workpiece 6 is cylindrical, and the outer periphery of the first workpiece 6 is provided with an external thread connected with the internal thread of the locking block 3.
The annular chamber that forms between retaining member 4 and the latch segment 3 is inserted to the first end of first work piece 6, and the annular chamber is stretched out to the second end of first work piece 6, and the second end of first work piece 6 is equipped with the round edge that extends to the side direction, through promoting the edge of first work piece 6 in order to promote first work piece 6, and then promote retaining segment 3 and retaining member 4, convenient operation.
Optionally, the locking block 3 is provided with an internal thread to be connected with the external thread of the first workpiece 6, and the first workpiece 6 is lifted upwards to drive the locking block 3 to be lifted, so that the periphery of the first part of the locking block 3 is in contact with the anti-rotation surface of the anti-rotation groove 5, and the locking block 3 is prevented from rotating along with the locking piece 4.
In some embodiments, step S5 is further included after step S4: the first workpiece 6 is removed. Namely: after the locking block 3 is locked with the edge plate of the blade 1, the first workpiece 6 is taken down.
In some embodiments, in step S4, a recess is provided at the end of the retaining member 4 that protrudes through the mortise 2, a second workpiece 7 is provided in the recess, and rotation of the retaining member 4 is achieved by rotating the second workpiece 7.
In the above embodiment, the end part penetrating out of the mortise 2 through the locking member 4 is provided with the groove, the second workpiece 7 is arranged in the groove, and the second workpiece 7 is rotated to realize the rotation of the locking member 4, so that the operation is convenient, and the blade tenon mounting structure is suitable for a narrow mounting space of a blade tenon mounting position.
Because latch segment 3 and retaining member 4 are installed behind tongue-and-groove 2, most part is blockked by blade 1, and only a small part position exposes tongue-and-groove 2, and the space of screwing up the operation is narrow and small, through the combined use of first work piece 6 and second work piece 7, does benefit to the screwing up of retaining member 4, and then does benefit to the locking that realizes latch segment 3 and blade 1.
The second workpiece 7 has a shape corresponding to the shape of the recess provided at the end of the retaining member 4, typically hexagonal, diamond or other shape, for tightening the retaining member 4.
In some embodiments, step S4 further comprises step S6: the second workpiece 7 is removed. Namely: after the locking block 3 is locked with the edge plate of the blade 1, the second workpiece 7 is taken down.
In some embodiments, in step S2, when the locking member 4 is inserted into the mortise 2 through the locking block 3, the end of the locking member 4 contacts the bottom of the mortise 2, as shown in fig. 1 and 2. Since the first end of the locking member 4 is inserted into the mortise 2 and is in contact with the bottom of the mortise 2, the second end of the locking member 4 protrudes out of the mortise 2 through the open end of the mortise 2. Thus, here the first end of the locking element 4 is in contact with the bottom of the groove 2.
In some embodiments, in step S3, the locking block 3 is lifted, and the locking member 4 is lifted, at which time the end (first end) of the locking member 4 leaves the bottom of the mortise 2, as shown in fig. 3.
In some embodiments, when the locking block 3 is inserted into the locking hole or locking groove 10 provided on the flange of the blade 1 in step S4, the end (first end) of the locking member 4 abuts against the bottom of the mortise 2, as shown in fig. 4.
As shown in fig. 3, the bottom of the mortise 2 is provided with a positioning groove 9 engaged with the end (first end) of the locking member 4. After the locking block 3 is locked with the blade 1, the end (first end) of the locking member 4 abuts against the positioning groove 9 provided at the bottom of the mortise 2, as shown in fig. 4.
In some embodiments, in step S2, a threaded sleeve 8 is installed inside the locking block 3, and the locking member 4 is screwed into the threaded sleeve 8 to achieve connection with the locking block 3.
Because the threaded screw sleeve 8 has self-locking performance, the locking piece 4 and the threaded screw sleeve 8 have preset tightness, and the locking of the locking piece 4 can be realized.
The latch segment 3 is equipped with the hole that is used for wearing to establish retaining member 4, and the hole lower extreme of latch segment 3 is the plain noodles for with 8 cooperation fixed connection of screw thread cover, the hole upper end of latch segment 3 sets up the internal thread, be used for with first work piece 6 external screw thread connection.
In some embodiments, the method for locking an aircraft engine blade further comprises a step S0: the anti-rotation groove 5 is formed in the position, close to the opening end of the mortise 2, of the circumferential side wall of the mortise 2, and the anti-rotation face matched with the periphery of the locking block 3 is arranged on the circumferential side wall of the anti-rotation groove 5. In step S2, the periphery of the locking block 3 is limited in the anti-rotation groove 5, and in step S3, the locking block 3 is lifted upwards, so that the periphery of the locking block 3 abuts against the anti-rotation surface arranged on the circumferential side wall of the anti-rotation groove 5, and the locking block 3 can be prevented from rotating in situ, so that the locking member 4 can be screwed down.
In some embodiments, the locking method of the locking block 3 and the blade 1 comprises:
after the blade 1, the locking block 3 and the locking member 4 are placed in the mortise 2, the locking block 3 is embedded into the anti-rotation groove 5, the second workpiece 7 is inserted into a groove of the locking member 4 and fixed with the groove of the locking member 4, the first workpiece 6 is screwed into an inner hole of the locking block 3, external threads of the first workpiece 6 are matched with internal threads of the locking block 3, the first workpiece 6 is lifted upwards, the locking block 3 and the locking member 4 are lifted, the circumferential direction of the locking block 3 is in butt fit with anti-rotation surfaces arranged on side walls of the anti-rotation groove 5, then the second workpiece 7 is rotated, the locking member 4 and the locking block 3 rotate relatively, the locking member 4 moves downwards, the locking block 3 moves upwards until the bottom (first end) of the locking member 4 is in contact with the bottom surface of the mortise 2, the top of the locking block 3 is inserted into a locking hole or a locking groove 10 formed in an edge plate of the blade 1, the blade 1 is locked, finally the first workpiece 6 and the second workpiece 7 are sequentially disassembled, and the final state after the blade 1 is locked is as shown in fig. 5.
