CN211202062U - Connection structure of gas turbine blade and turbine disc - Google Patents
Connection structure of gas turbine blade and turbine disc Download PDFInfo
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- CN211202062U CN211202062U CN201921439967.4U CN201921439967U CN211202062U CN 211202062 U CN211202062 U CN 211202062U CN 201921439967 U CN201921439967 U CN 201921439967U CN 211202062 U CN211202062 U CN 211202062U
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Abstract
The utility model relates to a connection structure of gas turbine blade and turbine dish, including the turbine dish, with this turbine dish complex a plurality of blades, characterized by: the blade axial limiting device further comprises a clamping ring and a buckle used for limiting the blade in the axial direction. The probability of damage to the turbine disk caused by stress concentration under the conditions of large load and high thermal stress can be reduced to the maximum extent; the reliability is high, and part quantity reduces, and assembly and disassembly convenient and fast can improve assembly efficiency, and need not use special frock clamp during the installation, spare part can used repeatedly.
Description
Technical Field
The utility model relates to a gas turbine engine, concretely relates to connection structure of gas turbine blade and turbine dish.
Background
At present, locking plates, baffles, locking plates and other parts are generally used for axially fixing axial flow turbine blades of gas turbine aeroengines or gas turbines. Wherein the earlier turbine blades without cooling can be in a locking piece mode with simple structure. And along with cooling channel's introduction, for preventing cooling air's leakage, and adopt the fixed mode of baffle, the axial locking mode assembly of baffle is comparatively convenient, but need punch and use the round bolt fastening on the turbine dish, and at turbine dish during operation, mechanical load and thermal load are very big, and hole and bolted connection on the turbine dish can lead to the rim plate to produce stress concentration to increase the risk that microcrack produced and turbine dish damage. In order to reduce the influence of the holes of the turbine disk, part of the engines adopt a locking plate (a bolt-free baffle) mode, the influence of the locking plate mode on the turbine disk is small, but the number of parts is large, the assembly process is complex, and the locking plate is required to be replaced during maintenance and cannot be reused. There is therefore a need for an improved connection of existing gas turbine blades to a turbine disk.
Disclosure of Invention
The utility model aims at providing a connection structure of a gas turbine blade and a turbine disc, which can reduce the probability of damage of the turbine disc caused by stress concentration under the conditions of large load and high thermal stress to the utmost extent; the reliability is high, and part quantity reduces, and assembly and disassembly convenient and fast can improve assembly efficiency, and need not use special frock clamp during the installation, spare part can used repeatedly.
A connection structure of gas turbine blade and turbine dish, including the turbine dish, with this turbine dish complex a plurality of blades, characterized by: the blade axial limiting device further comprises a clamping ring and a buckle used for limiting the blade in the axial direction.
Furthermore, a plurality of tenon teeth are uniformly distributed in the circumferential direction of the turbine disc, a tenon groove is formed between every two adjacent tenon teeth, a first axial limiting part used for limiting the blade is arranged at the right end part of each tenon tooth, a second axial limiting part used for limiting the blade is arranged at the left end part of each tenon tooth, the second axial limiting part extends leftwards and towards the axial lead direction of the turbine disc, a groove with an opening facing the axial lead direction of the turbine disc is formed by each second axial limiting part and the left end surface of the turbine disc, and a circle of annular groove is formed by the plurality of grooves; the blade comprises a blade body and a tenon connected with the blade body; the blade is matched with a mortise on the turbine disc through a tenon of the blade, and the right end face of the blade tenon is tightly attached to the first axial limiting part; the rand cooperates and locks through the buckle with the annular on the turbine disc, the left end face and the rand of blade tenon are hugged closely.
Furthermore, the left end face of the blade tenon extends leftwards and far away from the blade body to form a second auxiliary axial limiting part, and the shape of the second auxiliary axial limiting part is matched with a gap formed between two adjacent second axial limiting parts; the spacing portion of a plurality of second axial of turbine dish and a plurality of the spacing portion of second auxiliary axial of blade forms the round annular with the left end face of turbine dish, rand and this annular cooperation.
Further, the clamping ring is an open annular structure; the buckle is clamped into the opening part of the clamping ring.
Further, the buckle is provided with a clamping part with a U-shaped section, and the clamping part comprises a left side part, a right side part and a bottom part for connecting the left side part and the right side part; the clamping portion is clamped on the second axial limiting portion of the turbine disc and the second auxiliary axial limiting portion of the blade, one end face of the right side portion of the clamping portion is tightly attached to one end face of the clamping ring, and the other end face of the right side portion of the clamping portion is tightly attached to the other end of the clamping ring.
