Gas turbine air supply sealing assembly and gas turbine

Abstract

The present invention relates to the technical field of gas turbines, and particularly relates to a gas supply sealing assembly for a gas turbine and a gas turbine. The gas supply sealing assembly for the gas turbine comprises a turbine disk, a seal ring and a sealing assembly. A moving blade gas supply channel is provided in the turbine disk. The seal ring and the turbine disk are arranged at intervals in the radial direction of the turbine disk. The sealing assembly is arranged between the turbine disk and the seal ring. The sealing assembly, the turbine disk and the seal ring enclose a gas supply cavity, and the moving blade gas supply channel is communicated with the gas supply cavity. The gas supply sealing assembly of the present invention can increase the cold air flow rate in the moving blade cold air channel and improve the starting efficiency of the gas turbine.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and particularly to a gas turbine air supply sealing assembly and a gas turbine. Background Art

[0002] The working principle of a gas turbine engine is to use the compressed air of a compressor and the high-temperature and high-pressure gas generated after the fuel is mixed and burned to drive the turbine to rotate at a high speed, and the turbine drives the compressor through a turbine shaft, thus forming continuous operation. The turbine consists of stationary guide vanes (forming the stator component) and rotating moving blades (forming the rotor component). To ensure the reliable operation of the turbine rotor and avoid rubbing between the rotating and stationary parts, there is a certain gap between the rotating and stationary turbine disks. The existence of axial and radial gaps between the roots of the guide vanes and the moving blades may cause the high-temperature gas of the gas turbine to invade the turbine disk cavity through this gap, resulting in too high a temperature of the turbine disk and affecting the working safety and service life of the turbine disk. Therefore, cold air from the outlet of the high-pressure compressor is usually introduced into the turbine disk cavity as sealing gas to cool the turbine disk while preventing the gas from invading the turbine disk cavity, and at the same time, cooling gas is also provided for the moving blades.

[0003] The related art proposes a sealing structure for a turbine disk cavity with bypass air extraction, which adopts a mini disk seal. Oblique holes need to be drilled on the mini disk to introduce cold air into the cold air passage of the moving blade, resulting in too small a cold air flow rate flowing into the cold air passage of the moving blade and affecting the cooling of the moving blade. Moreover, the rotation of the mini disk with the rotor increases the rotational inertia of the gas turbine, thereby reducing the starting efficiency of the gas turbine. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems in the related art to some extent. For this purpose, an embodiment of the present invention provides a gas turbine air supply sealing assembly, which can increase the cold air flow rate in the cold air passage of the moving blade and improve the starting efficiency of the gas turbine.

[0005] The gas turbine air supply sealing assembly according to an embodiment of the present invention includes: a turbine disk, in which there is a moving blade air supply passage; a sealing ring, which is arranged at a radial interval from the turbine disk on the turbine disk; a sealing assembly, which is arranged between the turbine disk and the sealing ring, and the sealing assembly, the turbine disk and the sealing ring enclose an air supply cavity, and the moving blade air supply passage is communicated with the air supply cavity.

[0006] The gas turbine air supply sealing assembly of the present invention can increase the cold air flow rate in the cold air passage of the moving blade and improve the starting efficiency of the gas turbine.

[0007] In some embodiments, the turbine disk has a first protrusion and a second protrusion, both the first protrusion and the second protrusion extend along the axial direction of the turbine disk, and the first protrusion and the second protrusion are arranged at a radial interval on the turbine disk.

[0008] The sealing assembly includes a first sealing member and a second sealing member. The first sealing member is located between the first protrusion and the seal ring, and the second sealing member is located between the second protrusion and the seal ring.

[0009] In some embodiments, the dimension of the first protrusion in the axial direction of the turbine disk is smaller than the dimension of the second protrusion in the axial direction of the turbine disk.

[0010] In some embodiments, both the first sealing member and the second sealing member include a brush seal and a labyrinth seal, and the brush seal and the labyrinth seal are arranged at intervals in the axial direction of the turbine disk.

[0011] In some embodiments, the seal ring has a sealing cavity inside. One end of the sealing cavity is communicated with an external gas source, and the other end of the sealing cavity is communicated with the air supply cavity.

[0012] In some embodiments, the gas turbine air supply sealing assembly further includes a nozzle. The nozzle is connected to the seal ring, and the inlet of the nozzle is communicated with the sealing cavity, and the outlet of the nozzle is communicated with the air supply cavity.

[0013] In some embodiments, the number of the sealing assemblies is multiple, and the multiple sealing assemblies are arranged at intervals in the circumferential direction of the turbine disk.

