CN212177224U - Upper end wall level connection structure suitable for heavy gas turbine - Google Patents
Upper end wall level connection structure suitable for heavy gas turbine Download PDFInfo
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- CN212177224U CN212177224U CN202021116818.7U CN202021116818U CN212177224U CN 212177224 U CN212177224 U CN 212177224U CN 202021116818 U CN202021116818 U CN 202021116818U CN 212177224 U CN212177224 U CN 212177224U
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Abstract
The utility model relates to an upper end wall level connection structure suitable for heavy gas turbine belongs to gas turbine technical field. For solving the not good problem of current heavy gas turbine's upper end wall leakproofness, utility model provides an upper end wall and connection structure suitable for heavy gas turbine, include: the turbine cylinder body comprises a first-stage stationary blade, a first-stage moving blade, a second-stage stationary blade, a second-stage moving blade, a third-stage stationary blade, a third-stage moving blade, a first holding ring, a second holding ring, a third holding ring, a fourth holding ring and a moving blade retaining ring. Be equipped with the movable vane retaining ring on the first order movable blade, can completely cut off the cylinder body temperature, prevent that hot gas from getting into inside the cylinder body, reach the effect of sealed cylinder body, improve turbine cylinder life-span and turbine efficiency.
Description
Technical Field
The utility model belongs to the technical field of gas turbine, especially, relate to an upper end wall level connection structure suitable for heavy gas turbine.
Background
Currently, for a gas turbine unit, an effective method for improving the cycle efficiency of the gas turbine unit is to improve the aerodynamic efficiency and the cooling efficiency of the gas turbine, and the improvement of the turbine efficiency requires not only advanced blade design but also a reasonable connection structure. For a gas turbine, at present, there is almost no upper end wall radial flow channel structure specially designed for a heavy-duty gas turbine, so that at present, the connection structure of the upper end wall of the existing heavy-duty gas turbine has poor sealing performance, resulting in poor sealing performance of a main flow gas channel of the heavy-duty gas turbine.
SUMMERY OF THE UTILITY MODEL
For solving the above-mentioned not good problem of current heavy gas turbine's the upper end wall leakproofness, the utility model provides an upper end wall and connection structure suitable for heavy gas turbine.
The technical scheme of the utility model:
an upper endwall stage connection structure adapted for use in a heavy duty gas turbine engine, comprising: the turbine blade support structure comprises a first-stage stationary blade, a first-stage moving blade, a second-stage stationary blade, a second-stage moving blade, a third-stage stationary blade, a third-stage moving blade, a first holding ring, a second holding ring, a third holding ring, a fourth holding ring and a moving blade guard ring; the first stage stationary blades are installed with a first holding ring, a movable blade guard ring is arranged between the first stage movable blades and a second holding ring, the movable blade guard ring is installed on the second holding ring, two ends of the second stage stationary blades are installed on the second holding ring and a third holding ring respectively, a first sealing element is arranged between the second stage movable blades and the third holding ring, the first sealing element is installed on the third holding ring, two ends of the third stage stationary blades are installed on the third holding ring and a fourth holding ring respectively, a second sealing element is arranged between the third stage movable blades and the fourth holding ring, and the second sealing element is installed on the fourth holding ring.
Furthermore, the first holding ring is provided with a first connecting part, and the first stage stationary blade is installed with the first connecting part.
Furthermore, two ends of the second stage stationary blade are respectively provided with a second connecting part, and the second stage stationary blade is installed with the second holding ring and the third holding ring through the second connecting parts.
Furthermore, both ends of the third stage stationary blades are respectively provided with a third connecting part, and the third stage stationary blades are installed with a third holding ring and a fourth holding ring through the third connecting parts.
Furthermore, a first-stage stationary blade upper end wall is arranged on the first-stage stationary blade, a lower end face of the movable blade retaining ring is a movable blade retaining ring end wall, a second-stage stationary blade upper end wall is arranged on the second-stage stationary blade, a third retaining ring end wall is arranged on a lower end face of the third retaining ring, a third-stage stationary blade upper end wall is arranged on the third-stage stationary blade, a lower section of the fourth retaining ring is a fourth retaining ring end wall, and the first-stage stationary blade upper end wall, the movable blade retaining ring end wall, the second-stage stationary blade upper end wall, the third retaining ring end wall, the third-stage stationary blade upper end wall and the fourth retaining ring end wall form a heavy gas turbine meridian flow passage upper end wall structure.