Furthermore, the left side part of the buckle clamping part and the second axial limiting part of the turbine disc tenon tooth are correspondingly provided with pin holes, and pins used for buckle positioning are matched in the pin holes.
Further, the blade also comprises a flange plate positioned at the connecting part of the blade body and the tenon; the first axial limiting part protrudes out of the tooth crest face of the turbine disc tenon tooth; the right end of the flange plate is tightly attached to the first axial limiting part.
Further, the buckle still has the spacing portion that links to each other with the bottom of joint portion, and the both ends of this spacing portion all bulge in the both ends face of joint portion, and this spacing portion hugs closely with the interior anchor ring of rand.
Further, the two ends of the clamping ring close to the opening of the clamping ring are provided with mounting holes.
The utility model discloses profitable technological effect:
after the blades are matched with the turbine disc, the axial limiting of the blades can be realized only through the clamping rings and the buckles, so that compared with the existing structure, the number of parts is reduced, the assembly and disassembly are convenient and quick, the assembly efficiency is improved, a special tool clamp is not needed during installation, and the parts can be reused; because no mounting hole is machined on the turbine disc or other processes which are not beneficial to the integrity of the turbine disc are added, the probability of damage of the turbine disc caused by stress concentration under the conditions of large load and high thermal stress is reduced to the maximum extent; because the buckle has joint portion to be connected through the spacing portion of pin with the second axial of turbine disc, played the positioning action to buckle and rand, prevented that buckle and rand are rotatory, because the buckle has spacing portion, prevented that the rand from following perpendicular to turbine disc axle center direction drunkenness, improved the reliability of whole structure.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is a schematic view of the attachment of the collar to the blade and turbine disk;
FIG. 4 is a cross-sectional view of FIG. 1 (blade not shown);
FIG. 5 is a schematic structural view of a turbine disk;
FIG. 6 is an enlarged partial view of FIG. 5;
FIG. 7 is a schematic view of a blade configuration;
FIG. 8 is a schematic view of a single blade to turbine disk connection;
FIG. 9 is a schematic view of a plurality of blade to turbine disk connection;
FIG. 10 is a schematic view of the collar;
FIG. 11 is an enlarged partial view of FIG. 10;
fig. 12 is a schematic structural view of the buckle.
In the figure: 1-a turbine disk; 11-tenon tooth, 12-mortise and 13-groove; 111-a first axial limiting part, 112-a second axial limiting part;
2-a blade; 21-blade body, 22-tenon, 23-flange plate; 221-a second auxiliary axial limiting part;
3-a collar; 31-mounting holes;
4-buckling; 41-clamping part, 42-limiting part;
5-a pin; 51-pin hole.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and examples.
Referring to fig. 1 to 12, a connection structure of a gas turbine blade and a turbine disk includes a turbine disk 1, and a plurality of blades 2 engaged with the turbine disk 1, and is characterized in that: the blade limiting device further comprises a clamping ring 3 and a buckle 4 which are used for limiting the axial direction of the blade 2. Realize the axial of blade 2 spacing through rand 3 and buckle 4, for current structure, part quantity reduces for convenient assembling is swift, assembly efficiency is high.
A plurality of tenon teeth 11 are uniformly distributed in the circumferential direction of the turbine disc 1, a tenon groove 12 is formed between every two adjacent tenon teeth 11, a first axial limiting part 111 used for limiting the blade 2 is arranged at the right end part of each tenon tooth 11, a second axial limiting part 112 used for limiting the blade 2 is arranged at the left end part of each tenon tooth 11, the second axial limiting part 112 extends leftwards and towards the axial lead direction of the turbine disc 1, a groove 13 with an opening towards the axial lead direction of the turbine disc 1 is formed on each second axial limiting part 112 and the left end surface of the turbine disc 1, and a circle of annular groove 14 is formed by the plurality of grooves 13; the blade 2 comprises a blade body 21 and a tenon 22 connected with the blade body 21; the blade 2 is matched with the mortise 12 on the turbine disc 1 through the tenon 22, and the right end face of the tenon 22 of the blade 2 is tightly attached to the first axial limiting part 111; the clamping ring 3 is matched with the annular groove 14 on the turbine disc 1 and locked through the buckle 4, and the left end face of the tenon 22 of the blade 2 is tightly attached to the clamping ring 3. The right end part of the blade 2 is limited by the first axial limiting part 111 of the turbine disc 1, and the left end part of the blade is limited by the clamping ring 3, and because no mounting hole is processed on the turbine disc 1 or other processes which are not beneficial to ensuring the integrity of the turbine disc 1 are added; the possibility of damage to the turbine disk due to stress concentrations under high load and high thermal stress conditions can be minimized. The maximum radius of the ring groove 14 is larger than the distance from the bottom surface of the mortise 12 to the axial lead of the turbine disc 1, and the clamping ring 3 can limit the left end part of the tenon 22 of the blade 2 after being clamped into the ring groove 14.
