CN113153445B - Turbine engine turbine rotor blade's joggle structure and turbine engine - Google Patents
Turbine engine turbine rotor blade's joggle structure and turbine engine Download PDFInfo
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- CN113153445B CN113153445B CN202110404831.5A CN202110404831A CN113153445B CN 113153445 B CN113153445 B CN 113153445B CN 202110404831 A CN202110404831 A CN 202110404831A CN 113153445 B CN113153445 B CN 113153445B
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- tenon
- turbine
- groove
- 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
Abstract
The invention discloses a joggle joint structure of a turbine working blade of a turbine engine and the turbine engine, which comprises a turbine disk and the blade, wherein the turbine disk comprises a turbine disk main body and a joggle structure, the joggle structure comprises a first joggle and a second joggle positioned at the middle end part of the first joggle, convex teeth are symmetrically distributed on two sides of the first joggle, and a groove structure is formed between two adjacent joggle structures; the blade comprises a blade body and a tenon groove structure, wherein the tenon groove structure is used for being in tenon joint fit with the tenon structure, the tenon groove structure comprises a first tenon groove matched with the first tenon joint, and a second tenon groove matched with the second tenon joint and positioned in the first tenon groove; the first mortises comprise a third mortises and a fourth mortises; and a limiting piece for axially limiting the blade is arranged between one end of the first mortise, which is close to the groove structure, and the groove structure. The joggling structure of the turbine working blade of the turbine engine, disclosed by the invention, can be used for avoiding the problem of overlarge stress caused by overlarge cantilever of the blade edge plate of a typical joggling structure because the number of single-stage turbine rotor blades is reduced.
Description
Technical Field
The invention relates to the field of gas turbine engines, in particular to a joggle joint structure of turbine rotor blades of a turbine engine. In addition, the invention also relates to a gas turbine engine comprising the joggle structure of the turbine rotor blade of the turbine engine.
Background
At present, turbine rotor blades and turbine discs are connected in a joggle mode, as shown in fig. 1 and 2, blade tenons are wedge-shaped, trapezoid or semicircular teeth which are symmetrically distributed are arranged on two sides of each blade tenon, and mortises with the same molded surface are correspondingly formed on the edges of the turbine discs. 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 tooth is sheared and bent, the working surfaces of all teeth of tenon are extruded, and each section of tenon is stretched. At present, aeroengines are rapidly developed, the power/weight ratio of the aeroengines is continuously increased, and the number of blades at each stage of turbine working blades is reduced. However, as the number of blades per stage decreases, the cantilever length of the turbine rotor blade platform (as shown by L1 and L2 in FIG. 1) increases, the stress at the location where the platform meets the root extension increases, and the blade strength will be difficult to meet design requirements.
Disclosure of Invention
The invention provides a joggle joint structure of turbine working blades of a turbine engine, which aims to solve the technical problem that as the number of rotor blades of each stage is reduced, the cantilever length of a flange plate of the turbine working blades is increased, so that the stress at the joint position of the flange plate and a root extension is increased, and the strength of the blades is difficult to meet the design requirement.
The technical scheme adopted by the invention is as follows:
the tenon structure comprises a first tenon and a second tenon positioned at the middle end part of the first tenon, protruding 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, a tenon groove structure which is matched with the tenon structure in a tenon joint way is arranged at the edge plate of the blade main body, the tenon groove structure comprises a first tenon groove matched with the first tenon joint way, and a second tenon groove which is matched with the second tenon joint way and is positioned in the first tenon groove way; the first tenon groove comprises a third tenon groove matched with the molded surface of the convex tooth at one side of the first tenon, and a fourth tenon groove matched with the molded surface of the convex tooth at the other side of the first tenon; and a limiting piece for axially limiting the blade is arranged between one end of the first mortise, which is close to the groove structure, 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 tongue-and-groove is less than half of the circumferential width of the groove structure; the second tongue-and-groove circumferential width is less than half the groove structure circumferential width.