The utility model has the advantages that:
the utility model discloses by the upper end wall, hold the ring, movable vane retaining ring and sealing member constitute jointly, first order stationary blade is installed on holding the ring, connect through holding the ring between each stationary blade, the movable vane cooperates with corresponding ring of holding respectively, first stationary blade upper end wall, second stationary blade upper end wall, third stationary blade upper end wall, movable vane retaining ring end wall, the third is held ring end wall and fourth and is held ring end wall and constitute heavy gas turbine meridian runner upper end wall structure, but upper end wall structure separation mainstream gas is to turbine cylinder body heat transfer and upper end wall simple structure. Be provided with the movable vane retaining ring on the first order movable vane, can completely cut off the cylinder body temperature effectively, prevent that hot gas from getting into inside the cylinder body, reach the effect of sealed cylinder body, and then effectively improve turbine cylinder's life-span and turbine efficiency. And the movable vane retaining ring can be detached and replaced, and the installation is convenient. The utility model discloses a second level moving blade and third are held and are installed first sealing member between the ring, and this first sealing member has reduced moving blade top clearance, can guarantee under operating condition that second level moving blade and third hold the very little clearance between the ring, guarantee pneumatic efficiency. Third stage moving blade and fourth hold and install the second sealing member between the ring, this second sealing member has guaranteed the safe high-efficient operation of gas turbine, and then has improved the life-span of turbine cylinder.
Drawings
Fig. 1 is a schematic structural view of an upper-end wall-stage connection structure according to an embodiment of the present invention;
in the figure, 1, a first stage stationary blade; 2. a first stage moving blade; 3. a second stage stationary blade; 4. a second stage moving blade; 5. a third stage stationary blade; 6. a third stage moving blade; 7. a first holding ring; 8. a second holding ring; 9. a third holding ring; 10. a fourth holding ring; 11. a movable blade retaining ring; 12. a first seal member; 13. a second seal member; 14. a first connection portion; 15. a second connecting portion; 16. a third connecting portion; 17. an upper end wall of the first stage stationary blade; 18. a bucket shroud end wall; 19. an upper endwall of the second stage stationary blade; 20. a third retaining ring end wall; 21. an upper endwall of the third stage stationary blade; 22. a fourth retaining ring end wall.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described below with reference to specific embodiments shown in the accompanying drawings. It should be understood that the description is intended to be illustrative only and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The first embodiment is as follows: the present embodiment is explained with reference to fig. 1, and the present embodiment proposes the following technical solutions:
a first stage stationary blade 1, a first stage moving blade 2, a second stage stationary blade 3, a second stage moving blade 4, a third stage stationary blade 5, a third stage moving blade 6, a first retaining ring 7, a second retaining ring 8, a third retaining ring 9, a fourth retaining ring 10 and a moving blade retaining ring 11; wherein the first stage stationary blades 1 are installed with a first retaining ring 7, the first stage moving blades 2 are arranged between the first stage stationary blades 1 and the second stage stationary blades 3, the first stage moving blades 2 are fitted with a second retaining ring 8, both ends of the second stage stationary blades 3 are respectively installed on the second retaining ring 8 and the third retaining ring 9, the second stage moving blades 4 are arranged between the second stage stationary blades 3 and the third stage stationary blades 5, the second stage moving blades 4 are fitted with the third retaining ring 9, both ends of the third stage stationary blades 5 are respectively installed on the third retaining ring 9 and the fourth retaining ring 10, the third stage moving blades 6 are arranged outside the third stage stationary blades 5, and the third stage moving blades 6 are fitted with the fourth retaining ring 10;
a movable blade retaining ring 11 is arranged between the first-stage movable blade 2 and the second retaining ring 8, and the movable blade retaining ring 11 is installed on the second retaining ring 8;
a first sealing element 12 is arranged between the second-stage moving blades 4 and the third retaining ring 9, and the first sealing element 12 is installed on the third retaining ring 9;
a second seal 13 is arranged between the third stage moving blade 6 and the fourth retaining ring 10, and the second seal 13 is installed on the fourth retaining ring 10;
the first-stage stationary blade 1 is provided with a first-stage stationary blade upper end wall 17, the lower end face of the movable blade guard ring 11 is a movable blade guard ring end wall 18, the second-stage stationary blade 3 is provided with a second-stage stationary blade upper end wall 19, the lower end face of the third retaining ring 9 is a third retaining ring end wall 20, the third-stage stationary blade 5 is provided with a third-stage stationary blade upper end wall 21, and the lower section of the fourth retaining ring 10 is a fourth retaining ring end wall 22, wherein the first-stage stationary blade upper end wall 17, the movable blade guard ring end wall 18, the second-stage stationary blade upper end wall 19, the third retaining ring end wall 20, the third-stage stationary blade upper end wall 21 and the fourth retaining ring end wall 22 form a heavy-duty gas turbine radial flow passage upper end wall structure which can block main flow gas from transferring heat to a turbine cylinder and has a simple upper end wall structure. The movable vane retaining ring 11 is arranged on the first-stage movable vane 2, so that the temperature of the cylinder body can be effectively isolated, hot gas is prevented from entering the cylinder body, the effect of sealing the cylinder body is achieved, and the service life of the turbine cylinder and the turbine efficiency are effectively improved. And the movable vane retaining ring can be detached and replaced, and the installation is convenient. The utility model discloses a second level moving blade 4 and third are held and are installed first sealing member 12 between ring 9, and this first sealing member 12 has reduced moving blade top clearance, can guarantee under operating condition that second level moving blade 4 and third hold the very little interter-radial clearance between ring 9, guarantee pneumatic efficiency. Third stage moving blade 6 and fourth are held and are installed second sealing member 13 between the ring 10, and this second sealing member 13 has guaranteed the safe high-efficient operation of gas turbine, and then has improved the life-span of turbine cylinder.