The left end surface of the tenon 22 of the blade 2 extends leftwards and far away from the blade body 21 to form a second auxiliary axial limiting part 221, and the shape of the second auxiliary axial limiting part 221 is matched with a gap formed between two adjacent second axial limiting parts 112; the plurality of second axial limiting parts 112 of the turbine disc 1 and the plurality of second auxiliary axial limiting parts 221 of the blades 2 form a ring of ring grooves 14 with the left end face of the turbine disc 1, and the clamping ring 3 is matched with the ring grooves 14. The blade 2 is matched with the mortise 12 on the turbine disc 1 through the tenon 22, and the second auxiliary axial limiting part 221 is also matched with a clearance formed between two adjacent second axial limiting parts 112 on the turbine disc 1; not only can improve intensity and rigidity after blade 2 and the cooperation of turbine disc 1, can also increase the lifting surface area of rand, reduce rand 3's deformation risk.
The clamping ring 3 is an open annular structure; the buckle 4 is clamped into the opening part of the clamping ring 3. The buckle 4 is clamped into the opening part of the clamping ring 3, and the main purpose of the buckle is to enable the clamping ring 3 to be tightly attached to the root part of the ring groove 14 and prevent the clamping ring 3 from loosening.
The buckle 4 is provided with a clamping part 41 with a U-shaped section, and the clamping part 41 comprises a left side part, a right side part and a bottom part for connecting the left side part and the right side part; the clamping portion 41 is clamped on the second axial limiting portion 112 of the turbine disc 1 and the second auxiliary axial limiting portion 221 of the blade 2, one end face of the right side portion of the clamping portion 41 is tightly attached to one end face of the clamping ring 3, and the other end face of the right side portion of the clamping portion 41 is tightly attached to the other end of the clamping ring 3.
The left side part of the clamping part 41 of the buckle 4 and the second axial limiting part 112 of the tenon tooth 11 of the turbine disc 1 are correspondingly provided with pin holes 51, and pins 5 used for positioning the buckle 4 are matched in the pin holes 51. The pin 5 can play a positioning role for the buckle 4 and the clamping ring 3, and prevent the buckle 4 and the clamping ring 3 from rotating.
The blade 2 further comprises a flange plate 23 positioned at the connecting part of the blade body 21 and the tenon 22; the first axial limiting part 111 is a flange protruding from the top surface of the tenon 11 of the turbine disc 1; the right end of the flange plate 23 is closely attached to the first axial limiting portion 111.
The buckle 4 further has a limiting portion 42 connected to the bottom of the clamping portion 41, two end portions of the limiting portion 42 protrude out of two end surfaces of the clamping portion 41, and the limiting portion 42 is tightly attached to the inner annular surface of the clamping ring 3. The stopper 42 prevents the retainer ring 3 from moving in a direction perpendicular to the axis of the turbine disk.
The two ends of the collar 3 near the opening thereof are provided with mounting holes 31. The mounting holes 31 are provided to facilitate mounting of the collar 3.
The utility model is suitable for a gas turbine aeroengine or gas turbine's axial-flow turbine blade's axial fixity. After the blades are matched with the turbine disc, a ring of ring grooves are formed, clamping rings are matched in the ring grooves and are locked through buckles and pins, and therefore the axial fixation of the blades is achieved. Only a pinhole is respectively seted up on the spacing portion of two adjacent tenon teeth second axial on the turbine disc, and is minimum to turbine disc intensity influence, greatly reduced the probability of turbine disc damage, improved the reliability of whole structure. Meanwhile, a special tool clamp is not needed during installation, so that the installation and the disassembly are convenient; and when the maintenance is carried out, the parts can be repeatedly used.
