CN218151163U - Gas turbine exhaust diffuser structure - Google Patents
Gas turbine exhaust diffuser structure Download PDFInfo
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- CN218151163U CN218151163U CN202221985225.3U CN202221985225U CN218151163U CN 218151163 U CN218151163 U CN 218151163U CN 202221985225 U CN202221985225 U CN 202221985225U CN 218151163 U CN218151163 U CN 218151163U
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Abstract
The utility model discloses a gas turbine exhaust diffuser structure, which comprises a corrugated pipe, a front section cooling cylinder, a rear section cooling cylinder and a cooling cylinder flange; the cooling cylinder flange, the front section cooling cylinder, the corrugated pipe and the rear section cooling cylinder are sequentially and coaxially mounted and connected together from front to back; the cooling cylinder flange is used for being coaxially attached and fixed to the rear end face of the nozzle ring rear disc. The utility model discloses a gas turbine exhaust diffuser structure, cooling cylinder adopt the sectional type design, and two sections intermediate junction bellows are in order to reduce exhaust diffuser structure axial rigidity, embedding cooling cylinder flange between cooling cylinder front end and the nozzle ring back plate to can guarantee nozzle ring back plate sealing performance, can avoid again causing gas turbine's machine casket axial displacement big on the left side.
Description
Technical Field
The utility model relates to a gas turbine, in particular to gas turbine exhaust diffuser structure.
Background
The Gas Turbine (Gas Turbine) is one of the most important power devices in the world, is an advanced and complex mechanical power device, is a high-tech intensive product, represents the comprehensive level of development of many theoretical science and engineering fields, and is the embodiment of national comprehensive strength. The combustor is one of the most important parts of the gas turbine, and the performance index of the combustor is an important basis for measuring the performance of the gas turbine. The combustor is used for fully mixing and combusting compressed air sent by the compressor and fuel, releasing energy stored in the fuel as much as possible, converting the energy into heat energy of high-temperature gas and guiding the heat energy into a turbine to do work.
The exhaust diffuser is an important structural component of the gas turbine, and the main function of the exhaust diffuser is to exhaust high-speed tail gas which does work through a turbine rotor. Because cooling cylinder and nozzle ring after-disc adopt the piston ring structure to seal in the tradition, consider that the piston ring takes place wearing and tearing and gas leakage scheduling problem for a long time to use, so adopt flange seal structure. The flange is connected with the cooling cylinder and the nozzle ring rear disc in a flexible connection mode, and the problem that the axial displacement of the nozzle ring is greatly changed due to overlarge rigidity of the cooling cylinder is solved.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide a gas turbine exhaust diffuser structure can guarantee the 15 sealing performance of nozzle cascade back plate, can avoid again causing gas turbine's machine casket axial displacement big on the large side.
In order to solve the above technical problem, the present invention provides a gas turbine exhaust diffuser structure, which includes a corrugated pipe 1, a front section cooling cylinder 21, a rear section cooling cylinder 22 and a cooling cylinder flange 11;
the cooling cylinder flange 11, the front section cooling cylinder 21, the corrugated pipe 1 and the rear section cooling cylinder 22 are sequentially and coaxially installed and connected together from front to back;
the cooling cylinder flange 11 is used for being coaxially attached and fixed to the rear end face of the nozzle ring rear disc 15.
Preferably, the cooling cylinder flange 11 is welded and fixed on the inner side surface at the front end of the front section cooling cylinder 21;
the cooling cylinder flange 11 is used for being coaxially attached and fixed to the rear end face of the nozzle ring rear disc 15 through a plurality of first bolts 14.
Preferably, the outer side surface of the front end of the corrugated pipe 1 is coaxially welded and fixed to the inner side surface of the front flange 9 of the corrugated pipe, and the inner side surface of the rear end of the front section cooling cylinder 21 is coaxially welded and fixed to the outer side surface of the front flange 9 of the corrugated pipe, so that the corrugated pipe 1 and the front section cooling cylinder 21 are coaxially mounted and connected together.
Preferably, the outer side surface of the rear end of the corrugated pipe 1 is coaxially welded and fixed to the inner side surface of the corrugated pipe rear flange 10, and the inner side surface of the front end of the rear section cooling cylinder 22 is coaxially welded and fixed to the outer side surface of the corrugated pipe rear flange 10, so that the corrugated pipe 1 and the rear section cooling cylinder 22 are coaxially mounted and connected together.