The second embodiment is as follows: the present embodiment is explained with reference to fig. 1, and the present embodiment proposes the following technical solutions:
a first stage stationary blade 1, a first stage moving blade 2, a second stage stationary blade 3, a second stage moving blade 4, a third stage stationary blade 5, a third stage moving blade 6, a first retaining ring 7, a second retaining ring 8, a third retaining ring 9, a fourth retaining ring 10 and a moving blade retaining ring 11; wherein the first stage stationary blades 1 are installed with a first retaining ring 7, the first stage moving blades 2 are arranged between the first stage stationary blades 1 and the second stage stationary blades 3, the first stage moving blades 2 are fitted with a second retaining ring 8, both ends of the second stage stationary blades 3 are respectively installed on the second retaining ring 8 and the third retaining ring 9, the second stage moving blades 4 are arranged between the second stage stationary blades 3 and the third stage stationary blades 5, the second stage moving blades 4 are fitted with the third retaining ring 9, both ends of the third stage stationary blades 5 are respectively installed on the third retaining ring 9 and the fourth retaining ring 10, the third stage moving blades 6 are arranged outside the third stage stationary blades 5, and the third stage moving blades 6 are fitted with the fourth retaining ring 10;
the first-stage stationary blade 1 is provided with a first-stage stationary blade upper end wall 17, the lower end face of the second retaining ring 8 is a moving second retaining ring end wall, the second-stage stationary blade 3 is provided with a second-stage stationary blade upper end wall 19, the lower end face of the third retaining ring 9 is a third retaining ring end wall 20, the third-stage stationary blade 5 is provided with a third-stage stationary blade upper end wall 21, the lower section of the fourth retaining ring 10 is a fourth retaining ring end wall 22, and the first-stage stationary blade upper end wall 17, the second retaining ring end wall, the second-stage stationary blade upper end wall 19, the third retaining ring end wall 20, the third-stage stationary blade upper end wall 21 and the fourth retaining ring end wall 22 form a heavy-duty gas turbine radial flow passage upper end wall structure.
The third concrete implementation mode: the present embodiment is explained with reference to fig. 1, and the present embodiment proposes the following technical solutions:
a first stage stationary blade 1, a first stage moving blade 2, a second stage stationary blade 3, a second stage moving blade 4, a third stage stationary blade 5, a third stage moving blade 6, a first retaining ring 7, a second retaining ring 8, a third retaining ring 9, a fourth retaining ring 10 and a moving blade retaining ring 11; wherein the first stage stationary blades 1 are installed with a first retaining ring 7, the first stage moving blades 2 are arranged between the first stage stationary blades 1 and the second stage stationary blades 3, the first stage moving blades 2 are fitted with a second retaining ring 8, both ends of the second stage stationary blades 3 are respectively installed on the second retaining ring 8 and the third retaining ring 9, the second stage moving blades 4 are arranged between the second stage stationary blades 3 and the third stage stationary blades 5, the second stage moving blades 4 are fitted with the third retaining ring 9, both ends of the third stage stationary blades 5 are respectively installed on the third retaining ring 9 and the fourth retaining ring 10, the third stage moving blades 6 are arranged outside the third stage stationary blades 5, and the third stage moving blades 6 are fitted with the fourth retaining ring 10; a movable blade retaining ring 11 is arranged between the first-stage movable blade 2 and the second retaining ring 8, and the movable blade retaining ring 11 is installed on the second retaining ring 8;
the first-stage stationary blade 1 is provided with a first-stage stationary blade upper end wall 17, the lower end surface of the movable blade guard ring 11 is a movable blade guard ring end wall 18, the second-stage stationary blade 3 is provided with a second-stage stationary blade upper end wall 19, the lower end surface of the third retaining ring 9 is a third retaining ring end wall 20, the third-stage stationary blade 5 is provided with a third-stage stationary blade upper end wall 21, the lower section of the fourth retaining ring 10 is a fourth retaining ring end wall 22, and the first-stage stationary blade upper end wall 17, the movable blade guard ring end wall 18, the second-stage stationary blade upper end wall 19, the third retaining ring end wall 20, the third-stage stationary blade upper end wall 21 and the fourth retaining ring end wall 22 form a heavy-duty gas turbine radial flow passage upper end wall structure.