Claims (8)
1. A connection structure of gas turbine blade and turbine disk, includes turbine disk (1), with this turbine disk (1) complex a plurality of blades (2), characterized by: the blade limiting device also comprises a clamping ring (3) and a buckle (4) which are used for limiting the axial direction of the blade (2);
a plurality of tenon teeth (11) are uniformly distributed in the circumferential direction of the turbine disc (1), a tenon groove (12) is formed between every two adjacent tenon teeth (11), a first axial limiting part (111) used for limiting the blade (2) is arranged at the right end part of each tenon tooth (11), a second axial limiting part (112) used for limiting the blade (2) is arranged at the left end part of each tenon tooth (11), the second axial limiting part (112) extends leftwards and towards the axial lead direction of the turbine disc (1), a groove (13) with an opening towards the axial lead direction of the turbine disc (1) is formed on each second axial limiting part (112) and the left end surface of the turbine disc (1), and a circle of ring grooves (14) are formed by the grooves (13);
the blade (2) comprises a blade body (21) and a tenon (22) connected with the blade body (21); the blade (2) is matched with a mortise (12) on the turbine disc (1) through a tenon (22), and the right end face of the tenon (22) of the blade (2) is tightly attached to the first axial limiting part (111);
ring clip (3) and annular (14) cooperation on turbine disc (1) and through buckle (4) locking, the left end face of blade (2) tenon (22) is hugged closely with ring clip (3).
2. The gas turbine blade to turbine disk connection structure of claim 1, wherein: the left end face of the tenon (22) of the blade (2) extends leftwards and in the direction far away from the blade body (21) to form a second auxiliary axial limiting part (221), and the shape of the second auxiliary axial limiting part (221) is matched with a gap formed between every two adjacent second axial limiting parts (112); a plurality of second axial spacing portions (112) of turbine disc (1) and a plurality of the second auxiliary axial spacing portion (221) of blade (2) forms a round annular groove (14) with the left end face of turbine disc (1), rand (3) and this annular groove (14) cooperation.
3. The gas turbine blade-to-turbine disk connection structure as claimed in claim 2, wherein: the clamping ring (3) is an open annular structure; the buckle (4) is clamped into the opening part of the clamping ring (3).
4. The gas turbine blade to turbine disk connection structure of claim 3, wherein: the buckle (4) is provided with a clamping part (41) with a U-shaped section, and the clamping part (41) comprises a left side part, a right side part and a bottom part for connecting the left side part and the right side part; the clamping portion (41) is clamped on a second axial limiting portion (112) of the turbine disc (1) and a second auxiliary axial limiting portion (221) of the blade (2), one end face of the right side portion of the clamping portion (41) is tightly attached to one end face of the clamping ring (3), and the other end face of the right side portion of the clamping portion is tightly attached to the other end of the clamping ring (3).
5. The gas turbine blade-to-turbine disk connection structure as claimed in claim 4, wherein: the left side part of the clamping part (41) of the buckle (4) and the second axial limiting part (112) of the tenon tooth (11) of the turbine disc (1) are correspondingly provided with pin holes (51), and the pin holes (51) are internally matched with pins (5) used for positioning the buckle (4).
6. The structure for connecting a gas turbine blade to a turbine disk according to any one of claims 1 to 5, wherein: the blade (2) further comprises a flange plate (23) positioned at the connecting part of the blade body (21) and the tenon (22); the first axial limiting part (111) protrudes out of the tooth crest of the tenon tooth (11) of the turbine disc (1); the right end of the flange plate (23) is tightly attached to the first axial limiting part (111).
7. The gas turbine blade-to-turbine disk connection structure as claimed in claim 4, wherein: the buckle (4) is also provided with a limiting part (42) connected with the bottom of the clamping part (41), two end parts of the limiting part (42) protrude out of two end faces of the clamping part (41), and the limiting part (42) is tightly attached to the inner ring face of the clamping ring (3).
8. The gas turbine blade to turbine disk connection structure of claim 3, wherein: and two end parts of the clamping ring (3) close to the opening of the clamping ring are respectively provided with a mounting hole (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921439967.4U CN211202062U (en) | 2019-09-02 | 2019-09-02 | Connection structure of gas turbine blade and turbine disc |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921439967.4U CN211202062U (en) | 2019-09-02 | 2019-09-02 | Connection structure of gas turbine blade and turbine disc |
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| Publication Number | Publication Date |
|---|---|
| CN211202062U true CN211202062U (en) | 2020-08-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921439967.4U Active CN211202062U (en) | 2019-09-02 | 2019-09-02 | Connection structure of gas turbine blade and turbine disc |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439628A (en) * | 2019-09-02 | 2019-11-12 | 重庆天骄航空动力有限公司 | A kind of connection structure of gas turbine blades and the turbine disk |
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2019
- 2019-09-02 CN CN201921439967.4U patent/CN211202062U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439628A (en) * | 2019-09-02 | 2019-11-12 | 重庆天骄航空动力有限公司 | A kind of connection structure of gas turbine blades and the turbine disk |
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