CN113153445A - Tenon joint structure of turbine working blade of turbine engine and turbine engine - Google Patents
Tenon joint structure of turbine working blade of turbine engine and turbine engine Download PDFInfo
- Publication number
- CN113153445A CN113153445A CN202110404831.5A CN202110404831A CN113153445A CN 113153445 A CN113153445 A CN 113153445A CN 202110404831 A CN202110404831 A CN 202110404831A CN 113153445 A CN113153445 A CN 113153445A
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- mortise
- tenon
- turbine
- blade
- turbine engine
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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
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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
- F01D5/32—Locking, e.g. by final locking blades or keys
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a mortise joint structure of a turbine working blade of a turbine engine and the turbine engine, which comprise a turbine disc and blades, wherein the turbine disc comprises a turbine disc main body and a tenon structure, the tenon structure comprises a first tenon and a second tenon positioned at the middle end part of the first tenon, convex teeth are symmetrically distributed on two sides of the first tenon, and a groove structure is formed between two adjacent tenon structures; the blade comprises a blade main body and a mortise structure matched with the tenon structure in a joggled manner, wherein the mortise structure comprises a first mortise matched with the first tenon in a joggled manner and a second mortise matched with the second tenon in a joggled manner and positioned in the first mortise; the first mortise comprises a third mortise and a fourth mortise; a limiting part for limiting the axial direction of the blade is arranged between one end, close to the groove structure, of the first mortise and the groove structure. The joggle structure of the turbine working blade of the turbine engine provided by the invention can avoid the problem of overlarge stress caused by overlarge cantilever of the blade edge plate of a typical joggle structure due to the reduction of the number of single-stage turbine rotor blades.
Description
Technical Field
The present invention relates to the field of gas turbine engines, and more particularly, to a dovetail structure for turbine blades of a turbine engine. Furthermore, the invention also relates to a gas turbine engine comprising the dovetail structure of the turbine engine turbine working blade.
Background
At present, a turbine working blade is connected with a turbine disc in a joggle mode, as shown in fig. 1 and fig. 2, a blade tenon is wedge-shaped, trapezoidal or semicircular teeth are symmetrically distributed on two sides of the blade tenon, and mortises with the same molded surface are correspondingly formed in the edge of the turbine disc. In operation the centrifugal force of the blade forces the bearing surfaces of all the teeth of the tenon against the teeth of the disk. Under the action of centrifugal force and bending moment of blade, the tenon teeth are sheared and bent, the working surfaces of all teeth of the tenon are pressed, and the cross-sections of the tenon are stretched. At present, the aeroengine is rapidly developed, the power/weight ratio of the aeroengine is continuously increased, and the number of blades of each stage of a turbine working blade shows a descending trend. However, as the number of blades per stage is reduced, the cantilever length of the platform of the turbine rotor blade (as shown by L1 and L2 in FIG. 1) is increased, the stress at the position where the platform meets the extension root is increased, and the strength of the blade is difficult to meet the design requirement.
Disclosure of Invention
The invention provides a joggle structure of a turbine working blade of a turbine engine, which aims to solve the technical problem that the strength of the blade can hardly meet the design requirement due to the fact that the stress of the joint of a flange plate and a root extension is increased because the length of a cantilever of the flange plate of the turbine working blade is increased along with the reduction of the number of rotor blades of each stage.
The technical scheme adopted by the invention is as follows:
a joggle structure of a turbine working blade of a turbine engine comprises a turbine disc and a plurality of blades uniformly distributed on the periphery of the turbine disc, wherein the turbine disc comprises a turbine disc main body, tenon structures are uniformly distributed on the periphery of the turbine disc main body, each tenon structure comprises a first tenon and a second tenon positioned at the middle end part of the first tenon, convex teeth are symmetrically distributed on two sides of each first tenon, and a groove structure is formed between every two adjacent tenon structures; the blade comprises a blade main body, a mortise structure which is arranged at a flange plate of the blade main body and is used for being in mortise joint fit with the tenon structure, and the mortise structure comprises a first mortise which is in mortise joint fit with the first tenon and a second mortise which is in mortise joint fit with the second tenon and is arranged in the first mortise; the first tenon groove comprises a third tenon groove matched with the profile of the convex tooth on one side of the first tenon and a fourth tenon groove matched with the profile of the convex tooth on the other side of the first tenon; a limiting part for limiting the axial direction of the blade is arranged between one end, close to the groove structure, of the first mortise and the groove structure.
