CN114810220B - Aero-engine - Google Patents
Aero-engine Download PDFInfo
- Publication number
- CN114810220B CN114810220B CN202110330532.1A CN202110330532A CN114810220B CN 114810220 B CN114810220 B CN 114810220B CN 202110330532 A CN202110330532 A CN 202110330532A CN 114810220 B CN114810220 B CN 114810220B
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- Prior art keywords
- blade
- drum
- positioning hole
- positioning
- tenon
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- 238000003780 insertion Methods 0.000 claims description 12
- 230000037431 insertion Effects 0.000 claims description 12
- 238000009434 installation Methods 0.000 abstract description 5
- 238000012545 processing Methods 0.000 description 11
- 238000005516 engineering process Methods 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to an aeroengine, comprising: a drum (2) comprising a mortise (7) extending along its circumference, the bottom of the mortise (7) being provided with a first positioning hole (5); the blades are arranged side by side along the circumferential direction of the drum (2), each blade comprises a blade body (1) and a tenon (6) connected with the blade body (1) and matched with the tenon groove (7), and a second positioning hole (8) coaxially arranged with the first positioning hole (5) is formed in each blade; the positioning component (3) is inserted into the first positioning hole (5) and the second positioning hole (8) so as to limit the tenon (6) of the blade to move along the circumferential direction of the drum (2) in the mortise (7), and the circumferential positioning of the blade can be realized by inserting the positioning component (3) into the first positioning hole (5) and the second positioning hole (8), so that the blade positioning device has the characteristics of simple structure, convenience in installation and low cost.
Description
Technical Field
The invention relates to the field of aviation equipment, in particular to an aeroengine.
Background
Referring to fig. 1 to 4, an aeroengine includes a drum 10 and a plurality of rotor blades 20 arranged in a circumferential direction of the drum 10, and fig. 1 shows a schematic view of a meridian projection plane of a typical drum. Wherein a conventional drum 10 and a rotor blade 20 are tenon-coupled, dovetail-shaped mortises 11 are provided on the circumferential surface of the drum 10, the mortises 11 extend along the circumferential direction of the drum 10, roots of the rotor blade 20 are provided with tenons adapted to the mortises 11, and the width of an opening at the radially outer end of the mortises 11 is smaller than the width of the inside of the mortises 11 so as to define tenons for restricting the rotor blade 20 in the mortises 11. The dovetail groove 11 provided on the drum 10 includes a dovetail groove body and an insertion port 103 communicating with the dovetail groove body, and the dovetail of the rotor blade 20 is circumferentially moved in the dovetail groove 11 to a predetermined installation position after being inserted by the insertion port 103. Problems with circumferential positioning and circumferential locking of the rotor blades are thus involved. The aircraft engine further comprises a locking block assembly 100 for limiting the circumferential movement of the rotor blade 20 in the dovetail groove, wherein the locking block assembly 100 is fixedly mounted in the dovetail groove to define the rotor blade 20 in the mounted position, see fig. 2, and the dovetail groove 11 of the drum 10 is provided with a mating groove 101 and a spherical recess 102 for mounting the locking block, see fig. 3, and the mounting schematic of the rotor blade, the locking block assembly 100 and the drum is shown in fig. 4.
Therefore, the typical locking block assembly is complex in structural form, the number of each rotary vane is small (two groups are generally adopted), batch purchasing and processing can be avoided, and the processing quality is difficult to ensure. The locking block component has a certain weight, and the balance of the rotor is affected. In order to assemble the locking block assembly, the matching groove and the spherical nest are designed and processed in the tenon groove of the drum barrel, so that the processing technology of the drum barrel is complex, and the cost is increased. It can be seen from fig. 2 and fig. 4 that the blade is locked circumferentially by the locking block, and the through hole is required to be machined on the blade edge plate, so that the flow passage surface is provided with pits, is not smooth, and affects the aerodynamic efficiency.
