A carbon deposition preventing device for a gas turbine combustor

Abstract

The utility model provides a kind of gas turbine combustion chamber anti carbon deposition device, comprising: installation cylinder and splitter plate, the installation cylinder is in and is set inlaid groove, the middle part of inlaid groove inner side is set in cooling groove, and the upper end of installation cylinder outer side is set in liquid inlet, the lower end of installation cylinder outer side is set in liquid outlet, and liquid inlet and liquid outlet are all connected cooling groove, while jet pipe is fixedly connected in inlaid groove by limiting ring, the splitter plate is fixedly connected in the lower end of installation cylinder outer side, while the position of installation cylinder outer side corresponding to splitter plate is set in air inlet groove, and air inlet groove is connected the lower end of inlaid groove, and the lower surface of installation cylinder is fixedly connected fixed plate, and fixed plate surface is fixedly connected broken block relative to the position of inlaid groove.The utility model is by the cooperation of cooling groove, air inlet groove, splitter plate, broken block and discharge port, so that the device can effectively cool the jet pipe, and then the probability of gas coking can be reduced.

Description

Technical Field

[0001] This utility model relates to the field of gas turbine technology, specifically to a device for preventing carbon buildup in the combustion chamber of a gas turbine. Background Technology

[0002] When a gas turbine is running, fuel is ejected through the nozzle orifice at the nozzle head, and a small amount of fuel adheres to the nozzle head. Because the ejected fuel burns near the nozzle, the radiation temperature is high, so the nozzle is in a high-temperature environment for a long time during operation. After the gas turbine cuts off the fuel supply, a small amount of residue remains inside the nozzle. Although combustion in the combustion chamber stops, the temperature inside the combustion chamber is difficult to dissipate quickly. Consequently, the residue inside the nozzle is prone to coking at high temperatures. Since the nozzle flow channel size is small, coking and carbon deposits can easily reduce the nozzle area or even block the nozzle, reducing the theoretical mass of the fuel. This, in turn, affects the ignition and combustion efficiency of the combustion chamber, and impacts the subsequent use of the gas turbine. Utility Model Content

[0003] To overcome the shortcomings of the existing technology, a gas turbine combustion chamber anti-carbon deposit device is provided to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, a carbon deposit prevention device for a gas turbine combustion chamber is provided, comprising: an installation cylinder and a diverter plate. The installation cylinder has an interlocking groove, a cooling groove in the middle of the inner side of the interlocking groove, an inlet at the upper end of the outer side of the installation cylinder, and an outlet at the lower end of the outer side of the installation cylinder. Both the inlet and outlet are connected to the cooling groove. A jet pipe is fixedly connected to the interlocking groove via a limiting ring, and a gas residue groove is formed inside the jet pipe. The diverter plate is fixedly connected to the lower end of the outer side of the installation cylinder. An air inlet groove is formed on the outer side of the installation cylinder relative to the diverter plate, and the air inlet groove is connected to the lower end of the interlocking groove. A fixing plate is fixedly connected to the lower surface of the installation cylinder. A crushed block is fixedly connected to the surface of the fixing plate relative to the interlocking groove. A discharge port is symmetrically formed on the surface of the fixing plate near the crushed block, and the discharge port is connected to the interlocking groove.

[0005] Preferably, the mounting cylinder has a cuboid structure, the edges of the outer side of the mounting cylinder have an arc-shaped structure, the fitting groove opened inside the mounting cylinder has a cylindrical structure, and the cross-section of the mounting cylinder has an annular structure with an outer square and an inner circle.

[0006] Preferably, the cooling groove opened in the fitting groove has a spiral structure, and the limiting ring fixedly connected to the lower end of the fitting groove has a circular structure, and the axial section of the limiting ring has an L-shaped structure. At the same time, the limiting ring is located above the opening of the air inlet groove.

[0007] Preferably, the jet pipe has a cylindrical structure, the outer surface of the jet pipe and the fitting groove are interference fit, and the cross-section formed by the combination of the jet pipe and the gas residue groove is annular. At the same time, the opening at the lower end of the groove is frustum-shaped, and a limiting groove is opened on the lower surface of the jet pipe relative to the position of the bending part of the limiting ring. The limiting groove is annular.

[0008] Preferably, four sets of air inlet slots are symmetrically opened at the lower end of the outer side of the mounting cylinder. All four sets of air inlet slots are frustum-shaped structures, and the end of the air inlet slot near the fitting slot is inclined downward. At the same time, the diverter plate is U-shaped, and the cross-section of the diverter plate is C-shaped. The groove of the diverter plate is directly opposite the opening of the air inlet slot.