Further, the circumferential width of the platform of the blade body is equal to the circumferential width of the tongue and groove structure.
Further, the circumferential width of the first mortise is smaller than half of the circumferential width of the groove structure; the circumferential width of the second mortise is less than half of the circumferential width of the groove structure.
Further, the first mortise adopts a longitudinal tree-shaped mortise; the first tenon is a longitudinal tree-shaped tenon matched with the first mortise.
Furthermore, the cross sections of the second mortise and the second tenon are in a mutually matched convex structure.
Furthermore, the locating part adopts one of locking plate, guiding disc, baffle, piston ring.
Furthermore, the locking plate is of a cuboid structure; the locking plate comprises a base body and folding sections, and the folding sections are arranged at two ends of the base body and can be freely bent and used for being attached to and locked and connected with the turbine disc.
Further, the edge plate of the blade main body comprises 1 blade profile, 2 blade profiles or 3 blade profiles.
According to another aspect of the invention, a gas turbine engine is also provided, including the above-described dovetail structure for turbine engine turbine rotor blades.
The invention has the following beneficial effects:
the mortise structure of the turbine working blade of the turbine engine comprises a turbine disc and blades, a mortise structure is designed at a blade edge plate, the turbine disc is provided with a tenon structure matched with the mortise structure, the blades are locked and connected with the turbine disc, and the traditional fixing mode of the turbine disc and the blades is changed, namely the turbine blades are matched with the mortise structure on the turbine disc through the tenons, and the mortise structure at the blade edge plate avoids the problems that the number of the blades of a single-stage turbine rotor is reduced, and the stress is overlarge due to overlarge cantilever of the blade edge plate of a typical mortise structure. The tongue-and-groove structure of blade can freely be packed into turbine disc's tenon structure on, and the rethread locating part carries out axial spacing to the blade, restriction blade axial displacement. During operation, the centrifugal force of the blade forces the tenon on the mortise structure of the blade to press on the convex teeth of the turbine disc, and the transmission routes of the centrifugal force and the bending moment are respectively transmitted from the two ends of the mortise structure to the tenon structure of the turbine disc at the middle position and then transmitted to the turbine disc main body, so that the extrusion stress borne by the working surface of the blade is dispersed. The joggle structure of the turbine working blade of the turbine engine is novel in design, simple and convenient to assemble, high in practicability and stable in performance.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic illustration of a prior art dovetail connection of a turbine rotor blade to a turbine disk;
FIG. 2 is a prior art turbine rotor blade force transmission path;
FIG. 3 is a dovetail configuration view of a preferred turbine engine turbine rotor blade of the present invention;
FIG. 4 is a block diagram of a preferred blade of the present invention;
FIG. 5 is a block diagram of a preferred turbine disk of the present invention;
FIG. 6 is an assembly view of a dovetail configuration of a preferred turbine engine turbine rotor blade of the present invention; and
FIG. 7 is a blade force transmission path diagram for a dovetail configuration of a preferred turbine engine turbine rotor blade according to the present invention.