For circumferential dovetail connected drums and rotor blades, a conventional design employs a locking block locking arrangement for achieving blade circumferential positioning and circumferential locking. The prior art connection of the drum and the rotor blade has the following drawbacks:
1. the conventional locking block locking device has a complex structure, is small in use amount, cannot be purchased and processed in batches, and is difficult to ensure the processing quality;
2. conventional lock block assemblies have a weight that affects rotor balance.
3. The conventional drum mortises are required to be processed into matching grooves and spherical sockets with complex structural characteristics so as to assemble locking blocks, so that the drum mortises are complex in processing technology and high in cost;
4. for assembling and using the locking block, through holes are required to be processed on the blade edge plate, so that pits are formed on the channel surface, the channel surface is not smooth, and the pneumatic performance is affected.
Disclosure of Invention
The invention aims to provide an aeroengine, which aims to solve the problem that the locking structure of a blade is complex in the related art.
According to an aspect of an embodiment of the present invention, there is provided an aeroengine, the aeroengine comprising:
a drum comprising a mortise extending in a circumferential direction thereof, the bottom of the mortise being provided with a first positioning hole;
the blades are arranged side by side along the circumferential direction of the drum barrel, each blade comprises a blade body and a tenon which is connected with the blade body and is matched with the tenon groove, and a second positioning hole which is coaxial with the first positioning hole is formed in the blade;
and the positioning component is inserted into the first positioning hole and the second positioning hole to limit the tenon of the blade to move in the mortise along the circumferential direction of the drum.
In some embodiments, the second locating hole is provided on an end face of the tenon adjacent to an end of the bottom of the mortise.
In some embodiments, the blade further comprises a blade rim plate located between the blade body and the tenon, the blade rim plate protruding from the tenon in a circumferential direction of the drum, and the second locating hole is provided on the blade rim plate.
In some embodiments, a boss is provided on the blade edge plate, and the second locating hole is provided on the boss.
In some embodiments, the positioning member comprises a threaded rod, and at least one of the first positioning hole and the second positioning hole is a threaded hole that mates with the threaded rod.
In some embodiments, the positioning member is a bolt.
In some embodiments of the present invention, in some embodiments,
the first positioning hole is a through hole; and/or
The second positioning hole is a blind hole.
In some embodiments, the first mounting hole has an axial direction that coincides with a radial direction of the drum.
In some embodiments, the dovetail includes a dovetail body that is open at an outer end of the dovetail body in a radial direction of the drum, the dovetail having an open width that is less than a width of at least a portion of an interior cavity of the dovetail to limit removal of the blade from the dovetail in the radial direction of the drum.
In some embodiments, the dovetail slot further includes an insertion slot in communication with the dovetail slot body, the insertion slot having a width that is not less than a maximum width of the dovetail.
By applying the technical scheme of the invention, the circumferential positioning of the blade can be realized by inserting the positioning component into the first positioning hole and the second positioning hole, and the blade positioning device has the characteristics of simple structure, convenience in installation and low cost.
Other features of the present invention and its advantages will become apparent from the following detailed description of exemplary embodiments of the invention, which proceeds with reference to the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the related art, the drawings that are required to be used in the embodiments or the related technical descriptions will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort to those skilled in the art.
Fig. 1 shows a schematic structural view of a meridian projection plane of a drum of a related art aircraft engine;
FIG. 2 shows a schematic perspective view of a drum and rotor blade of a related art aircraft engine;
FIG. 3 shows a schematic structural view of the mortise of the drum of an aeroengine of the related art;
FIG. 4 shows a schematic top view of a drum and rotor blade of a related art aircraft engine;
FIG. 5 shows a schematic structural view of a drum and a blade according to a first embodiment of the present invention;
FIG. 6 shows a schematic structural view of a blade according to a first embodiment of the present invention;
FIG. 7 shows a schematic partial construction of a drum according to a first embodiment of the invention;
FIG. 8 shows a schematic structural view of a drum and blades of a second embodiment of the present invention;
FIG. 9 shows a schematic structural view of a blade according to a second embodiment of the present invention;
fig. 10 shows a schematic partial structural view of a drum according to a second embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
FIG. 5 shows a schematic structural view of the drum and blades of the aeroengine of the present embodiment;
fig. 6 shows a schematic structural view of a blade of the aeroengine of the present embodiment; fig. 7 shows a schematic partial structural view of a drum of an aircraft engine of an embodiment.