Further, the first mortises adopt longitudinal tree mortises; the first tenon adopts a longitudinal tree-shaped tenon matched with the first tenon groove.
Further, the cross sections of the second mortises and the second tenons are mutually matched convex structures.
Further, the limiting piece adopts one of a locking plate, a flow guiding disc, a baffle plate and a piston ring.
Further, the locking plate adopts 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 to be attached to and locked and connected with the turbine disc.
Further, the blade body includes 1 profile, 2 profiles or 3 profiles on the platform.
According to another aspect of the present invention, there is also provided a gas turbine engine comprising the above-described dovetail arrangement of turbine engine turbine rotor blades.
The invention has the following beneficial effects:
the joggle joint structure of the turbine working blade of the turbine engine comprises a turbine disc and blades, and the blade disc is provided with a joggle joint structure matched with the joggle joint structure by designing the joggle joint structure at the blade edge plate, so that the locking connection of the blades and the turbine disc is realized, and the problem that the stress is overlarge due to overlarge blade edge plate cantilever of a typical joggle joint structure is avoided because the conventional fixing mode of the turbine disc and the blades, namely, the turbine blades are matched with the joggle joint structure on the turbine disc through the joggle joint. The tenon structure of the blade can be freely arranged on the tenon structure of the turbine disc, and the axial limiting part is used for axially limiting the blade to limit the axial movement of the blade. When the turbine blade works, the centrifugal force of the blade forces the tenons 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 to the turbine disc main body, so that the working surface of the blade is dispersed to bear extrusion stress. The joggle joint structure of the turbine working blade of the turbine engine is novel in design, simple and convenient to assemble, high in practicality and stable in performance.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The invention will be described in further detail with reference to the accompanying drawings.
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 specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic illustration of a dovetail connection of a prior art turbine rotor blade with a turbine disk;
FIG. 2 is a prior art turbine rotor blade force transmission path;
FIG. 3 is a block diagram of a dovetail joint of a turbine rotor blade of a preferred turbine engine of the present invention;
FIG. 4 is a block diagram of a preferred vane of the present invention;
FIG. 5 is a diagram of a preferred turbine disk configuration of the present invention;
FIG. 6 is a dovetail structural assembly view of a preferred turbine engine turbine rotor blade of the present invention; and
FIG. 7 is a blade force transmission path diagram in a dovetail configuration of a turbine engine turbine rotor blade according to a preferred embodiment of the present invention.
Reference numerals illustrate:
1. a turbine disk; 2. a blade; 3. a limiting piece;
11. a turbine disc body; 12. a tenon structure; 121. a first tenon; 122. a second tenon; 13. a groove structure;
21. a blade body; 22. a tongue and groove structure; 221. a first tongue-and-groove; 2211. a third tongue-and-groove; 2212. a fourth tongue-and-groove; 222. and a second tongue-and-groove.
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
FIG. 1 is a schematic illustration of a dovetail connection of a prior art turbine rotor blade with a turbine disk; FIG. 2 is a prior art turbine rotor blade force transmission path; FIG. 3 is a block diagram of a dovetail joint of a turbine rotor blade of a preferred turbine engine of the present invention; FIG. 4 is a block diagram of a preferred vane of the present invention; FIG. 5 is a diagram of a preferred turbine disk configuration of the present invention; FIG. 6 is a dovetail structural assembly view of a preferred turbine engine turbine rotor blade of the present invention; FIG. 7 is a blade force transmission path diagram in a dovetail configuration of a turbine engine turbine rotor blade according to a preferred embodiment of the present invention.