The reference numbers illustrate:
1. a turbine disk; 2. a blade; 3. a limiting member;
11. a turbine disk body; 12. a tenon structure; 121. a first tenon; 122. a second tenon; 13. a groove structure;
21. a blade main body; 22. a tongue and groove structure; 221. a first tongue-and-groove; 2211. a third mortise; 2212. a fourth mortise; 222. and a second mortise.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic illustration of a prior art dovetail connection of a turbine rotor blade to a turbine disk; FIG. 2 is a prior art turbine rotor blade force transmission path; FIG. 3 is a dovetail configuration view of a preferred turbine engine turbine rotor blade of the present invention; FIG. 4 is a block diagram of a preferred blade of the present invention; FIG. 5 is a block diagram of a preferred turbine disk of the present invention; FIG. 6 is an assembly view of a dovetail configuration of a preferred turbine engine turbine rotor blade of the present invention; FIG. 7 is a blade force transmission path diagram for a dovetail configuration of a preferred turbine engine turbine rotor blade according to the present invention.
As shown in fig. 3, 4, 5 and 7, the mortise structure of the turbine working blade of the turbine engine of the present embodiment includes a turbine disc 1 and a plurality of blades 2 uniformly distributed around the turbine disc 1, the turbine disc 1 includes a turbine disc main body 11, tenon structures 12 uniformly distributed around the turbine disc main body 11, the tenon structures 12 include first tenons 121 and second tenons 122 located at the middle end portions of the first tenons 121, protruding teeth are symmetrically distributed on two sides of the first tenons 121, and a groove structure 13 is formed between two adjacent tenon structures 12; the blade 2 comprises a blade main body 21, a mortise structure 22 which is arranged at a flange plate of the blade main body 21 and is used for being in mortise fit with the tenon structure 12, wherein the mortise structure 22 comprises a first mortise 221 which is in mortise fit with the first tenon 121 and a second mortise 222 which is in mortise fit with the second tenon 122 and is arranged inside the first mortise 221; the first mortise 221 comprises a third mortise 2211 matched with the profile of the convex teeth on one side of the first tenon 121, and a fourth mortise 2212 matched with the profile of the convex teeth on the other side of the first tenon 121; a limiting piece 3 for axial limiting of the blade 2 is arranged between one end of the first mortise 221 close to the groove structure 13 and the groove structure 13. The mortise structure of the turbine working blade of the turbine engine comprises a turbine disc 1 and blades 2, a mortise structure 22 is designed at the edge plate of each blade 2, the turbine disc 1 is provided with a tenon structure 12 matched with the mortise structure 22, locking connection of the blades 2 and the turbine disc 1 is achieved, and the problem that the number of single-stage turbine rotor blades 2 is reduced, and the problem that stress is overlarge due to overlarge cantilever of the edge plate of the typical mortise structure blade 2 is solved in the traditional fixing mode of the turbine disc 1 and the blades 2, namely the turbine rotor blades 2 are matched with the mortise structure 22 on the turbine disc 1 through tenons, and the mortise structure 22 at the edge plate of each blade 2 is adopted. The tongue-and-groove structure 22 of the blade 2 can be freely installed on the tenon structure 12 of the turbine disc 1, and then the blade 2 is axially limited by the limiting part 3, so that the axial movement of the blade 2 is limited. The joggle structure of the turbine working blade of the turbine engine is novel in design, simple and convenient to assemble, high in practicability and stable in performance.
As shown in fig. 2 and 4, in the rotor structure of a gas turbine adopting a typical dovetail structure, when the number of the blades 2 is reduced, the cantilever section L1 of the blade 2 flange plate is increased, and the stress at the flange plate and the transition pilot circle of the root extension is increased and the strength is unacceptable, so that the dovetail structure L1 adopting the turbine engine turbine working blade is shortened, and the stress at the transition pilot circle can be controlled within an allowable range.
Above-mentioned turbine disk 1 both can have designed into tenon structure 12 according to blade 2's structure redesign, also can adopt current turbine disk 1 to protruding body between two mortises with current turbine disk is as tenon structure 12, and the tenon tooth of mortise is as the dogtooth of tenon structure 12, and the mortise is as groove structure 13, thereby does not change the structure of former turbine disk, only need make new blade 2, reduces manufacturing cost, increases work efficiency.