As shown in connection with fig. 5 to 7, the aircraft engine of the present embodiment includes a drum 2 and a plurality of blades arranged side by side in the circumferential direction of the drum 2, and the drum 2 is provided with a dovetail groove 7 extending in the circumferential direction of the drum 2. The blade comprises a blade body 1 and a tenon 6 connected with the blade body 1 and adapted to the mortise 7.
The mortise slot 7 includes a mortise body, an outer end of which in a radial direction of the drum 2 is open, and a width of the opening of the mortise 7 is smaller than a width of at least a portion of an inner cavity of the mortise 7 to restrict the blade from being separated from the mortise 7 in the radial direction.
In some embodiments, the dovetail groove 7 is a dovetail groove. In other embodiments, the mortise 7 has a substantially triangular cross-section, the apex of the triangle being farther from the axis of the drum 2 than the base opposite the apex.
The mortise 7 includes a mortise body and an insertion opening communicating with the mortise body, and a width of the insertion opening is not less than a maximum width of the tenon. When the blade is mounted on the drum 2, the tenon 6 of the blade is first inserted into the mortise 7 from the insertion port described above, and then the tenon 7 of the blade is moved in the mortise 7 in the circumferential direction of the drum 2, thereby moving the blade to a predetermined mounting position.
In this embodiment, the bottom of the dovetail groove 7 is provided with a first positioning hole 5, the blade is provided with a second positioning hole 8 coaxially arranged with the first positioning hole 5, the aeroengine further comprises a positioning component 3, and the positioning component 3 is inserted into the first positioning hole 5 and the second positioning hole 8 to limit the movement of the dovetail 6 of the blade in the dovetail groove 7 along the circumferential direction of the drum 2.
In this embodiment, through inserting the locating part 3 in first locating hole 5 and second locating hole 8, can realize the circumference location of blade, have simple structure, simple to operate and low cost's characteristics.
The first positioning holes 5 are through holes provided on the circumferential surface of the drum 2 as shown in fig. 5 and 7.
As shown in connection with fig. 5 and 6, the second positioning hole 8 is provided on the end face of the tenon 6 adjacent to the end of the bottom of the mortise 7.
In some embodiments, the second positioning hole 8 is a blind hole.
In the present embodiment, the first positioning hole 5 and the second positioning hole 8 are coaxial and the axial directions of the first positioning hole 5 and the second positioning hole 8 each extend in the radial direction of the drum 2.
In some embodiments, the positioning member 3 comprises a screw, and at least one of the first positioning hole 5 and the second positioning hole 8 is a threaded hole adapted to the screw.
In some embodiments, the positioning member 3 is a bolt. A mounting washer 4 is provided between the nut of the bolt and the inner circumferential surface of the drum 2.
The blade further comprises a blade rim plate 10, the blade rim plate 10 being located between the blade body 1 and the tenon 6, the blade rim plate 10 protruding from the tenon 6 in the circumferential direction of the drum 2. The blade edge plates 10 are arranged on the openings of the mortises 7 in a covering mode, and the blade edge plates 10 of two adjacent blades are abutted.
In this embodiment, the blades are positioned circumferentially in the dovetail groove 7 by bolts, so that the following technical effects are achieved:
1. the rotor blade circumferential positioning and circumferential locking are realized, the locking structure is simple, the processing difficulty is reduced, the cost is reduced, the universality degree is high, and the installation is convenient.
2. The bolts are less heavy than conventional lock block assemblies, improving rotor balance to some extent.
3. The drum mortise structure is simpler, the processing of the matching groove and the spherical nest is avoided, the processing technology is convenient, and the cost is reduced.
4. The blade edge plate does not need to be provided with a through hole, so that pits on the surface of the runner are avoided, and the aerodynamic performance is improved.