Preferably, the gas turbine exhaust diffuser structure further comprises an expansion pipe 3, an exhaust pipe 4, a connecting ring 5, an exhaust diffuser connecting flange 6, a connecting ring flange 7 and an exhaust pipe connecting flange 8;
the inner diameter of the expansion pipe 3 is gradually increased from front to back;
the cooling cylinder flange 11, the front section cooling cylinder 21, the corrugated pipe 1 and the rear section cooling cylinder 22 are coaxially sleeved outside the expansion pipe 3, and the cooling cylinder flange 11 is attached and sleeved outside the front end of the expansion pipe 3;
the connecting ring 5 is sequentially a front part, a middle part and a rear part from the front to the rear; the inner diameter of the front part of the connecting ring 5 is larger than that of the rear part of the connecting ring 5, and the inner diameter of the middle part of the connecting ring 5 is gradually reduced from front to back;
the outer side surface of the front part of the connecting ring 5 and the inner side surface of the connecting ring flange 7 are welded and fixed together;
the inner side surface of the rear part of the connecting ring 5 is welded and fixed with the outer side surface of the rear part of the expansion pipe 3;
the exhaust diffuser connecting flange 6 is coaxially connected and fixed on the connecting ring flange 7 through a second bolt 12;
the front part of the exhaust pipe 4 is coaxially sleeved outside the rear part of the expansion pipe 3;
the inner diameter of the rear part of the exhaust pipe 4 is gradually increased from front to rear;
the outer side surface of the front end of the exhaust pipe 4 is coaxially welded and fixed with the inner side surface of the exhaust pipe connecting flange 8;
the inner side surface of the exhaust pipe connecting flange 8 is coaxially welded and fixed to the outer side surface of the front end of the exhaust pipe 4;
the combustion chamber shell 18 is coaxially sleeved outside the rear end of the rear section cooling cylinder 22;
the exhaust pipe connecting flange 8, the connecting ring flange 7, the exhaust diffuser connecting flange 6 and the combustion chamber shell 18 are sequentially attached and coaxially connected and fixed together from back to front through a third bolt 13.
Preferably, the second bolt 12 is a hexagon socket bolt.
The utility model discloses a gas turbine exhaust diffuser structure, cooling cylinder adopt the sectional type design, and two sections intermediate junction bellows 1 are in order to reduce exhaust diffuser structure axial rigidity, and embedding cooling cylinder flange 11 between cooling cylinder front end and the nozzle ring back plate 15 to can guarantee nozzle ring back plate 15 sealing performance, can avoid again causing gas turbine's machine casket axial displacement big on the left.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings required for the present invention are briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic cross-sectional view of an embodiment of a gas turbine exhaust diffuser configuration according to the present invention;
FIG. 2 is a schematic cross-sectional view of a bellows and cooling jacket connection according to an embodiment of the gas turbine exhaust diffuser structure of the present invention;
fig. 3 is a schematic cross-sectional view illustrating a cooling cylinder and an exhaust pipe connected to a gas turbine exhaust diffuser structure according to an embodiment of the present invention.
Description of the reference numerals:
1, a corrugated pipe; 21 a front section cooling cylinder; 22 a rear section cooling cylinder 22;11 cooling the cylinder flange; 15 nozzle ring rear disc; 14 a first bolt; 9, a corrugated pipe front flange; 10 bellows rear flange; 3 expanding the tube; 4, exhausting the pipe; 5 connecting rings; 6, connecting a flange of the exhaust diffuser; 7 connecting the ring flange; 8, connecting the exhaust pipe with a flange; 12 a second bolt; 18 a combustor casing; 13 third bolt.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments, but not all embodiments, of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Example one
As shown in fig. 1 and 2, the gas turbine exhaust diffuser structure includes a corrugated pipe 1, a front section cooling cylinder 21, a rear section cooling cylinder 22 and a cooling cylinder flange 11;
the cooling cylinder flange 11, the front section cooling cylinder 21, the corrugated pipe 1 and the rear section cooling cylinder 22 are sequentially and coaxially mounted and connected together from front to back;
the cooling cylinder flange 11 is used for being coaxially attached and fixed to the rear end face of the nozzle ring rear disc 15.
In the exhaust diffuser structure of the gas turbine according to the first embodiment, the cooling cylinder is designed in a sectional manner, the bellows 1 is connected between the two sections to reduce the axial rigidity of the exhaust diffuser structure, and the cooling cylinder flange 11 is embedded between the front end of the cooling cylinder and the nozzle ring rear disk 15, so that the sealing performance of the nozzle ring rear disk 15 can be ensured, and the large axial displacement of the casing of the gas turbine can be avoided.