In the present embodiment, the circumferential width of the platform of the blade body 21 is equal to the circumferential width of the tongue and groove structure 22. The mortise structure of the turbine engine turbine working blade is designed to be the same as the circumferential width of the flange plate of the blade main body 21 in order to solve the problem that a large cantilever structure appears on the flange plate of a typical mortise structure, namely, the mortise structure 22 is aligned with the two ends of the flange plate in the circumferential direction, disturbance to surrounding air flow during rotation is reduced, and the stability of the turbine structure of the engine is further ensured. Moreover, since the mortise structure 22 includes the first mortise 221 and the second mortise 222, the first mortise 221 and the second mortise 222 are respectively located at the left and right sides of the tenon structure 12, that is, fall into the previous groove structure 13 and the subsequent groove structure 13, and therefore, the mortise structure 22 is aligned with both ends of the flange in the circumferential direction, so as to be conveniently inserted into the groove structure 13.
In this embodiment, the circumferential width of the first tongue-and-groove 221 is less than half of the circumferential width of the groove structure 13. The second groove 222 has a circumferential width less than half the circumferential width of the groove structure 13. Form groove structure 13 between two above-mentioned adjacent tenon structures 12, tenon structure 12 and mortise structure 22 joggle cooperation, first tongue-and-groove 221 and fourth tongue-and-groove 2212 of mortise structure 22 are located the both ends of tenon structure 12 respectively, also fall into in preceding groove structure 13 and the last groove structure 13 at tenon structure 12 both ends respectively promptly to make a groove structure 13 hold fourth tongue-and-groove 2212 of last tongue-and-groove structure 22 and the third tongue-and-groove 2211 of next tongue-and-groove structure 22. Thus, the first tongue-and-groove 221 has a circumferential width less than half the circumferential width of the groove structure 13. The second groove 222 has a circumferential width less than half the circumferential width of the groove structure 13. So that the tongue-and-groove structure 22 can fall into the groove structure 13 to achieve the mounting of the limiting member 3 between the end of the first tongue-and-groove 221 and the groove structure 13. In addition, the total circumferential width of the first mortise 221 and the second mortise 222 is smaller than the circumferential width of the groove structure 13, so that the first mortise 221 entering the groove structure 13 is in clearance fit with the groove structure 13 and a gap is left, and the mortise structure 22 is prevented from deforming and extruding the turbine disc 1 to affect the structural stability of the turbine disc 1.
In this embodiment, the first mortise 221 is a longitudinal tree-shaped mortise. The first tenon 121 is a longitudinal tree-shaped tenon matched with the first mortise 221. Above-mentioned first tongue-and-groove 221 adopts and indulges tree-shaped tongue-and-groove, and first tenon 121 adopts and indulges tree-shaped tenon, through indulging tree-shaped tenon and indulging the mutually supporting of tree-shaped tongue-and-groove, has guaranteed the stability of cooperation between first tenon 121 and the first tongue-and-groove 221.
In this embodiment, the cross sections of the second tongue-and-groove 222 and the second tongue 122 are in a mutually-matched convex structure. The cross sections of the second tenon 222 and the second tenon 122 are in a convex structure which is matched with each other, the side end faces of the convex structure are planar, and the head of the second tenon 122 and the inner side face of the second tenon 222 are both planar instead of in an opposite shape, so that the processing time of the second tenon 122 on the second tenon 222 of the blade 2 and the processing time of the second tenon 122 on the turbine disc 1 are shortened, and the manufacturing efficiency of the turbine is further improved.