As shown in fig. 3, 4, 5 and 7, the dovetail joint structure of the turbine working blade of the turbine engine in this embodiment includes a turbine disk 1 and a plurality of blades 2 uniformly distributed on the periphery of the turbine disk 1, the turbine disk 1 includes a turbine disk main body 11, tenon structures 12 uniformly distributed on the periphery of the turbine disk main body 11, the tenon structures 12 include a first tenon 121 and a second tenon 122 located at the middle end of the first tenon 121, protruding teeth are symmetrically distributed on two sides of the first tenon 121, and a groove structure 13 is formed between two adjacent tenon structures 12; the blade 2 comprises a blade main body 21, a tenon groove structure 22 for joggling and matching with the tenon structure 12 is arranged at the edge plate of the blade main body 21, the tenon groove structure 22 comprises a first tenon groove 221 joggled and matched with the first tenon 121, and a second tenon groove 222 joggled and matched with the second tenon 122 and positioned inside the first tenon groove 221; the first tenon 221 comprises a third tenon groove 2211 matched with the profile of the convex tooth on one side of the first tenon 121, and a fourth tenon groove 2212 matched with the profile of the convex tooth on the other side of the first tenon 121; a limiting piece 3 for axially limiting the blade 2 is arranged between one end of the first mortise 221 near the groove structure 13 and the groove structure 13. The joggle joint structure of the turbine working blade of the turbine engine comprises a turbine disc 1 and a blade 2, wherein a joggle groove structure 22 is designed at the edge plate of the blade 2, the turbine disc 1 is provided with a joggle head structure 12 matched with the joggle groove structure 22, so that the locking connection of the blade 2 and the turbine disc 1 is realized, and the problem that the stress is overlarge due to overlarge cantilever of the blade 2 of a typical joggle joint structure is solved in the traditional fixing mode of the turbine disc 1 and the blade 2, namely, the turbine rotor blade 2 is matched with the joggle groove structure 22 on the turbine disc 1 through a joggle head, and the joggle groove structure 22 at the edge plate of the blade 2 is avoided. The tongue-and-groove structure 22 of the blade 2 can be freely arranged on the tenon structure 12 of the turbine disc 1, and then the limiting piece 3 is used for axially limiting the blade 2 to limit the axial movement of the blade 2. The joggle joint structure of the turbine working blade of the turbine engine is novel in design, simple and convenient to assemble, high in practicality and stable in performance.
As shown in fig. 2 and 4, in the gas turbine rotor structure adopting the typical joggle structure, when the number of blades 2 is reduced, the cantilever section L1 of the edge plate of the blade 2 is increased, and the stress at the transition circle of the edge plate and the extension root is increased, so that the strength is unacceptable, and therefore, the joggle structure L1 of the turbine working blade of the turbine engine is shortened, so that the stress at the transition circle can be controlled within the allowable range.
The turbine disk 1 can be redesigned into the tenon structure 12 according to the structure of the blade 2, and the existing turbine disk 1 can be adopted, so that a convex body between two tenon grooves of the existing turbine disk is used as the tenon structure 12, tenon teeth of the tenon grooves are used as convex teeth of the tenon structure 12, and the tenon grooves are used as the groove structure 13, thereby not changing the structure of the original turbine disk, only manufacturing a new blade 2 is needed, reducing manufacturing cost and increasing working efficiency.
In this embodiment, the circumferential width of the flange of the blade body 21 is equal to the circumferential width of the tongue-and-groove structure 22. The above-mentioned turbine engine turbine rotor blade's joggle structure is for solving typical joggle structure rim plate and appears big cantilever structure, designs the circumferential width of tongue-and-groove structure 22 the same with the circumferential width of the rim plate of blade main part 21, and the both ends of tongue-and-groove structure 22 and the circumferential direction of rim plate align promptly, reduce the disturbance to surrounding air flow when rotating, further guaranteed engine turbine structure's stability. Moreover, since the tongue-and-groove structure 22 includes the first tongue-and-groove 221 and the second tongue-and-groove 222, the first tongue-and-groove 221 and the second tongue-and-groove 222 are located on the left and right sides of the tenon structure 12, respectively, that is, fall into the preceding groove structure 13 and the following groove structure 13, respectively, the tongue-and-groove structure 22 is aligned with both ends in the circumferential direction of the flange, so that entry into the groove structure 13 is facilitated.