[0009] Preferably, the fixing plate has a square structure, the dimensions of the fixing plate and the end face of the mounting cylinder are matched, and the crushing block fixedly connected to the surface of the fixing plate has a hemispherical structure, the diameter of the crushing block is smaller than the diameter of the fitting groove, and the upper surface of the crushing block is located below the opening of the air inlet groove.

[0010] Preferably, multiple sets of discharge ports are opened at equal intervals around the upper surface of the fixed plate relative to the edge of the fitting groove in the circumferential direction, and the multiple sets of discharge ports are all cylindrical in structure. The multiple sets of discharge ports are combined together to form a circular distribution. At the same time, the positioning ring fixedly connected to the upper surface of the fixed plate has a U-shaped structure, and the positioning groove is opened on the lower surface of the mounting cylinder relative to the position of the positioning ring.

[0011] Compared with the prior art, the beneficial effects of this utility model are: By combining the mounting cylinder, cooling tank, and limiting ring, the nozzle can be effectively cooled, thereby reducing the probability of residual fuel inside the nozzle coking at high temperatures. Furthermore, the vertical arrangement of the device effectively reduces the likelihood of residue remaining inside the nozzle, further reducing the chance of the lower opening of the fuel tank being blocked and ensuring optimal fuel injection. Simultaneously, the combination of the flow divider and air intake slot reduces the probability of residue remaining on the surface of the fixed plate and broken pieces, and also provides appropriate air cooling to the lower end of the fitting groove, further reducing the likelihood of carbon buildup problems in the device and combustion chamber. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of an embodiment of the present utility model.

[0013] Figure 2 This is a top view of an embodiment of the present utility model.

[0014] Figure 3 This is an embodiment of the present utility model. Figure 1 A schematic diagram of the cross-section at point AA.

[0015] Figure 4This is an embodiment of the present utility model. Figure 1 Enlarged diagram of point B.

[0016] In the diagram: 1. Mounting cylinder; 2. Jet pipe; 3. Liquid inlet; 4. Cooling tank; 5. Gas residue tank; 6. Diverter plate; 7. Air inlet; 8. Limiting ring; 9. Fixing plate; 10. Fitting groove; 11. Crushed block; 12. Discharge port; 13. Positioning ring; 14. Liquid outlet. Detailed Implementation

[0017] Reference Figures 1 to 4 As shown, this utility model provides a carbon deposit prevention device for a gas turbine combustion chamber, including: an installation cylinder 1 and a diverter plate 6. The installation cylinder 1 has an interlocking groove 10, a cooling groove 4 in the middle of the inner side of the interlocking groove 10, an inlet 3 at the upper end of the outer side of the installation cylinder 1, and an outlet 14 at the lower end of the outer side of the installation cylinder 1. Both the inlet 3 and the outlet 14 are connected to the cooling groove 4. At the same time, a jet pipe 2 is fixedly connected to the interlocking groove 10 by a limiting ring 8. A gas residue groove 5 is opened inside the jet pipe 2. The diverter plate 6 is fixedly connected to the lower end of the outer side of the installation cylinder 1. An air inlet groove 7 is opened on the outer side of the installation cylinder 1 relative to the position of the diverter plate 6, and the air inlet groove 7 is connected to the lower end of the interlocking groove 10. A fixing plate 9 is fixedly connected to the lower surface of the installation cylinder 1. A crushing block 11 is fixedly connected to the surface of the fixing plate 9 relative to the position of the interlocking groove 10. At the same time, a discharge port 12 is symmetrically opened on the surface of the fixing plate 9 near the position of the crushing block 11, and the discharge port 12 is connected to the interlocking groove 10.

[0018] In this embodiment, after the gas turbine cuts off the gas supply, combustion inside the combustion chamber gradually ceases. The residue in the gas residue tank 5 of the jet pipe 2 continues to fall under the influence of gravity, impacting the crushing block 11 and breaking the residue into fine droplets. External gas flows into the fitting groove 10 through the diverter plate 6 and the air inlet 7, and the airflow carries the fine droplets from the discharge port 12 into the combustion chamber for combustion. During the airflow, the lower end of the jet pipe 2 is cooled by air. Then, the coolant flows into the cooling tank 4 through the inlet 3 and flows out of the cooling tank 4 through the outlet 14, allowing the coolant to quickly cool the jet pipe 2. This reduces the probability of coking of the residue in the residue tank 5 due to continuous high temperature, thereby helping to reduce the probability of carbon buildup in the combustion chamber and jet pipe 2.

[0019] In a preferred embodiment, the mounting cylinder 1 has a cuboid structure, the edges of the outer side of the mounting cylinder 1 have an arc-shaped structure, and the fitting groove 10 opened inside the mounting cylinder 1 has a cylindrical structure. At the same time, the cross-section of the mounting cylinder 1 has an annular structure with a square outer surface and a circular inner surface.