[0014] The gas turbine according to an embodiment of the present invention includes: an air supply sealing assembly, which is the gas turbine air supply sealing assembly described in any one of the above; moving blades, which surround the outside of the turbine disk; and stationary blades, which surround the outside of the seal ring.

[0015] In some embodiments, the gas turbine further includes a baffle. The moving blade and the turbine disk are arranged at intervals between the turbine disks to form a root cavity, and the baffle is connected to the turbine disk to seal the root cavity.

[0016] In some embodiments, the number of the baffles is multiple, and the multiple baffles correspond to the multiple sealing assemblies one by one. Description of the Drawings

[0017] Figure 1 is a schematic diagram of the gas turbine air supply sealing assembly according to an embodiment of the present invention.

[0018] Figure 2 is Figure 1 an enlarged view of area A in

[0019] Reference Signs:

[0020] Turbine disk 1, first protrusion 11, second protrusion 12,

[0021] Sealing ring 2,

[0022] Sealing assembly 3, first sealing component 31, first labyrinth seal 311, first brush seal 312, first honeycomb seal 313, second sealing component 32, second labyrinth seal 321, second brush seal 322, second honeycomb seal 323,

[0023] Moving blade air supply channel 4, air supply cavity 5, moving blade 6, stationary blade 7, baffle 8, first cold air channel 9, second cold air channel 10, air supply hole 20. Specific embodiments

[0024] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, and should not be construed as limiting the present invention.

[0025] As Figure 1 shown, the gas turbine air supply sealing assembly of the embodiment of the present invention includes a turbine disk 1, a sealing ring 2, and a sealing assembly 3. The turbine disk 1 has a moving blade 6 air supply channel 4 therein. The sealing ring 2 and the turbine disk 1 are arranged at intervals in the radial direction of the turbine disk 1. The sealing assembly 3 is arranged between the turbine disk 1 and the sealing ring 2. The sealing assembly 3, the turbine disk 1, and the sealing ring 2 enclose an air supply cavity 5. The moving blade 6 air supply channel 4 communicates with the air supply cavity 5.

[0026] Specifically, as Figure 1 and Figure 2 shown, the turbine disk 1 has a moving blade 6 air supply channel 4 extending in the left - right direction. The sealing ring 2 and the turbine disk 1 are arranged at intervals in the radial direction of the turbine disk 1. The sealing assembly 3 is arranged in the gap between the turbine disk 1 and the sealing ring 2, that is, the sealing ring and the sealing ring 2, the turbine disk 1 enclose an air supply cavity 5.

[0027] The sealing ring 2 is provided with an air supply hole 20. The air supply hole 20 is adapted to supply gas into the air supply cavity 5 to cool the turbine disk 1 and improve the working efficiency of the turbine disk 1. The sealing assembly 3 is adapted to seal the air supply cavity 5 so that more gas in the air supply hole 20 flows into the moving blade 6 air supply channel 4.

[0028] The gas turbine air supply sealing assembly of the present invention can increase the cold air flow rate in the cold air passage of the moving blade 6 by providing the sealing assembly 3. Compared with the related art where a mini-disc is provided on the turbine disk 1 to seal the gap between the seal ring 2 and the turbine disk 1, and in the related art, inclined holes need to be drilled on the mini-disc provided on the turbine disk 1 to ensure the air supply flow rate of the air supply passage 4 of the moving blade 6. Furthermore, when the gas turbine starts, the weight of the mini-disc itself increases the rotational inertia of the turbine disk 1. The gas turbine sealing assembly 3 of the embodiment of the present invention seals the gap between the seal ring 2 and the turbine disk 1 by using the sealing assembly 3, avoiding the use of a mini-disc to seal the gap between the seal ring 2 and the turbine disk 1, and avoiding drilling inclined holes on the mini-disc to ensure the air supply flow rate of the moving blade 6, thereby improving the starting speed of the gas turbine and the flow rate of the air supply passage 4 of the moving blade 6.

[0029] In some embodiments, the turbine disk 1 has a first protrusion 11 and a second protrusion 12. Both the first protrusion 11 and the second protrusion 12 extend along the axial direction of the turbine disk 1, and the first protrusion 11 and the second protrusion 12 are arranged at intervals in the radial direction of the turbine disk 1.

[0030] The sealing assembly includes a first sealing member 31 and a second sealing member 32. The first sealing member 31 is located between the first protrusion 11 and the seal ring 2, and the second sealing member 32 is located between the second protrusion 12 and the seal ring 2.