In this embodiment, the circumferential width of the first mortise slot 221 is smaller than half the circumferential width of the groove structure 13. The second tongue-and-groove 222 has a circumferential width that is less than half the circumferential width of the groove structure 13. The groove structures 13 are formed between the two adjacent tenon structures 12, the tenon structures 12 are in joggle fit with the tenon structures 22, and the first tenon groove 221 and the fourth tenon groove 2212 of the tenon structures 22 are respectively located at two ends of the tenon structures 12, that is, fall into the previous groove structure 13 and the next groove structure 13 at two ends of the tenon structures 12 respectively, so that one groove structure 13 accommodates the fourth tenon groove 2212 of the previous tenon structure 22 and the third tenon groove 2211 of the next tenon structure 22. Thus, the circumferential width of the first mortise slot 221 is smaller than half the circumferential width of the groove structure 13. The second tongue-and-groove 222 has a circumferential width that is less than half the circumferential width of the groove structure 13. So that the tongue-and-groove structure 22 can be dropped into the groove structure 13 to achieve the mounting of the stop 3 between the end of the first tongue-and-groove 221 and the groove structure 13. And, 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 clearance is reserved, so that the deformation of the mortise structure 22 to squeeze the turbine disc 1 is prevented from affecting 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 adopts a longitudinal tree-shaped tenon matched with the first tenon groove 221. The first tenon 221 adopts a longitudinal tree-shaped tenon, the first tenon 121 adopts a longitudinal tree-shaped tenon, and the stability of the cooperation between the first tenon 121 and the first tenon 221 is ensured through the mutual cooperation of the longitudinal tree-shaped tenon and the longitudinal tree-shaped tenon.
In this embodiment, the cross sections of the second dovetail groove 222 and the second dovetail 122 are in a convex-shaped structure. The cross sections of the second tenon groove 222 and the second tenon 122 are of mutually matched convex structures, the side end faces of the convex structures are all plane, and the heads of the second tenon groove 122 and the inner side faces of the second tenon groove 222 are all plane, but not of different shapes, so that the processing time of the second tenon groove 222 of the blade 2 and the second tenon groove 122 on the turbine disc 1 is 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 guide plate, a baffle plate and a piston ring. For axial limiting of the blades 2
As shown in fig. 3 and 6, in this embodiment, the locking plate adopts a rectangular parallelepiped 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 for being attached to and locked and connected with the turbine disc 1. The locking plate is of a cuboid structure, the structure is simple, the blade 2 and the turbine disc 1 are matched with the tenon structure 22 through the tenon structure 12, and the locking connection of the tenon structure 12 and the tenon structure 22 is further increased through the locking plate. The locking piece comprises a base body and folding sections 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. During the installation process, the turbine disk 1 is fixed first, and then the blades 2 and the locking pieces are assembled to the turbine disk 1. Wherein the locking plate initial state is the flat board, 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 carry out axial spacing to rotor blade 2, assembly operation is simple, convenient, has improved blade 2 and the fixed work efficiency of turbine disc 1 greatly, has reduced the fixed degree of difficulty and the cost of blade 2 moreover.
In this embodiment, the blade body 21 includes 1 profile, 2 profiles, or 3 profiles on the platform. The blade 2 includes a blade main body 21 and a tongue-and-groove structure 22, wherein the edge plate of the blade main body 21 can be provided with 1 blade profile, 2 blade profiles or 3 blade profiles, the tongue-and-groove structure 22 of one unit can be provided with not only 1 blade profile but also 2 blade profiles or 3 blade profiles, and the strength of the blade 2 meets the requirement. The next blade 2 typically comprises only 1 profile, but due to the tongue and groove structure 22 on the blade 2, the stress situation of the blade 2 is changed, and the possibility of designing a plurality of blades 2 on the platform is realized.