In this embodiment, the limiting member 3 is one of a locking plate, a diversion plate, a baffle, and an expansion ring. For axial spacing of blades 2
As shown in fig. 3 and 6, in the present embodiment, the locking plate has a rectangular parallelepiped structure; the locking plate comprises a base body and folding sections, wherein the folding sections are arranged at two ends of the base body and can be freely bent and used for being attached to and locked and connected with the turbine disc 1. The locking plate that adopts is the cuboid structure, simple structure, cooperates with tongue-and-groove structure 22 through tenon structure 12 between blade 2 and the turbine dish 1 to further increase the locking connection of tenon structure 12 and tongue-and-groove structure 22 through the locking plate. The locking plate comprises a base body and folding sections positioned at two ends of the base body, and the axial length of the base body is the same as that of the groove structure 13. In the installation process, firstly the turbine disc 1 is fixed, and then the blades 2 and the locking plates are assembled on the turbine disc 1. Wherein locking plate initial state is dull and stereotyped, assembles turbine disc 1 back, and the base member is installed in groove structure 13, and folding section uses the frock to buckle it to hug closely turbine disc 1, thereby it is spacing to carry out the axial to working blade 2, and assembly easy operation, convenience have improved blade 2 and the fixed work efficiency of turbine disc 1 greatly, have reduced blade 2's the fixed degree of difficulty and cost moreover.
In the present embodiment, the platform of the blade body 21 includes 1 blade profile, 2 blade profiles, or 3 blade profiles. The blade 2 comprises a blade main body 21 and a mortise structure 22, wherein 1 blade profile, 2 blade profiles or 3 blade profiles can be arranged on a flange plate of the blade main body 21, 1 blade profile, 2 blade profiles or 3 blade profiles can be arranged on the mortise structure 22 of one unit, and the strength of the blade 2 meets the requirement. Normally, the following blade 2 only comprises 1 blade profile, but due to the tongue and groove structure 22 on the blade 2, the stress condition of the blade 2 is changed, and the possibility that a plurality of blades 2 can be designed on the flange plate is realized.
Preferably, when blades 2 with larger blade profiles are used, a blade profile can also be provided with a plurality of tongue-and-groove structure 22 units, so as to meet the requirements of different turbine engines. A plurality of blades 2 can be welded to form a circular structure, and then the blades of the whole circular structure are arranged on the wheel disc 1.
According to another aspect of the invention, a turbine engine is also provided, which comprises the tenon structure of the turbine engine turbine working blade. Above-mentioned turbine engine has avoided typical joggle structure listrium to appear big cantilever structure including turbine engine turbine rotor blade's joggle structure, and the modern design, and the assembly is simple, convenient, and the practicality is strong, and the stable performance.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A joggle structure of turbine engine turbine working blade, comprising a turbine disk (1) and a plurality of blades (2) uniformly distributed on the periphery of the turbine disk (1),
the turbine disc (1) comprises a turbine disc main body (11), tenon head structures (12) uniformly distributed on the periphery of the turbine disc main body (11),
the tenon structure (12) comprises a first tenon (121) and a second tenon (122) positioned at the middle end part of the first tenon (121), convex teeth are symmetrically distributed on two sides of the first tenon (121), and a groove structure (13) is formed between every two adjacent tenon structures (12);
the blade (2) comprises a blade main body (21), a mortise structure (22) which is arranged at a flange plate of the blade main body (21) and is used for being in mortise fit with the tenon structure (12), the mortise structure (22) comprises a first mortise (221) which is in mortise fit with the first tenon (121), and a second mortise (222) which is in mortise fit with the second tenon (122) and is arranged inside the first mortise (221);
the first mortise (221) comprises a third mortise (2211) matched with the profile of the convex teeth on one side of the first tenon (121), and a fourth mortise (2212) matched with the profile of the convex teeth on the other side of the first tenon (121);
a limiting part (3) used for axial limiting of the blade (2) is arranged between one end, close to the groove structure (13), of the first mortise (221) and the groove structure (13).
2. The dovetail structure of a turbine engine turbine rotor blade according to claim 1,
the circumferential width of the edge plate of the blade main body (21) is equal to the circumferential width of the mortise structure (22).