Example two
Based on the structure of the exhaust diffuser of the gas turbine in the first embodiment, as shown in fig. 2, the cooling cylinder flange 11 is welded and fixed to the inner side surface at the front end of the front section cooling cylinder 21;
the cooling cylinder flange 11 is used for being coaxially attached and fixed to the rear end face of the nozzle ring rear disk 15 through a plurality of first bolts 14.
EXAMPLE III
Based on the gas turbine exhaust diffuser structure of the first embodiment, as shown in fig. 2, the outer side surface at the front end of the corrugated pipe 1 is coaxially welded and fixed to the inner side surface of the corrugated pipe front flange 9, and the inner side surface at the rear end of the front section cooling cylinder 21 is coaxially welded and fixed to the outer side surface of the corrugated pipe front flange 9, so that the corrugated pipe 1 and the front section cooling cylinder 21 are coaxially installed and connected together.
Example four
Based on the structure of the exhaust diffuser of the gas turbine in the first embodiment, as shown in fig. 2, the outer side surface at the rear end of the corrugated pipe 1 is coaxially welded and fixed to the inner side surface of the corrugated pipe rear flange 10, and the inner side surface at the front end of the rear-stage cooling cylinder 22 is coaxially welded and fixed to the outer side surface of the corrugated pipe rear flange 10, so that the corrugated pipe 1 and the rear-stage cooling cylinder 22 are coaxially installed and connected together.
EXAMPLE five
According to the first embodiment, as shown in fig. 3, the exhaust diffuser structure of the gas turbine further includes an expansion pipe 3, an exhaust pipe 4, a connection ring 5, an exhaust diffuser connection flange 6, a connection ring flange 7, and an exhaust pipe connection flange 8;
the inner diameter of the expansion pipe 3 is gradually increased from front to back;
the cooling cylinder flange 11, the front section cooling cylinder 21, the corrugated pipe 1 and the rear section cooling cylinder 22 are coaxially sleeved outside the expansion pipe 3, and the cooling cylinder flange 11 is fitted and sleeved outside the front end of the expansion pipe 3;
the connecting ring 5 is sequentially a front part, a middle part and a rear part from front to back; the inner diameter of the front part of the connecting ring 5 is larger than that of the rear part of the connecting ring 5, and the inner diameter of the middle part of the connecting ring 5 is gradually reduced from front to back;
the outer side surface of the front part of the connecting ring 5 is welded and fixed with the inner side surface of the connecting ring flange 7;
the inner side surface of the rear part of the connecting ring 5 is welded and fixed with the outer side surface of the rear part of the expansion pipe 3;
the exhaust diffuser connecting flange 6 is coaxially connected and fixed on the connecting ring flange 7 through a second bolt 12;
the front part of the exhaust pipe 4 is coaxially sleeved outside the rear part of the expansion pipe 3;
the inner diameter of the rear part of the exhaust pipe 4 is gradually increased from front to rear;
the outer side face of the front end of the exhaust pipe 4 and the inner side face of the exhaust pipe connecting flange 8 are coaxially welded and fixed together;
the inner side surface of the exhaust pipe connecting flange 8 is coaxially welded and fixed to the outer side surface of the front end of the exhaust pipe 4;
the combustion chamber shell 18 is coaxially sleeved outside the rear end of the rear section cooling cylinder 22;
the exhaust pipe connecting flange 8, the connecting ring flange 7, the exhaust diffuser connecting flange 6 and the combustion chamber shell 18 are sequentially attached and coaxially connected and fixed together from back to front through a third bolt 13.
Preferably, the second bolt 12 is a hexagon socket head cap screw.
In the exhaust diffuser structure of the gas turbine according to the fifth embodiment, the connecting ring 5 has low radial rigidity, so that the expansion of the expansion pipe 3 is facilitated, and the function of fixing the expansion pipe 3 is achieved; the expansion pipe 3 and the exhaust pipe 4 are in flaring structures and play a role in reducing pressure and speed of high-speed airflow.
The structure of the exhaust diffuser of the gas turbine in the fifth embodiment is controlled as follows:
(a) Establishing a finite element simulation model of the diffuser;
(b) Determining the position of the corrugated pipe according to the simulation result;
(c) Researching the influence of the geometric parameters of the corrugated pipe on the rigidity of the corrugated pipe based on the position of the corrugated pipe in the step (b), and obtaining the geometric parameters of the corrugated pipe under the optimal axial rigidity;
(d) And calculating the final stress, deformation, fatigue life and creep life of the corrugated pipe based on the geometric parameters of the corrugated pipe under the optimal axial rigidity. When the four evaluation parameters meet the design requirements, the design is completed.