[0020] In this embodiment, as Figure 1 and Figure 2The arc-shaped edge on the outer side of the mounting cylinder 1 can effectively reduce the probability of thermal stress accumulation at the edge of the mounting cylinder 1, and reduce the probability of damage to the mounting cylinder 1.

[0021] In a preferred embodiment, the cooling groove 4 opened in the fitting groove 10 has a spiral structure, and the limiting ring 8 fixedly connected to the lower end of the fitting groove 10 has a circular structure, and the axial section of the limiting ring 8 has an L-shaped structure. At the same time, the limiting ring 8 is located above the opening of the air intake groove 7.

[0022] In this embodiment, as Figure 1 , Figure 2 and Figure 4 The combination of the inlet 3, cooling tank 4 and outlet 14 allows the coolant to flow rapidly on the surface of the jet pipe 2, thereby effectively enhancing the cooling effect of the jet pipe 2 and reducing the probability of coking of the residue in the residue tank 5 due to continuous high temperature. At the same time, the setting of the limiting ring 8 can not only limit the installation position of the jet pipe 2, but also help enhance the sealing effect at the connection between the mounting cylinder 1 and the jet pipe 2.

[0023] In a preferred embodiment, the jet pipe 2 has a cylindrical structure, the outer side of the jet pipe 2 and the fitting groove 10 are interference fit, and the radial cross section formed by the jet pipe 2 and the residue groove 5 is annular. At the same time, the lower opening of the residue groove 5 is frustoconical, and a limiting groove is opened on the lower surface of the jet pipe 2 relative to the position of the bending part of the limiting ring 8. The limiting groove is annular.

[0024] In this embodiment, as Figure 1 , Figure 2 and Figure 4 The interference fit between the jet pipe 2 and the fitting groove 10 ensures a good sealing effect on the contact surface between them, thus effectively preventing accidental leakage of coolant. At the same time, the structure of the opening at the lower end of the residue groove 5 helps to enhance the impact force when the gas is ejected, thereby enhancing the combustion effect of the gas.

[0025] As a preferred embodiment, four sets of air inlet grooves 7 are symmetrically opened at the lower end of the outer side of the mounting cylinder 1. All four sets of air inlet grooves 7 are frustoconical in shape, and the end of the air inlet groove 7 near the fitting groove 10 is inclined downward. At the same time, the diverter plate 6 is U-shaped, and the cross section of the diverter plate 6 is C-shaped. The groove of the diverter plate 6 is directly opposite the opening of the air inlet groove 7.

[0026] In this embodiment, as Figure 1 and Figure 3The design of the diverter plate 6 allows one set of gas pipes to simultaneously supply gas to four sets of air inlet slots 7, thereby effectively simplifying the structure of the device. At the same time, the design of the air inlet slots 7 can effectively enhance the flow velocity of the airflow when it flows into the interlocking slot 10, so that the airflow can quickly carry the gas into the combustion chamber of the gas turbine for combustion. It can also provide auxiliary air cooling for the jet pipe 2 and the crushed block 11, reducing the probability of carbon buildup on their surfaces.

[0027] In a preferred embodiment, the fixing plate 9 has a square structure, the dimensions of the fixing plate 9 and the end face of the mounting cylinder 1 are matched, and the breaking block 11 fixedly connected to the surface of the fixing plate 9 has a hemispherical structure. The diameter of the breaking block 11 is smaller than the diameter of the fitting groove 10, and the upper surface of the breaking block 11 is located below the opening of the air inlet groove 7.

[0028] In a preferred embodiment, multiple sets of discharge ports 12 are opened at equal intervals around the edge of the fitting groove 10 on the upper surface of the fixing plate 9, and the multiple sets of discharge ports 12 are all cylindrical in shape. The multiple sets of discharge ports 12 are combined together to form a circular distribution. At the same time, the positioning ring 13 fixedly connected to the upper surface of the fixing plate 9 has a U-shaped structure, and the positioning groove is opened on the lower surface of the mounting cylinder 1 relative to the positioning ring 13.

[0029] In this embodiment, as Figure 1 and Figure 3 The opening of the discharge port 12 can effectively enhance the efficiency of the airflow carrying the gas out, and can also effectively reduce the probability of gas remaining in the fitting groove 10, ensuring that the gas can be injected into the combustion chamber of the gas turbine for corresponding combustion, thereby reducing the probability of carbon deposits in the combustion chamber and inside the device. At the same time, the setting of the positioning ring 13 can help enhance the installation efficiency of the fixing plate 9.