3. The dovetail structure of a turbine engine turbine rotor blade according to claim 1,
the circumferential width of the first mortise (221) is less than half of the circumferential width of the groove structure (13);
the circumferential width of the second tongue-and-groove (222) is less than half of the circumferential width of the groove structure (13).
4. The dovetail structure of a turbine engine turbine rotor blade according to claim 1,
the first mortise (221) adopts a longitudinal tree-shaped mortise;
the first tenon (121) is a longitudinal tree-shaped tenon matched with the first mortise (221).
5. The dovetail structure of a turbine engine turbine rotor blade according to claim 1,
the cross sections of the second mortise (222) and the second tenon (122) are of convex structures matched with each other.
6. The dovetail structure of a turbine engine turbine rotor blade according to claim 5,
the limiting part (3) adopts one of a locking plate, a flow guide disc, a baffle plate and an expansion ring.
7. The dovetail structure of a turbine engine turbine rotor blade according to claim 6,
the locking plate is of a cuboid structure;
the locking plate comprises a base body and folding sections, wherein the folding sections are arranged at two ends of the base body and can be freely bent and used for being attached to and locked and connected with the turbine disc (1).
8. The dovetail structure of a turbine engine turbine rotor blade according to claim 1,
the edge plate of the blade main body (21) comprises 1 blade profile, 2 blade profiles or 3 blade profiles.
9. A turbine engine comprising the dovetail structure of a turbine engine turbine rotor blade according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110404831.5A CN113153445B (en) | 2021-04-15 | 2021-04-15 | Turbine engine turbine rotor blade's joggle structure and turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110404831.5A CN113153445B (en) | 2021-04-15 | 2021-04-15 | Turbine engine turbine rotor blade's joggle structure and turbine engine |
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| CN113153445A true CN113153445A (en) | 2021-07-23 |
| CN113153445B CN113153445B (en) | 2023-04-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114082391A (en) * | 2021-11-12 | 2022-02-25 | 武汉科技大学 | Self-stabilizing baffling type super-gravity rotating bed |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004218642A (en) * | 2003-01-16 | 2004-08-05 | Snecma Moteurs | System for holding ring-shaped plate to radially directed surface of disc |
| CN101336335A (en) * | 2005-12-01 | 2008-12-31 | 株式会社东芝 | Turbine rotor blade, turbine rotor and steam turbine comprising them |
| CN202578804U (en) * | 2012-04-13 | 2012-12-05 | 中国航空动力机械研究所 | Densification device for turbine rabbet |
| CN110259521A (en) * | 2019-07-31 | 2019-09-20 | 中国科学院工程热物理研究所 | A kind of blade retention for turbomachine |
| CN111472845A (en) * | 2020-05-27 | 2020-07-31 | 上海尚实能源科技有限公司 | Turbine disc and blade locking mechanism for turboprop engine |
-
2021
- 2021-04-15 CN CN202110404831.5A patent/CN113153445B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004218642A (en) * | 2003-01-16 | 2004-08-05 | Snecma Moteurs | System for holding ring-shaped plate to radially directed surface of disc |
| CN101336335A (en) * | 2005-12-01 | 2008-12-31 | 株式会社东芝 | Turbine rotor blade, turbine rotor and steam turbine comprising them |
| CN202578804U (en) * | 2012-04-13 | 2012-12-05 | 中国航空动力机械研究所 | Densification device for turbine rabbet |
| CN110259521A (en) * | 2019-07-31 | 2019-09-20 | 中国科学院工程热物理研究所 | A kind of blade retention for turbomachine |
| CN111472845A (en) * | 2020-05-27 | 2020-07-31 | 上海尚实能源科技有限公司 | Turbine disc and blade locking mechanism for turboprop engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114082391A (en) * | 2021-11-12 | 2022-02-25 | 武汉科技大学 | Self-stabilizing baffling type super-gravity rotating bed |
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| CN113153445B (en) | 2023-04-28 |
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