CN114810220A - Aircraft engine - Google Patents
Aircraft engine Download PDFInfo
- Publication number
- CN114810220A CN114810220A CN202110330532.1A CN202110330532A CN114810220A CN 114810220 A CN114810220 A CN 114810220A CN 202110330532 A CN202110330532 A CN 202110330532A CN 114810220 A CN114810220 A CN 114810220A
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- Prior art keywords
- mortise
- blade
- drum
- positioning hole
- aircraft engine
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000012545 processing Methods 0.000 description 12
- 238000003780 insertion Methods 0.000 description 10
- 230000037431 insertion Effects 0.000 description 10
- 238000009434 installation Methods 0.000 description 8
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
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
Abstract
The invention relates to an aircraft engine, comprising: the drum barrel (2) comprises a mortise (7) extending along the circumferential direction of the drum barrel, and the bottom of the mortise (7) is provided with a first positioning hole (5); the blades are arranged side by side along the circumferential direction of the drum barrel (2), each blade comprises a blade body (1) and a tenon (6) which is connected with the blade body (1) and is matched with the tenon groove (7), and a second positioning hole (8) which is coaxial 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) to limit the tenon (6) of the blade to move along the circumferential direction of the drum barrel (2) in the mortise (7), and the positioning component (3) is inserted into the first positioning hole (5) and the second positioning hole (8) to realize the circumferential positioning of the blade.
Description
Technical Field
The invention relates to the field of aviation equipment, in particular to an aero-engine.
Background
Referring to fig. 1 to 4, an aircraft engine comprises a drum 10 and a plurality of rotor blades 20 arranged along the circumference of the drum 10, and fig. 1 shows a schematic representation of the structure of a typical meridian projection plane of the drum. Wherein, a common drum 10 is in tenon connection with a rotor blade 20, a dovetail-shaped mortise 11 is arranged on the circumferential surface of the drum 10, the mortise 11 extends along the circumferential direction of the drum 10, a tenon matched with the mortise 11 is arranged at the root of the rotor blade 20, and the width of the opening at the radial outer end of the mortise 11 is smaller than the width inside the mortise 11, so as to limit the tenon of the rotor blade 20 in the mortise 11. The mortise 11 provided in the drum 10 includes a mortise body and an insertion opening 103 communicating with the mortise body, and the rotor blade 20 is inserted through the insertion opening 103 and then moved in the mortise 11 in a circumferential direction to a predetermined installation position. Problems with circumferential positioning and circumferential locking of the rotor blades are therefore involved. The aircraft engine further comprises a locking block assembly 100 for limiting the circumferential movement of the rotor blade 20 in the mortise, the locking block assembly 100 is fixedly arranged in the mortise to limit the rotor blade 20 at the installation position, see fig. 2, a matching groove 101 and a spherical socket 102 for installing the locking block are required to be designed on the mortise 11 of the drum 10, see fig. 3, and the installation schematic diagram 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 the rotary blades used in each stage is small (two groups are generally adopted), batch purchasing and processing cannot be achieved, and the processing quality is difficult to guarantee. The lock block assembly has a certain weight, which affects the rotor balance. In order to match with the locking block assembly for assembly, a matching groove and a spherical nest need to be designed and processed in the mortise of the drum barrel, so that the processing technology of the drum barrel is complex, and the cost is increased. As can be seen from the figures 2 and 4, the locking blocks are adopted to circumferentially lock the blades, through holes need to be processed on the blade edge plates, and therefore pits exist on the flow channel surface, the flow channel surface is not smooth, and the pneumatic efficiency is affected.
For a drum and a rotor blade which are connected by a circumferential dovetail joint, a locking block locking device is adopted in the conventional design for realizing circumferential positioning and circumferential locking of the blade. The prior art drum and rotor blade attachment structure has the following drawbacks:
1. the conventional locking block locking device has a complex structure and a small using amount, is not purchased and processed in batches, and is difficult to ensure the processing quality;
2. conventional lock block assemblies have a certain weight that affects rotor balance.
