Sealing element structure for combustion chamber of gas turbine

Abstract

A seal structure for a combustion chamber of a gas turbine. When the sealing element is impacted by airflow for a long time and the rigidity of the sealing element is insufficient, the sealing element can be deformed and vibrated to cause failure, so that the combustion chamber part has the conditions of local high temperature and dislocation. The sealing element comprises a sealing element inner ring and a sealing element outer ring, the sealing element inner ring and the sealing element outer ring are concentrically matched, and the movable end of the sealing element inner ring is provided with a bent part and completely covers the movable end of the outer ring; the sealing element inner ring is provided with a plurality of inner ring gaps which are uniformly distributed; the sealing piece outer ring is provided with a plurality of outer ring gaps which are evenly distributed, the positions of the outer ring gaps coincide with the positions of the inner ring gaps, and the number of the outer ring gaps is consistent with that of the inner ring gaps. The invention is applied to gas turbine combustion chamber sealing.

Description

Technical Field

[0001] The invention relates to a sealing structure for a combustion chamber of a gas turbine. Background Art

[0002] At present, flexible spring clamp seals are commonly used in gas turbine combustion chambers for hoods and flame tubes; between the flame tube and the transition section, they are used to provide concentric control between the co-annular parts and provide sealing effects. The seal achieves the sealing effect by maintaining the degree of freedom on one side of the spring ring. At the same time, the seal also needs to ensure that a certain flow of air passes through the seal to ensure the temperature of the seal itself and nearby combustion chamber components. However, if the seal is impacted by the airflow for a long time, the seal may deform and vibrate if the rigidity is insufficient, leading to failure, causing local high temperature and misalignment of the combustion chamber components, which poses a risk to the continuous operation of the gas turbine. Summary of the invention

[0003] The purpose of the present invention is to solve the above-mentioned problems and provide a seal structure for a gas turbine combustion chamber, which can improve the seal stiffness and reduce the risks of seal vibration and deformation while ensuring the air flow through the seal.

[0004] The above purpose is achieved through the following technical solutions: A sealing structure for a gas turbine combustion chamber, comprising: a sealing inner ring and a sealing outer ring, wherein the sealing inner ring is concentrically matched with the sealing outer ring, and the movable end of the sealing inner ring has a curved portion and completely covers the movable end of the outer ring; The inner ring of the seal has a plurality of inner ring gaps that are evenly arranged; The outer ring of the seal has a plurality of outer ring gaps that are evenly arranged, the positions of the outer ring gaps and the inner ring gaps coincide with each other, and the number of the outer ring gaps is consistent with the number of the inner ring gaps.

[0005] The seal structure for a gas turbine combustion chamber is described, wherein the inner ring gap includes an inner ring gap a and an inner ring gap b, and the gaps a and b are both composed of welding holes and gaps, the welding hole is close to the fixed end of the inner ring of the seal, and the distance between the center of the welding hole and the fixed end of the inner ring of the seal is 5%-20% of the total length of the inner ring of the seal, the length of the gap a extends from the welding hole to the end of the movable end of the inner ring of the seal, and the distance between the inner ring gap b and the end face of the inner ring of the seal is 10%-30% of the total length of the inner ring of the seal.

[0006] The sealing structure for a gas turbine combustion chamber has a gap width of 0.5 mm to 2 mm.

[0007] In the sealing structure for a gas turbine combustion chamber, the inner ring gap a is in multiple relation with the inner ring gap b, and the inner ring gap a and the inner ring gap b are arranged alternately.

[0008] In the sealing structure for a gas turbine combustion chamber, all the outer ring gaps of the outer ring of the sealing are non-penetrating gaps. Beneficial Effects

[0009] 1. The present invention proposes a sealing structure for concentrically assembled components of a gas turbine combustion chamber, which can improve the strength of the seal, reduce the vibration of the seal caused by the airflow in the combustion chamber, reduce the fatigue loss of the seal, and increase the service life of the seal.

[0010] 2. The sealing structure proposed in the present invention has good rigidity and is not easily deformed, which can ensure the cooling effect of the cooling gas on the combustion chamber components and reduce the risk of high-temperature areas. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 The overall cross-sectional view of the seal; Figure 2 It is a schematic diagram of the inner ring of the seal; Figure 3 It is a schematic diagram of the outer ring of the seal; Figure 4 It is a schematic diagram of the seal gap; Figure 5 It is a schematic diagram of the installation of the connection between the nozzle cap and the flame tube of the present invention; Figure 6 It is a schematic diagram of the installation of the present invention at the connection between the flame tube and the transition section; In the figure: 1. Inner ring of seal; 2. Outer ring of seal; 3. Moving end of seal; 4. Fixed end of seal; 5. Moving end of inner ring; 6. Fixed end of inner ring; 7. Inner ring gap a; 8. Inner ring gap b; 9. Moving end of outer ring; 10. Fixed end of outer ring; 11. Outer ring gap; 12. Welding hole; 13. Gap; 14. Seal; 15. Nozzle cap; 16. Flame tube head; 17. Flame tube tail; 18. Guide bushing; 19. Transition section head. DETAILED DESCRIPTION

[0012] Reference Figure 1-Figure 4 , a sealing structure for a gas turbine combustion chamber, comprising: a sealing inner ring 1 and a sealing outer ring 2, wherein the sealing inner ring is concentrically matched with the sealing outer ring, and the sealing inner ring movable end 5 has a curved portion and completely covers the outer ring movable end 9; The inner ring of the seal has a plurality of inner ring gaps that are evenly arranged; The outer ring of the seal has a plurality of outer ring gaps 11 that are evenly arranged. The positions of the outer ring gaps and the inner ring gaps coincide with each other, and the number of the outer ring gaps is consistent with the number of the inner ring gaps.