In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are used only for the convenience of distinguishing the components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.
Furthermore, the technical features of one embodiment may be combined with one or more other embodiments advantageously without explicit negatives.
Finally, it should be noted that the above examples are only used to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications of the embodiments of the invention or equivalent substitutions for parts of the technical features are possible; without departing from the spirit of the invention, it is intended to cover all modifications within the scope of the invention as claimed.
Claims (8)
1. A locking method for an aircraft engine blade is characterized by comprising the following steps:
s1: installing tenons of the blades (1) in the mortises (2);
s2: a locking block (3) is arranged in the mortise (2); the locking piece (4) penetrates through the locking block (3) and is inserted into the mortise (2), and the locking piece (4) is connected with the locking block (3) through threads;
s3: the method comprises the following steps that a first workpiece (6) is arranged between a locking piece (4) and a locking block (3), the first workpiece (6) is connected with the locking piece (4) or the locking block (3) through threads, the end, far away from a mortise (2), of the first workpiece (6) is provided with a laterally extending edge, the locking block (3) is lifted through lifting the edge of the first workpiece (6), and the periphery of the locking block (3) is abutted to an anti-rotation surface arranged on the circumferential side wall, close to the opening end of the mortise (2), of the mortise; and
s4: the tip that retaining member (4) are located outside tongue-and-groove (2) is equipped with the recess, sets up second work piece (7) in the recess, realizes the rotation of retaining member (4) through rotatory second work piece (7), and rotatory retaining member (4) make latch segment (3) further promote, until latch segment (3) insert the locking hole or the locking groove (10) that set up on the flange of blade (1).
2. A method of locking an aircraft engine blade according to claim 1, further comprising, after step S4, step S5: the first workpiece (6) is removed.
3. A method for locking an aircraft engine blade according to claim 1, further comprising, after step S4, step S6: the second workpiece (7) is removed.
4. A method for locking an aircraft engine blade according to claim 1, characterised in that in step S2, the end of the locking piece (4) is brought into contact with the bottom of the mortise slot (2) when the locking piece (4) is inserted through the locking piece (3) into the mortise slot (2).
5. A method for locking an aircraft engine blade according to claim 4, characterised in that in step S3 the locking piece (3) is lifted, while the locking piece (3) brings about the lifting of the locking piece (4), at which point the end of the locking piece (4) leaves the bottom of the mortise slot (2).
6. A method for locking an aircraft engine blade according to claim 5, characterised in that in step S4, when the locking piece (3) is inserted into the locking hole or locking groove (10) provided in the flange of the blade (1), the end of the locking piece (4) abuts against the bottom of the mortise (2).
7. A method for locking an aircraft engine blade according to claim 1, characterised in that in step S2, a threaded sleeve (8) is mounted inside the locking block (3) and the locking element (4) is screwed into the threaded sleeve (8) to achieve the connection with the locking block (3).
8. A method of locking an aircraft engine blade according to claim 1, characterised in that it further comprises a step S0: an anti-rotation groove (5) is formed in the position, close to the opening end of the mortise (2), of the circumferential side wall of the mortise (2), and an anti-rotation surface matched with the periphery of the locking block (3) is arranged on the circumferential side wall of the anti-rotation groove (5); in the step S2, the locking block (3) is limited in the anti-rotation groove (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010090160.5A CN113251000B (en) | 2020-02-13 | 2020-02-13 | Locking method of aircraft engine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010090160.5A CN113251000B (en) | 2020-02-13 | 2020-02-13 | Locking method of aircraft engine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113251000A CN113251000A (en) | 2021-08-13 |
| CN113251000B true CN113251000B (en) | 2022-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010090160.5A Active CN113251000B (en) | 2020-02-13 | 2020-02-13 | Locking method of aircraft engine blade |
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| CN (1) | CN113251000B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103122867A (en) * | 2013-01-28 | 2013-05-29 | 河南科技大学 | Fan and locking device of front mesh enclosure and back mesh enclosure of fan |
| CN110005637A (en) * | 2018-01-04 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | Axial-flow type aeroengine rotor |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7901187B2 (en) * | 2006-06-23 | 2011-03-08 | Siemens Energy, Inc. | Turbine rotor blade groove entry slot lock structure |
| US20150101350A1 (en) * | 2013-10-16 | 2015-04-16 | General Electric Company | Locking spacer assembly |
| CN104481594A (en) * | 2014-10-28 | 2015-04-01 | 哈尔滨汽轮机厂有限责任公司 | Locking device used for circumferential compressor annular dovetail-shaped blade root of gas compressor |
| CN105889125B (en) * | 2016-06-21 | 2019-01-18 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of compressor rotor |
| CN106014490B (en) * | 2016-06-22 | 2019-03-08 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of locking mechanism of rotor blade |
| CN109209994B (en) * | 2017-06-29 | 2020-06-05 | 中国航发商用航空发动机有限责任公司 | Rotor blade locking device |
-
2020
- 2020-02-13 CN CN202010090160.5A patent/CN113251000B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103122867A (en) * | 2013-01-28 | 2013-05-29 | 河南科技大学 | Fan and locking device of front mesh enclosure and back mesh enclosure of fan |
| CN110005637A (en) * | 2018-01-04 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | Axial-flow type aeroengine rotor |
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| CN113251000A (en) | 2021-08-13 |
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