3. The conventional drum mortise needs to be processed with a matching groove and a spherical socket with complex structural characteristics to assemble a locking block, so that the drum mortise is complex in processing technology and high in cost;
4. for the assembly use latch segment, need at blade flange processing through-hole, lead to the runner face to have the pit, unsmooth influences the aerodynamic performance.
Disclosure of Invention
The invention aims to provide an aircraft engine to solve the problem of complicated blade locking structure in the related art.
According to an aspect of an embodiment of the present invention, there is provided an aircraft engine, comprising:
the drum comprises a mortise extending along the circumferential direction of the drum, and the bottom of the mortise is 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 mortise, and a second positioning hole which is coaxial with the first positioning hole is formed in each blade;
and the positioning component is inserted into the first positioning hole and the second positioning hole so as to limit the tenon of the blade to move in the mortise along the circumferential direction of the drum barrel.
In some embodiments, the second positioning hole is provided on an end surface of the tenon adjacent to an end of the bottom of the mortise.
In some embodiments, the blade further includes a blade rim plate, the blade rim plate is located between the blade body and the tenon, the blade rim plate protrudes from the tenon along the circumferential direction of the drum, and the second positioning hole is formed in the blade rim plate.
In some embodiments, the blade edge plate is provided with a boss, and the second positioning hole is provided on the boss.
In some embodiments, the positioning component comprises a threaded rod, and at least one of the first positioning hole and the second positioning hole is a threaded hole matched with the threaded rod.
In some embodiments, the positioning member is a bolt.
In some embodiments of the present invention, the,
the first positioning hole is a through hole; and/or
The second positioning hole is a blind hole.
In some embodiments, the axial direction of the first mounting hole coincides with the radial direction of the drum.
In some embodiments, the tongue and groove includes a tongue and groove body, an outer end of the tongue and groove body in a radial direction of the drum being open, a width of the opening of the tongue and groove being smaller than a width of at least a portion of the inner cavity of the tongue and groove to limit the blade from escaping the tongue and groove in the radial direction of the drum.
In some embodiments, the mortise further comprises an insertion opening in communication with the mortise body, the insertion opening having a width not less than a maximum width of the tenon.
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 advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, 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 needed to be used in the description of the embodiments or the related art will be briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 shows a schematic view of the structure of a meridian projection plane of a drum of a related art aircraft engine;
FIG. 2 illustrates a perspective view of a drum and rotor blade of a related art aircraft engine;
FIG. 3 shows a schematic view of the structure of a tongue and groove of a drum of a related art aircraft engine;
FIG. 4 illustrates 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 blades of a first embodiment of the present invention;
FIG. 6 shows a schematic structural view of a blade of a first embodiment of the present invention;
fig. 7 shows a schematic structural view of a part of the drum of the 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 of a second embodiment of the present invention;
fig. 10 shows a schematic structural view of a part of a drum of a second embodiment 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 of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example one
FIG. 5 shows a schematic structural view of a drum and blades of the aircraft engine of the present embodiment;
FIG. 6 shows a schematic structural view of a blade of the aircraft engine of the present embodiment; fig. 7 shows a schematic structural view of a part 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 comprises a drum 2 and a plurality of blades arranged side by side along the circumferential direction of the drum 2, the drum 2 being provided with a tongue-and-groove 7 extending along the circumferential direction of the drum 2. The blade comprises a blade body 1 and a tenon 6 which is connected with the blade body 1 and is matched with a mortise 7.
The mortise 7 comprises a mortise body, the outer end of the mortise body in the radial direction of the drum 2 is open, and the width of the opening of the mortise 7 is smaller than the width of at least a part of the inner cavity of the mortise 7 so as to limit the blade from escaping from the mortise 7 in the radial direction.
In some embodiments, the tongue groove 7 is a dovetail groove. In other embodiments the tongue groove 7 is substantially triangular in cross-section, the apex of the triangle being further from the axis of the drum 2 than the base opposite the apex.
The mortise 7 comprises a mortise body and an insertion opening communicated with the mortise body, and the width of the insertion opening is not less than the maximum width of the tenon. When mounting the blade on the drum 2, the tenon 6 of the blade is first inserted into the mortise 7 from the insertion opening 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 mortise 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, and the aircraft engine further comprises a positioning component 3, wherein 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 in the mortise 7 along the circumferential direction of the drum 2.