[0031] Specifically, as Figure 1 and Figure 2 shown, the first protrusion 11 and the second protrusion 12 extend in the left-right direction, the first protrusion 11 and the second protrusion 12 are arranged at intervals in the left-right direction, a first cold air passage 9 is formed in the left-right direction between the first protrusion 11 and the seal ring 2, the first seal is adapted to seal the first cold air passage 9, a second cold air passage 10 is formed in the radial direction of the turbine disk 1 between the seal ring 2 and the turbine disk 1, and the second sealing member 32 is adapted to seal the second cold air passage 10. Furthermore, the air supply volume entering the first cold air passage 9 and the second cold air passage 10 from the air supply holes 20 on the seal ring 2 is reduced, thereby increasing the air supply volume of the air supply passage 4 of the moving blade 6, improving the cooling efficiency of the moving blade 6, and further improving the working efficiency and safety of the gas turbine.

[0032] In some embodiments, the dimension of the first protrusion 11 in the axial direction of the turbine disk 1 is smaller than the dimension of the second protrusion 12 in the axial direction of the turbine disk 1.

[0033] The dimension of the first protrusion 11 in the left - right direction is smaller than that of the second protrusion 12 in the left - right direction. Consequently, the dimension of the first sealing member 31 in the left - right direction is larger than that of the second sealing member 32 in the left - right direction. As a result, the sealing performance of the first sealing member 31 for the first cold - air passage 9 in the left - right direction is greater than that of the second sealing member 32 in the left - right direction. Thus, the gas volume in the first cold - air passage 9 is less than that in the second cold - air passage 10. One end of the second cold - air passage 10 is in communication with the gas in the gas turbine. By increasing the gas flow rate in the second cold - air passage 10, the gas in the gas turbine is prevented from entering the second cold - air passage 10, thereby enhancing the stability and safety of the operation of the gas turbine.

[0034] In some embodiments, both the first sealing member 31 and the second sealing member 32 include a brush seal and a labyrinth seal, and the brush seal and the labyrinth seal are arranged at intervals in the axial direction of the turbine disk 1.

[0035] Specifically, as Figure 1 and Figure 2 shown, the brush seal is divided into a first brush seal 312 and a second brush seal 322, and the labyrinth seal is divided into a first labyrinth seal 311 and a second labyrinth seal 321. The first sealing member includes the first labyrinth seal 311 and the first brush seal 312, and the second sealing member includes the second labyrinth seal 321 and the second brush seal 322. One end of the first brush seal 312 is connected to the sealing ring 2, and the other end of the first brush seal 312 extends radially along the turbine disk 1 and is adapted to seal the first cold - air passage 9. Optionally, the first brush seal 312 includes a plurality of brush wires, one end of the plurality of brush wires extends radially along the turbine disk 1, and the plurality of brush wires extend in the direction close to the first protrusion 11. One end of the first labyrinth seal 311 is connected to one end of the first protrusion 11, and the other end of the first labyrinth seal 311 extends radially along the turbine disk 1 to seal the first cold - air passage 9. Optionally, the first labyrinth seal 311 is provided with a plurality of labyrinth teeth, and the plurality of labyrinth teeth are arranged at intervals in the left - right direction on the first protrusion 11 to seal the first cold - air passage 9, thereby improving the sealing performance of the first sealing member for the first cold - air passage 9 and further enhancing the stability and safety of the gas - supply sealing assembly of the gas turbine.

[0036] One end of the second brush seal 322 is connected to the seal ring 2. The other end of the second brush seal 322 extends radially along the turbine disk 1 to seal the second cold air passage 10, and the second brush seal 322 extends in the direction close to the seal ring 2. One end of the second labyrinth seal 321 is connected to one end of the seal ring 2. The other end of the second labyrinth seal 321 extends radially along the turbine disk 1 to seal the second cold air passage 10. Optionally, the second labyrinth seal 321 is provided with a plurality of labyrinth teeth. The plurality of labyrinth teeth are arranged at intervals in the left-right direction on the second protrusion 12 to seal the second cold air passage 10, thereby improving the sealing performance of the second seal for the second cold air passage 10, and further improving the stability and safety of the gas turbine air supply sealing assembly.

[0037] Optionally, the seal ring 2 is provided with a third protrusion. The third protrusion extends in the left-right direction, and the third protrusion is staggeredly arranged with the second protrusion 12 in the radial direction of the turbine disk 1. That is, one end of the second brush seal 322 is connected to the third protrusion. The other end of the second brush seal 322 extends radially along the turbine disk 1 to seal the second cold air passage 10, and the second brush seal 322 extends in the direction close to the third protrusion.