The above are merely preferred embodiments of the present application and are not intended to limit the present application. Various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (6)
1. The structure of the exhaust diffuser of the gas turbine is characterized by comprising a corrugated pipe (1), a front section cooling cylinder (21), a rear section cooling cylinder (22) and a cooling cylinder flange (11);
the cooling cylinder flange (11), the front section cooling cylinder (21), the corrugated pipe (1) and the rear section cooling cylinder (22) are sequentially and coaxially mounted and connected together from front to back;
the cooling cylinder flange (11) is used for being coaxially attached and fixed to the rear end face of the nozzle ring rear disc (15).
2. The gas turbine exhaust diffuser structure of claim 1,
the cooling cylinder flange (11) is welded and fixed on the inner side surface at the front end of the front section cooling cylinder (21);
the cooling cylinder flange (11) is used for being coaxially attached and fixed to the rear end face of the nozzle ring rear disc (15) through a plurality of first bolts (14).
3. The gas turbine exhaust diffuser structure of claim 1,
the outer side face of the front end of the corrugated pipe (1) is coaxially welded and fixed to the inner side face of a front corrugated pipe flange (9), the inner side face of the rear end of the front section cooling cylinder (21) is coaxially welded and fixed to the outer side face of the front corrugated pipe flange (9), and the corrugated pipe (1) and the front section cooling cylinder (21) are coaxially mounted and connected together.
4. The gas turbine exhaust diffuser structure of claim 1,
the outer side face of the rear end of the corrugated pipe (1) is coaxially welded and fixed to the inner side face of the corrugated pipe rear flange (10), the inner side face of the front end of the rear section cooling cylinder (22) is coaxially welded and fixed to the outer side face of the corrugated pipe rear flange (10), and the corrugated pipe (1) and the rear section cooling cylinder (22) are coaxially mounted and connected together.
5. The gas turbine exhaust diffuser structure of claim 1,
the gas turbine exhaust diffuser structure also comprises an expansion pipe (3), an exhaust pipe (4), a connecting ring (5), an exhaust diffuser connecting flange (6), a connecting ring flange (7) and an exhaust pipe connecting flange (8);
the inner diameter of the expansion pipe (3) is gradually increased from front to back;
the cooling cylinder flange (11), the front section cooling cylinder (21), the corrugated pipe (1) and the rear section cooling cylinder (22) are coaxially sleeved outside the expansion pipe (3), and the cooling cylinder flange (11) is fitted and sleeved outside the front end of the expansion pipe (3);
the connecting ring (5) is sequentially a front part, a middle part and a rear part from front to back; the inner diameter of the front part of the connecting ring (5) is larger than that of the rear part of the connecting ring (5), and the inner diameter of the middle part of the connecting ring (5) is gradually reduced from front to back;
the outer side surface of the front part of the connecting ring (5) is welded and fixed with the inner side surface of the connecting ring flange (7);
the inner side surface of the rear part of the connecting ring (5) is welded and fixed with the outer side surface of the rear part of the expansion pipe (3);
the exhaust diffuser connecting flange (6) is coaxially connected and fixed on the connecting ring flange (7) through a second bolt (12);
the front part of the exhaust pipe (4) is coaxially sleeved outside the rear part of the expansion pipe (3);
the inner diameter of the rear part of the exhaust pipe (4) is gradually increased from front to back;
the outer side face of the front end of the exhaust pipe (4) is coaxially welded and fixed with the inner side face of the exhaust pipe connecting flange (8);
the inner side surface of the exhaust pipe connecting flange (8) is coaxially welded and fixed to the outer side surface of the front end of the exhaust pipe (4);
the combustion chamber shell (18) is coaxially sleeved on the outer side of the rear end of the rear section cooling cylinder (22);
the exhaust pipe connecting flange (8), the connecting ring flange (7), the exhaust diffuser connecting flange (6) and the combustion chamber shell (18) are sequentially attached and coaxially connected and fixed together from back to front through a third bolt (13).
6. The gas turbine exhaust diffuser structure of claim 5,
the second bolt (12) is a hexagon socket head cap screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221985225.3U CN218151163U (en) | 2022-07-29 | 2022-07-29 | Gas turbine exhaust diffuser structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221985225.3U CN218151163U (en) | 2022-07-29 | 2022-07-29 | Gas turbine exhaust diffuser structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218151163U true CN218151163U (en) | 2022-12-27 |
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ID=84596467
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221985225.3U Active CN218151163U (en) | 2022-07-29 | 2022-07-29 | Gas turbine exhaust diffuser structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218151163U (en) |
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2022
- 2022-07-29 CN CN202221985225.3U patent/CN218151163U/en active Active
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