In this embodiment, 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, and the positioning device has the characteristics of simple structure, convenience in installation and low cost.
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 fig. 5 and 6 in conjunction, the second positioning hole 8 is provided on the end surface of the tenon 6 adjacent to one end of the bottom of the mortise 7.
In some embodiments, the second positioning hole 8 is a blind hole.
In this 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 extend in the radial direction of the drum 2.
In some embodiments, the positioning component 3 comprises a threaded rod, and at least one of the first positioning hole 5 and the second positioning hole 8 is a threaded hole adapted to the threaded rod.
In some embodiments, the positioning member 3 is a bolt. A mounting washer 4 is arranged between the nut of the bolt and the inner circumferential surface of the drum 2.
The blade further comprises a blade platform 10, the blade platform 10 being located between the blade body 1 and the rabbet 6, the blade platform 10 protruding from the rabbet 6 in the circumferential direction of the drum 2. The blade edge plates 10 are covered on the opening of the mortise 7, and the blade edge plates 10 of two adjacent blades are abutted.
In this embodiment, the blade is circumferentially positioned in the mortise 7 by the bolt, so that the following technical effects are achieved:
1. the locking mechanism has the advantages that the circumferential positioning and circumferential locking of the rotor blades 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 lighter than conventional locking block assemblies, improving rotor balance to a certain extent.
3. The drum mortise structure is simpler, avoids processing cooperation groove and spherical nest, makes things convenient for processing technology, reduce cost.
4. The blade edge plate does not need to be provided with a through hole, thereby avoiding a pit on the runner surface and improving the pneumatic performance.
5. The bolts are arranged from the inside to the outside of the drum barrel, and when the rotor works, the bolts can tightly abut against the inner side wall surface of the drum barrel 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 a drum and blades of the aircraft engine of the present embodiment;
FIG. 9 shows a schematic structural view of a blade of the aircraft engine of the present embodiment; fig. 10 shows a schematic structural view of a part of a drum of an aircraft engine of an embodiment.
As shown in connection with fig. 8 to 10, the aero-engine of the present embodiment comprises a drum 2 and a plurality of blades arranged side by side along the circumferential direction of the drum 2, the drum 2 being provided with a tongue-and-groove 7 extending along the circumferential direction of the drum 2. The blade comprises a blade body 1 and a tenon 6 which is connected with the blade body 1 and is matched with a mortise 7.
The mortise 7 comprises a mortise body, the outer end of the mortise body in the radial direction of the drum 2 is open, and the width of the opening of the mortise 7 is smaller than the width of at least a part of the inner cavity of the mortise 7 so as to limit the blade from escaping from the mortise 7 in the radial direction.
In some embodiments, the tongue groove 7 is a dovetail groove. In other embodiments the tongue groove 7 is substantially triangular in cross-section, the apex of the triangle being further from the axis of the drum 2 than the base opposite the apex.
The mortise 7 comprises a mortise body and an insertion opening communicated with the mortise body, and the width of the insertion opening is not less than the maximum width of the tenon. When mounting the blade on the drum 2, the tenon 6 of the blade is first inserted into the mortise 7 from the insertion opening 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 mortise 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, and the aircraft engine further comprises a positioning component 3, wherein 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 in the mortise 7 along the circumferential direction of the drum 2.
In this embodiment, 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, and the positioning device has the characteristics of simple structure, convenience in installation and low cost.
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 fig. 8 and 9, the blade further includes a blade platform 10, the blade platform 10 is located between the blade body 1 and the tenon 6, and the blade platform 10 protrudes from the tenon 6 along the circumferential direction of the drum 2. The second positioning hole 8 is provided on the blade rim plate 10.
In some embodiments, the vane 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 this 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 extend in the radial direction of the drum 2.
In some embodiments, the positioning component 3 comprises a threaded rod, and at least one of the first positioning hole 5 and the second positioning hole 8 is a threaded hole adapted to the threaded rod.
In some embodiments, the positioning member 3 is a bolt. A mounting washer 4 is arranged between the nut of the bolt and the inner circumferential surface of the drum 2.