[0038] Optionally, the sealing assembly 3 further includes a honeycomb seal. The honeycomb seal includes a first honeycomb seal 313 and a second honeycomb seal 323. That is, the first seal includes a first labyrinth seal 311, a first brush seal 312, and a first honeycomb seal 313. The second seal includes a second labyrinth seal 321, a second brush seal 322, and a second honeycomb seal 323. One end of the first honeycomb seal is connected to the first protrusion 11. The other end of the first honeycomb seal 313 extends radially along the turbine disk 1 to seal the first cold air passage 9. Optionally, the first honeycomb seal 313 and the first labyrinth seal 311 are arranged at intervals relative to each other in the radial direction of the turbine disk 1 to improve the sealing performance of the first seal for the first cold air passage 9, and further improve the stability and safety of the gas turbine air supply sealing assembly.

[0039] One end of the second honeycomb seal is connected to the second protrusion 12. The other end of the second honeycomb seal 323 extends radially along the turbine disk 1 to seal the second cold air passage 10. Optionally, the second honeycomb seal 323 and the second labyrinth seal 321 are arranged at intervals relative to each other in the radial direction of the turbine disk 1 to improve the sealing performance of the first seal for the first cold air passage 9, and further improve the stability and safety of the gas turbine air supply sealing assembly.

[0040] In some embodiments, the seal ring 2 has a sealing cavity inside. One end of the sealing cavity is communicated with an external air source, and the other end of the sealing cavity is communicated with the air supply cavity 5.

[0041] Specifically, as Figure 1 and Figure 2As shown, there is a sealing cavity inside the sealing ring 2. One end of the sealing cavity is connected to a gas supply source, and the other end is connected to the gas supply hole 20 to introduce gas into the gas supply cavity 5. By providing the sealing cavity, while the cooling gas cools the sealing ring 2, the gas accumulates in the sealing cavity to form a stable pressure, thereby facilitating the gas to enter the gas supply cavity 5 through the gas supply hole 20, and further improving the stability and safety of the gas supply of the gas turbine.

[0042] In some embodiments, the gas supply sealing assembly of the gas turbine further includes a nozzle. The nozzle is connected to the sealing ring 2, and the inlet of the nozzle is connected to the sealing cavity, and the outlet of the nozzle is connected to the gas supply cavity 5.

[0043] Specifically, as Figure 1 and Figure 2 shown, the inlet of the nozzle is connected to the sealing cavity of the sealing ring 2, and the outlet of the nozzle is connected to the gas supply cavity 5. In other words, the inlet of the nozzle is connected to the gas supply hole 20, and the other end of the nozzle is connected to the gas supply cavity 5. By providing the nozzle, the stability and safety of the gas supply of the gas turbine are improved.

[0044] In some embodiments, the number of the sealing assemblies 3 is multiple, and the multiple sealing assemblies 3 are arranged at intervals in the circumferential direction of the turbine disk 1.

[0045] The number of the sealing assemblies 3 is multiple. The multiple sealing assemblies 3 are arranged between the turbine disk 1 and the sealing ring 2 and are arranged at intervals in the circumferential direction of the turbine disk 1, so as to supply gas to the gas supply channels 4 of the multiple moving blades 6 on the turbine disk 1 of the gas turbine, and improve the stability and safety of the gas turbine.

[0046] The gas turbine according to the embodiment of the present invention includes a gas supply sealing assembly 3, a moving blade 6, and a stationary blade 7. The gas supply sealing assembly 3 is the gas supply sealing assembly of any one of the above, the moving blade 6 surrounds the outside of the turbine disk 1, and the stationary blade 7 surrounds the outside of the sealing ring 2.

[0047] Specifically, as Figure 1 and Figure 2 shown, one end of the moving blade 6 is connected to the turbine disk 1, and the moving blade 6 is adapted to generate mechanical energy by using the internal energy of the gas. One end of the stationary blade 7 is connected to the sealing ring 2, and the other end of the stationary blade 7 is adapted to guide the gas, and the stationary blade 7 is adapted to increase the flow rate of the gas, thereby improving the operating efficiency of the gas turbine. The sealing assembly 3 is adapted to seal the turbine disk 1 and the sealing ring 2 to form a gas supply cavity 5. One end of the sealing ring 2 is connected to a gas supply source, and the other end of the sealing ring 2 is connected to the nozzle to supply gas to the gas supply cavity 5. The sealing assembly 3 is adapted to seal the gas supply cavity 5 to increase the gas flow rate of the gas supply channel 4 of the moving blade 6.

[0048] In some embodiments of the gas turbine, it further includes a baffle 8. The moving blade 6 and the turbine disk 1 are arranged at intervals between the turbine disks 1 to form a root cavity, and the baffle 8 is connected to the turbine disk 1 to seal the root cavity.