5. The bolts are installed from inside to outside of the inner side of the drum, and when the rotor works, the bolts can abut against the inner side wall surface of the drum under the action of centrifugal force, so that the failure is not easy to occur.
Example two
FIG. 8 shows a schematic structural view of the drum and blades of the aeroengine of the present embodiment;
fig. 9 shows a schematic structural view of a blade of the aeroengine of the present embodiment; fig. 10 shows a schematic structural view of a part of a drum of an aeroengine of an embodiment.
As shown in connection with fig. 8 to 10, the aircraft engine of the present embodiment includes a drum 2 and a plurality of blades arranged side by side in the circumferential direction of the drum 2, and the drum 2 is provided with a dovetail groove 7 extending in the circumferential direction of the drum 2. The blade comprises a blade body 1 and a tenon 6 connected with the blade body 1 and adapted to the mortise 7.
The mortise slot 7 includes a mortise body, an outer end of which in a radial direction of the drum 2 is open, and a width of the opening of the mortise 7 is smaller than a width of at least a portion of an inner cavity of the mortise 7 to restrict the blade from being separated from the mortise 7 in the radial direction.
In some embodiments, the dovetail groove 7 is a dovetail groove. In other embodiments, the mortise 7 has a substantially triangular cross-section, the apex of the triangle being farther from the axis of the drum 2 than the base opposite the apex.
The mortise 7 includes a mortise body and an insertion opening communicating with the mortise body, and a width of the insertion opening is not less than a maximum width of the tenon. When the blade is mounted on the drum 2, the tenon 6 of the blade is first inserted into the mortise 7 from the insertion port described above, and then the tenon 7 of the blade is moved in the mortise 7 in the circumferential direction of the drum 2, thereby moving the blade to a predetermined mounting position.
In this embodiment, the bottom of the dovetail groove 7 is provided with a first positioning hole 5, the blade is provided with a second positioning hole 8 coaxially arranged with the first positioning hole 5, the aeroengine further comprises a positioning component 3, and the positioning component 3 is inserted into the first positioning hole 5 and the second positioning hole 8 to limit the movement of the dovetail 6 of the blade in the dovetail groove 7 along the circumferential direction of the drum 2.
In this embodiment, through inserting the locating part 3 in first locating hole 5 and second locating hole 8, can realize the circumference location of blade, have simple structure, simple to operate and low cost's characteristics.
The first positioning holes 5 are through holes provided on the circumferential surface of the drum 2 as shown in fig. 8 and 10.
As shown in connection with fig. 8 and 9, the blade further comprises a blade rim plate 10, the blade rim plate 10 being located between the blade body 1 and the tenon 6, the blade rim plate 10 protruding from the tenon 6 in the circumferential direction of the drum 2. The second positioning holes 8 are provided on the blade edge plate 10.
In some embodiments, the blade edge plate 10 is provided with a boss 11, and the second positioning hole 8 is provided on the boss 11.
In some embodiments, the second positioning hole 8 is a blind hole.
In the present embodiment, the first positioning hole 5 and the second positioning hole 8 are coaxial and the axial directions of the first positioning hole 5 and the second positioning hole 8 each extend in the radial direction of the drum 2.
In some embodiments, the positioning member 3 comprises a screw, and at least one of the first positioning hole 5 and the second positioning hole 8 is a threaded hole adapted to the screw.
In some embodiments, the positioning member 3 is a bolt. A mounting washer 4 is provided between the nut of the bolt and the inner circumferential surface of the drum 2.
In this embodiment, the blades are positioned circumferentially in the dovetail groove 7 by bolts, so that the following technical effects are achieved:
1. the rotor blade circumferential positioning and circumferential locking are realized, the locking structure is simple, the processing difficulty is reduced, the cost is reduced, the universality degree is high, and the installation is convenient.
2. The bolts are less heavy than conventional lock block assemblies, improving rotor balance to some extent.
3. The drum mortise structure is simpler, the processing of the matching groove and the spherical nest is avoided, the processing technology is convenient, and the cost is reduced.