Preferably, when a larger blade 2 is used, a single blade profile may also use multiple tongue and groove arrangements 22 units to accommodate different turbine engine requirements. Or a plurality of blades 2 can be welded to form a circular structure, and then the blades with the whole circular structure are arranged on the wheel disc 1.
According to another aspect of the present invention, there is also provided a turbine engine including the above-described dovetail structure of turbine rotor blades of the turbine engine. Above-mentioned turbine engine includes turbine engine turbine rotor blade's joggle structure, has avoided typical joggle structure edge plate to appear big cantilever structure, and turbine engine turbine rotor blade's joggle structure, novel in design, the assembly is simple, convenient, and the practicality is strong, and stable performance.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The joggle joint structure of turbine working blades of a turbine engine comprises a turbine disc (1) and a plurality of blades (2) uniformly distributed on the periphery of the turbine disc (1), and is characterized in that,
the turbine disc (1) comprises a turbine disc main body (11), tenon 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), protruding teeth are symmetrically distributed on two sides of the first tenon (121), and a groove structure (13) is formed between two adjacent tenon structures (12);
the blade (2) comprises a blade main body (21), a tenon groove structure (22) for joggling and matching with the tenon structure (12) is arranged at the edge plate of the blade main body (21), the tenon groove structure (22) comprises a first tenon groove (221) joggled and matched with the first tenon (121), and a second tenon groove (222) joggled and matched with the second tenon (122) and positioned in the first tenon groove (221);
the first tenon groove (221) comprises a third tenon groove (2211) matched with the profile of the convex tooth at one side of the first tenon (121), and a fourth tenon groove (2212) matched with the profile of the convex tooth at the other side of the first tenon (121);
the centrifugal force and bending moment on the blade are transmitted from two ends of the tenon groove structure to the tenon structure of the turbine disc at the middle position respectively, and the force and moment born by the tenon structure are transmitted to the turbine disc main body;
the first mortise slot (221) is in clearance fit with the groove structure (13) and is provided with a clearance;
and a limiting piece (3) for axially limiting 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. A dovetail arrangement for a turbine engine turbine rotor blade according to claim 1,
the circumferential width of the flange plate of the blade main body (21) is equal to the circumferential width of the mortise structure (22).
3. A dovetail arrangement for a turbine engine turbine rotor blade according to claim 1,
the circumferential width of the first tongue-and-groove (221) is smaller than half of the circumferential width of the groove structure (13);
the second tongue-and-groove (222) has a circumferential width which is smaller than half the circumferential width of the groove structure (13).
4. A dovetail arrangement for a turbine engine turbine rotor blade according to claim 1,
the first mortises (221) adopt longitudinal tree mortises;
the first tenon (121) adopts a longitudinal tree tenon matched with the first tenon groove (221).
5. A dovetail arrangement for a turbine engine turbine rotor blade according to claim 1,
the cross sections of the second mortises (222) and the second tenons (122) are mutually matched convex structures.
6. A dovetail construction for a turbine engine turbine rotor blade according to claim 5,
the limiting piece (3) adopts one of a locking plate, a flow guiding disc, a baffle plate and a piston ring.
7. A dovetail construction for a turbine engine turbine rotor blade according to claim 6,
the locking plate adopts 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 to be attached to the turbine disc (1) and locked and connected.
8. A dovetail arrangement for 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 arrangement of turbine engine turbine rotor blades of any one of claims 1 to 8.
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| 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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| 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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| CN113153445B true CN113153445B (en) | 2023-04-28 |
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| FR2850130B1 (en) * | 2003-01-16 | 2006-01-20 | Snecma Moteurs | DEVICE FOR RETAINING AN ANNULAR FLASK AGAINST A RADIAL FACE OF A DISK |
| JP4673732B2 (en) * | 2005-12-01 | 2011-04-20 | 株式会社東芝 | Turbine blades and steam turbines |
| 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 |
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