[0049] Specifically, as Figure 1 and Figure 2 shown, one end of the baffle 8 is connected to the second protrusion 12, and the other end of the baffle 8 is connected to the moving blade 6 to isolate the Schengen cavity from the second cold air duct, thereby preventing the gas in the Schengen cavity from entering the second cold air passage 10, and further improving the stability and safety of the gas turbine operation.

[0050] In some embodiments, the number of the baffles 8 is multiple, and the multiple baffles 8 correspond to the multiple sealing components 3 one by one.

[0051] The multiple baffles 8 are connected to the multiple second protrusions 12 one by one, improving the stability and safety of the gas turbine.

[0052] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation of the present invention.

[0053] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined.

[0054] In the present invention, unless otherwise clearly specified and limited, the terms "mounted", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, or communicable with each other; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0055] In the present invention, unless otherwise clearly specified or limited, a first feature being "on" or "under" a second feature may mean that the first and second features are in direct contact, or the first and second features are indirectly in contact via an intermediate medium. Further, a first feature being "above", "over" and "on top of" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the horizontal height of the first feature is higher than that of the second feature. A first feature being "under", "below" and "beneath" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the horizontal height of the first feature is less than that of the second feature.

[0056] In the present invention, the terms "an embodiment", "some embodiments", "example", "specific example", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples.

[0057] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. A gas turbine air supply sealing assembly, characterized in that, Comprising: A turbine disk, within which there is a moving blade air supply passage; A seal ring, which is arranged at a radial interval from the turbine disk on the turbine disk; A sealing assembly, which is arranged between the turbine disk and the seal ring. The sealing assembly, the turbine disk and the seal ring enclose an air supply cavity, and the moving blade air supply passage communicates with the air supply cavity; On the turbine disk, there are a first protrusion and a second protrusion. Both the first protrusion and the second protrusion extend along the axial direction of the turbine disk, and the first protrusion and the second protrusion are arranged at a radial interval on the turbine disk; The sealing assembly includes a first sealing member and a second sealing member. The first sealing member is located between the first protrusion and the seal ring, and the second sealing member is located between the second protrusion and the seal ring; The first protrusion and the second protrusion extend along the left-right direction, and the first protrusion and the second protrusion are arranged at a left-right interval. A first cold air passage is formed in the left-right direction between the first protrusion and the seal ring. The first seal is adapted to seal the first cold air passage. A second cold air passage is formed in the radial direction of the turbine disk between the seal ring and the turbine disk. The second sealing member is adapted to seal the second cold air passage; The dimension of the first protrusion in the axial direction of the turbine disk is smaller than the dimension of the second protrusion in the axial direction of the turbine disk. The sealing performance of the first sealing member for the first cold air passage in the left-right direction is greater than that of the second sealing member in the left-right direction, so that the gas volume in the first cold air passage is less than the gas volume in the second cold air passage. One end of the second cold air passage communicates with the gas in the gas turbine; 2. The gas turbine air supply sealing assembly according to claim 1, characterized in that, Both the first sealing member and the second sealing member include a brush seal and a labyrinth seal, and the brush seal and the labyrinth seal are arranged at an axial interval on the turbine disk; 3. The gas turbine air supply sealing assembly according to claim 1, characterized in that, Inside the seal ring, there is a sealing cavity. One end of the sealing cavity communicates with an external air source, and the other end of the sealing cavity communicates with the air supply cavity; 4. The gas turbine air supply sealing assembly according to claim 2, characterized in that, It further includes a nozzle, which is connected to the seal ring, and the inlet of the nozzle communicates with the sealing cavity, and the outlet of the nozzle communicates with the air supply cavity; 5. The gas turbine air supply sealing assembly according to any one of claims 1-4, characterized in that, The number of the sealing assemblies is multiple, and the multiple sealing assemblies are arranged at a circumferential interval on the turbine disk; 6. A gas turbine, characterized in that, Comprising: An air supply sealing assembly, which is the gas turbine air supply sealing assembly according to any one of claims 1-5; Moving blades, which surround the outside of the turbine disk; Stationary blades, which surround the outside of the seal ring; 7. The gas turbine according to claim 6, characterized in that, It further includes a baffle. The moving blade and the turbine disk are arranged at an interval between the turbine disks to form a root cavity, and the baffle is connected to the turbine disk to seal the root cavity; 8. The gas turbine according to claim 7, characterized in that, The number of the baffles is multiple, and the multiple baffles correspond to the multiple sealing assemblies one by one.

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