[0013] A plurality of inner ring gaps are arranged in the inner ring of the seal, and a plurality of outer ring gaps are arranged in the outer ring of the seal. The gaps are used for welding the seal at the welding holes and for allowing air to pass through the gaps to protect the sealing structure when it expands due to heat and increase its durability.

[0014] The outer ring gaps of the outer ring of the seal are all non-through gaps, the inner ring gaps include inner ring gap a, part number: 7 and inner ring gap b, part number: 8, inner ring gap b is a through gap, inner ring gap a is a non-through gap, the end of the gap extending from the welding hole to the corresponding active end is a through gap, and the end of the gap not extending from the welding hole to the corresponding active end is a non-through gap; The gaps a and b are both composed of a welding hole 12 and a gap 13. The welding hole is located close to the fixed end 6 of the inner ring of the seal, and the distance between the center of the welding hole and the fixed end of the inner ring of the seal is 5%-20% of the total length of the inner ring of the seal. The length of the gap a extends from the welding hole to the end of the movable end of the inner ring of the seal, and the distance between the inner ring gap b and the end face of the inner ring of the seal is 10%-30% of the total length of the inner ring of the seal.

[0015] The sealing structure for a gas turbine combustion chamber has a gap width of 0.5 mm to 2 mm.

[0016] In the seal structure for a gas turbine combustion chamber, the inner ring gap a is in multiple relation with the inner ring gap b, and the inner ring gap a and the inner ring gap b are arranged alternately, and the seal stiffness is adjusted by sensitively adjusting the gap distribution, thereby reducing the risk of seal deformation; The gaps in the outer ring of the seal are all composed of non-penetrating gaps, which are located in the same position as the gaps in the inner ring, and the number is the same as the number of inner rings. The fixed end of the inner ring of the seal is welded to the outer ring of the seal, and the movable end of the inner ring of the seal completely covers the movable end of the outer ring, and a certain gap is maintained between the curved part of the inner ring and the movable end of the outer ring. The inner ring completely covers the movable end of the outer ring to reduce the impact of air impact on the seal.

[0017] Reference Figure 5 The seal is connected to the nozzle cap by welding at the fixed end. The fixed end is located between the gap between the nozzle cap and the front end of the flame tube. The free end is close to the nozzle cap and is located outside the gap between the nozzle cap and the front end of the flame tube. It is used to achieve the sealing of the nozzle cap and the front end of the flame tube. It has a certain rigidity while ensuring the sealing performance and has good anti-vibration and anti-deformation capabilities.

[0018] Reference Figure 6 The seal is connected to the front end of the transition section by welding at the fixed end. The fixed end is located between the gap between the rear end of the flame tube and the front end of the transition section. The free end is close to the rear end of the flame tube and is located outside the gap between the rear end of the flame tube and the front end of the transition section. It is used to achieve the sealing of the plug-in connection between the rear end of the flame tube and the front end of the transition section. It has a certain rigidity while ensuring the sealing performance and has good anti-vibration and anti-deformation capabilities.

Claims

1. A sealing structure for a gas turbine combustion chamber, characterized in that: The components include: a sealing inner ring and a sealing outer ring, wherein the sealing inner ring is concentrically matched with the sealing outer ring, and the movable end of the sealing inner ring has a curved portion and completely covers the movable end of the outer ring; The inner ring of the seal has a plurality of inner ring gaps that are evenly arranged; The outer ring of the seal has a plurality of outer ring gaps that are evenly arranged, the positions of the outer ring gaps and the inner ring gaps coincide with each other, and the number of the outer ring gaps is consistent with the number of the inner ring gaps.

2. The seal structure for a gas turbine combustion chamber according to claim 1, characterized in that: The inner ring gap includes inner ring gap a and inner ring gap b. Both gaps a and b are composed of welding holes and gaps. The welding hole is close to the fixed end of the inner ring of the seal, and the distance between the center of the welding hole and the fixed end of the inner ring of the seal is 5%-20% of the total length of the inner ring of the seal. The length of the gap a extends from the welding hole to the end of the movable end of the inner ring of the seal, and the distance between the inner ring gap b and the end face of the inner ring of the seal is 10%-30% of the total length of the inner ring of the seal.

3. The seal structure for a gas turbine combustion chamber according to claim 2, characterized in that: The gap width is 0.5mm-2mm.

4. A sealing structure for a gas turbine combustion chamber according to claim 3, characterized in that: The inner circle gap a is in multiple relation with the inner circle gap b, and the inner circle gap a and the inner circle gap b are arranged alternately.

5. A sealing structure for a gas turbine combustion chamber according to claim 4, characterized in that: The outer ring gaps of the outer ring of the sealing element are all non-through gaps.

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