[0030] The gas turbine combustion chamber anti-carbon deposit device of this utility model, through the cooperation of cooling tank 4, air inlet tank 7, flow divider 6, crushing block 11 and discharge port 12, enables the device to effectively perform dual cooling treatment on the jet pipe 2, thereby reducing the probability of coking of the gas and thus reducing the probability of carbon deposit problems in the combustion chamber and inside the device.

Claims

1. A device for preventing carbon buildup in a gas turbine combustion chamber, comprising: The mounting cylinder (1) and the diverter plate (6) are characterized in that: a fitting groove (10) is opened in the mounting cylinder (1), a cooling groove (4) is opened in the middle of the inner side of the fitting groove (10), and a liquid inlet (3) is opened at the upper end of the outer side of the mounting cylinder (1), and a liquid outlet (14) is opened at the lower end of the outer side of the mounting cylinder (1). The liquid inlet (3) and the liquid outlet (14) are both connected to the cooling groove (4). At the same time, the jet pipe (2) is fixedly connected to the fitting groove (10) by a limiting ring (8), and a gas residue groove (5) is opened inside the jet pipe (2). The diverter plate (6) is fixedly connected to the lower end of the outer side of the mounting cylinder (1), and the outer side of the mounting cylinder (1) is provided with an air inlet groove (7) corresponding to the position of the diverter plate (6), and the air inlet groove (7) is connected to the lower end of the fitting groove (10). The lower surface of the mounting cylinder (1) is fixedly connected with a fixing plate (9), and the surface of the fixing plate (9) is fixedly connected with a crushed block (11) relative to the position of the fitting groove (10). At the same time, the surface of the fixing plate (9) is symmetrically provided with a discharge port (12) near the position of the crushed block (11), and the discharge port (12) is connected to the fitting groove (10).

2. The anti-carbon deposit device for a gas turbine combustion chamber according to claim 1, characterized in that, The mounting cylinder (1) has a cuboid structure, the edges of the outer side of the mounting cylinder (1) have an arc-shaped structure, and the fitting groove (10) opened inside the mounting cylinder (1) has a cylindrical structure. At the same time, the cross-section of the mounting cylinder (1) has an annular structure with an outer square and an inner circle.

3. The anti-carbon deposit device for a gas turbine combustion chamber according to claim 1, characterized in that, The cooling groove (4) opened in the fitting groove (10) has a spiral structure, and the limiting ring (8) fixedly connected to the lower end of the fitting groove (10) has a circular structure, and the axial section of the limiting ring (8) has an L-shaped structure. At the same time, the limiting ring (8) is located above the opening of the air inlet groove (7).

4. The anti-carbon deposit device for a gas turbine combustion chamber according to claim 1, characterized in that, The jet pipe (2) has a cylindrical structure. The outer side of the jet pipe (2) and the fitting groove (10) are in an interference fit. The radial cross section formed by the jet pipe (2) and the gas residue groove (5) is annular. At the same time, the lower opening of the gas residue groove (5) is frustum-shaped. The lower surface of the jet pipe (2) is provided with a limiting groove corresponding to the position of the bend of the limiting ring (8). The limiting groove is annular.

5. The anti-carbon deposit device for a gas turbine combustion chamber according to claim 1, characterized in that, Four sets of air inlet grooves (7) are symmetrically opened at the lower end of the outer side of the mounting cylinder (1). The four sets of air inlet grooves (7) are all in the shape of a frustum. The end of the air inlet groove (7) close to the fitting groove (10) is inclined downward. At the same time, the diverter plate (6) is in the shape of a square. The cross section of the diverter plate (6) is in the shape of a c. The groove of the diverter plate (6) is directly opposite the opening of the air inlet groove (7).

6. The anti-carbon deposit device for a gas turbine combustion chamber according to claim 1, characterized in that, The fixing plate (9) has a square structure. The dimensions of the fixing plate (9) and the end face of the mounting cylinder (1) are compatible. The broken block (11) fixedly connected to the surface of the fixing plate (9) has a hemispherical structure. The diameter of the broken block (11) is smaller than the diameter of the fitting groove (10). At the same time, the upper surface of the broken block (11) is located below the opening of the air inlet groove (7).

7. The anti-carbon deposit device for a gas turbine combustion chamber according to claim 1, characterized in that, Multiple sets of discharge ports (12) are opened at equal intervals around the edge of the fitting groove (10) on the upper surface of the fixed plate (9), and the multiple sets of discharge ports (12) are all cylindrical in shape. The multiple sets of discharge ports (12) are combined together to form a circular distribution. At the same time, the positioning ring (13) fixedly connected to the upper surface of the fixed plate (9) is in the shape of a square, and the positioning groove is opened on the lower surface of the mounting cylinder (1) relative to the positioning ring (13).

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