Claims (5)
1. An upper endwall stage connection structure adapted for use in a heavy duty gas turbine engine, comprising: the turbine blade support structure comprises a first-stage stationary blade (1), a first-stage moving blade (2), a second-stage stationary blade (3), a second-stage moving blade (4), a third-stage stationary blade (5), a third-stage moving blade (6), a first holding ring (7), a second holding ring (8), a third holding ring (9), a fourth holding ring (10) and a moving blade guard ring (11); wherein the first stage stationary blades (1) are mounted with a first retaining ring (7), a movable blade guard ring (11) is arranged between the first-stage movable blade (2) and the second holding ring (8), the movable blade guard ring (11) is arranged on the second holding ring (8), two ends of the second stage stationary blade (3) are respectively arranged on a second holding ring (8) and a third holding ring (9), a first sealing element (12) is arranged between the second-stage moving blade (4) and the third holding ring (9), the first sealing element (12) is installed on the third holding ring (9), two ends of the third stage stationary blades (5) are respectively arranged on a third holding ring (9) and a fourth holding ring (10), a second sealing element (13) is arranged between the third stage moving blade (6) and the fourth holding ring (10), and the second sealing element (13) is installed on the fourth holding ring (10).
2. The upper endwall stage connection structure for a heavy duty gas turbine as claimed in claim 1 wherein said first retaining ring (7) has first connections (14) thereon, the first stage vanes (1) being mounted with the first connections (14).
3. The upper end wall stage connection structure suitable for a heavy duty gas turbine according to claim 1, wherein both ends of the second stage stationary blades (3) are respectively provided with a second connection portion (15), and the second stage stationary blades (3) are installed with the second and third holding rings (8, 9) through the second connection portions (15).
4. The upper endwall stage connection structure for a heavy duty gas turbine as claimed in claim 1, wherein said third stage vanes (5) have third connections (16) at both ends, respectively, the third stage vanes (5) being mounted to a third and a fourth carrier ring (9, 10) via the third connections (16).
5. The upper endwall stage attachment structure for a heavy duty gas turbine as claimed in claim 1, the turbine blade support structure is characterized in that a first-stage stationary blade upper end wall (17) is arranged on a first-stage stationary blade (1), a moving blade guard ring end wall (18) is arranged on the lower end surface of a moving blade guard ring (11), a second-stage stationary blade upper end wall (19) is arranged on a second-stage stationary blade (3), a third retaining ring end wall (20) is arranged on the lower end surface of a third retaining ring (9), a third-stage stationary blade upper end wall (21) is arranged on a third-stage stationary blade (5), a fourth retaining ring end wall (22) is arranged on the lower section of a fourth retaining ring (10), the first-stage stator blade upper end wall (17), the rotor blade retaining ring end wall (18), the second-stage stator blade upper end wall (19), the third retaining ring end wall (20), the third-stage stator blade upper end wall (21) and the fourth retaining ring end wall (22) form an upper end wall structure of a radial flow channel of the heavy-duty gas turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021116818.7U CN212177224U (en) | 2020-06-16 | 2020-06-16 | Upper end wall level connection structure suitable for heavy gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021116818.7U CN212177224U (en) | 2020-06-16 | 2020-06-16 | Upper end wall level connection structure suitable for heavy gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212177224U true CN212177224U (en) | 2020-12-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021116818.7U Active CN212177224U (en) | 2020-06-16 | 2020-06-16 | Upper end wall level connection structure suitable for heavy gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212177224U (en) |
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2020
- 2020-06-16 CN CN202021116818.7U patent/CN212177224U/en active Active
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