In this embodiment, the blade is circumferentially positioned in the mortise 7 by the bolt, so that the following technical effects are achieved:
1. the locking mechanism has the advantages that the circumferential positioning and circumferential locking of the rotor blades 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 lighter than conventional locking block assemblies, improving rotor balance to a certain extent.
3. The drum mortise structure is simpler, avoids processing cooperation groove and spherical nest, makes things convenient for processing technology, reduce cost.
4. The blade edge plate does not need to be provided with a through hole, thereby avoiding a pit on the runner surface and improving the pneumatic performance.
5. The bolts are arranged from the inside to the outside of the drum barrel, and when the rotor works, the bolts can tightly abut against the inner side wall surface of the drum barrel under the action of centrifugal force, so that the failure is not easy to occur.
The present invention is not limited to the above exemplary embodiments, and any modifications, equivalent replacements, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An aircraft engine, comprising:
the drum barrel (2) comprises a mortise (7) extending along the circumferential direction of the drum barrel, and the bottom of the mortise (7) is provided with a first positioning hole (5);
the blades are arranged side by side along the circumferential direction of the drum barrel (2), each blade comprises a blade body (1) and a tenon (6) which is connected with the blade body (1) and is matched with the mortise (7), and a second positioning hole (8) which is coaxial with the first positioning hole (5) is formed in each blade;
and 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 in the mortise (7) along the circumferential direction of the drum (2).
2. An aircraft engine according to claim 1, characterised in that the second locating hole (8) is provided in the end face of the tenon (6) adjacent to the end of the base of the mortise (7).
3. The aircraft engine according to claim 1, characterized in that the blade further comprises a blade flange (10), the blade flange (10) is located between the blade body (1) and the tenon (6), the blade flange (10) protrudes from the tenon (6) along the circumferential direction of the drum (2), and the second positioning hole (8) is formed in the blade flange (10).
4. An aircraft engine according to claim 3, characterised in that a boss (11) is provided on the blade platform (10), the second locating hole (8) being provided on the boss (11).
5. An aircraft engine according to claim 1, characterised in that the locating component (3) comprises a threaded rod, at least one of the first locating hole (5) and the second locating hole (8) being a threaded hole adapted to the threaded rod.
6. An aircraft engine according to claim 1, characterised in that the positioning means (3) are bolts.
7. The aircraft engine of claim 1,
the first positioning hole (5) is a through hole; and/or
The second positioning hole (8) is a blind hole.
8. An aircraft engine according to claim 1, characterised in that the axial direction of the first mounting hole (8) coincides with the radial direction of the drum (2).
9. An aircraft engine according to claim 1, characterised in that the mortise (7) comprises a mortise body whose outer end in the radial direction of the drum (2) is open, the open width of the mortise (7) being smaller than the width of at least a part of the inner cavity of the mortise (7) to limit the blades from escaping from the mortise (7) in the radial direction of the drum (2).
10. An aircraft engine according to claim 9, characterised in that the mortise (7) further comprises an insert opening communicating with the mortise body, the insert opening having a width not less than the maximum width of the tenon.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2021101263907 | 2021-01-29 | ||
| CN202110126390 | 2021-01-29 |
Publications (2)
| Publication Number | Publication Date |
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| CN114810220A true CN114810220A (en) | 2022-07-29 |
| CN114810220B CN114810220B (en) | 2024-02-20 |
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| CN202110330532.1A Active CN114810220B (en) | 2021-01-29 | 2021-03-25 | Aero-engine |
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2021
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| US20150159496A1 (en) * | 2011-04-05 | 2015-06-11 | Snecma | Sealing ring for a turbine stage of an aircraft turbomachine, comprising slotted anti-rotation pegs |
| 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 |
| US20200072064A1 (en) * | 2018-08-31 | 2020-03-05 | Rolls-Royce Corporation | Platform with axial attachment for blade with circumferential attachment |
| US20200102842A1 (en) * | 2018-09-27 | 2020-04-02 | Rolls-Royce Corporation | Turbine wheel assembly with ceramic matrix composite blades |
| 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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