4. The blade edge plate does not need to be provided with a through hole, so that pits on the surface of the runner are avoided, and the aerodynamic performance is improved.
5. The bolts are installed from inside to outside of the inner side of the drum, and when the rotor works, the bolts can abut against the inner side wall surface of the drum under the action of centrifugal force, so that the failure is not easy to occur.
The foregoing is illustrative of the present invention and is not to be construed as limiting thereof, but rather, any modification, equivalent replacement, improvement or the like which comes within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (5)
1. An aircraft engine, comprising:
a drum (2) comprising a mortise (7) extending along its circumference, the bottom of the mortise (7) being provided with a first positioning hole (5);
a plurality of blades arranged side by side along the circumferential direction of the drum (2), each blade comprising a blade body (1) and a tenon (6) connected with the blade body (1) and adapted to the tenon groove (7), wherein a second positioning hole (8) coaxially arranged with the first positioning hole (5) is arranged on the blade;
a positioning component (3) inserted into the first positioning hole (5) and the second positioning hole (8) to limit the tenon (6) of the blade to move in the tenon groove (7) along the circumferential direction of the drum (2), the blade further comprises a blade flange (10), the blade flange (10) is positioned between the blade body (1) and the tenon (6), the blade flange (10) protrudes out of the tenon (6) along the circumferential direction of the drum (2), the second positioning hole (8) is arranged on the blade flange (10),
a boss (11) is arranged on the blade edge plate (10), the second positioning hole (8) is arranged on the boss (11),
the first positioning hole (5) is a through hole; the second positioning hole (8) is a blind hole, and the axial direction of the second positioning hole (8) is consistent with the radial direction of the drum barrel (2).
2. The aircraft engine according to claim 1, characterized in that the positioning component (3) comprises a screw, at least one of the first positioning hole (5) and the second positioning hole (8) being a threaded hole adapted to the screw.
3. An aeroengine as claimed in claim 1, wherein said positioning member (3) is a bolt.
4. An aeroengine according to claim 1, wherein the dovetail groove (7) comprises a dovetail groove body which is open at its radially outer end in the drum (2), the dovetail groove (7) having an open width smaller than the width of at least a portion of the inner cavity of the dovetail groove (7) to limit the blade from escaping the dovetail groove (7) in the radial direction of the drum (2).
5. The aircraft engine according to claim 4, characterized in that the dovetail groove (7) further comprises an insertion opening communicating with the dovetail groove body, the insertion opening having a width not smaller than the maximum width of the dovetail.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110126390 | 2021-01-29 | ||
| CN2021101263907 | 2021-01-29 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114810220A CN114810220A (en) | 2022-07-29 |
| CN114810220B true CN114810220B (en) | 2024-02-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110330532.1A Active CN114810220B (en) | 2021-01-29 | 2021-03-25 | Aero-engine |
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| CN (1) | CN114810220B (en) |
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| EP1840338A1 (en) * | 2006-03-28 | 2007-10-03 | Siemens Aktiengesellschaft | Arrangement for axial locking of turbine blades in a rotor and gas turbine with such an arrangement |
| CN203441545U (en) * | 2013-08-05 | 2014-02-19 | 汉美综合科技（常州）有限公司 | Bolt shaft tightening impeller and connection structure of impeller and turbine shaft |
| CN204113351U (en) * | 2014-07-28 | 2015-01-21 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Locking device between blade and wheel disc |
| CN205799150U (en) * | 2016-06-22 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of positioner for grinding blade tip |
| CN206448844U (en) * | 2017-02-22 | 2017-08-29 | 成都成发科能动力工程有限公司 | A kind of turbine rotor movable vane piece and turbine rotor movable vane slice mounting structure |
| EP3751102A1 (en) * | 2019-06-11 | 2020-12-16 | Safran Aero Boosters SA | Rotor for the compressor of a turbomachine and corresponding assembly method |
| CN112196626A (en) * | 2020-08-31 | 2021-01-08 | 中国航发南方工业有限公司 | Small turbine for aeroengine |
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