Blade profile pre-swirl nozzle system with cooling circuit and gas turbine with same

Abstract

The application discloses a vane type pre-swirl nozzle system with a cooling pipeline and a gas turbine with the same, and the vane type pre-swirl nozzle system with the cooling pipeline comprises a casing, a rotating disc, a stationary disc, a guide vane, a cooling pipeline and a cooling medium driving device. The rotating disc is internally provided with a blade inlet cavity, and the rotating disc is provided with a rotating disc receiving hole in communication with the blade inlet cavity. The main flow channel is formed between the rotating disc and the casing and between the stationary disc and the casing. The disc cavity and the pre-swirl cavity are formed between the rotating disc and the stationary disc, the rotating disc receiving hole is in communication with the pre-swirl cavity, and the stationary disc is provided with a nozzle in communication with the pre-swirl cavity. The guide vane is arranged in the nozzle. The cooling pipeline is arranged in the guide vane. The cooling medium driving device drives the cooling medium in the cooling pipeline to circulate. The vane type pre-swirl nozzle system with the cooling pipeline can reduce the temperature of the cooling airflow, reduce the amount of cooling gas, has the advantages of good cooling effect, improved operation efficiency of the gas turbine and the like.

Description

Technical Field

[0001] This invention relates to the field of gas turbine manufacturing technology, and more specifically, to a blade pre-swirl nozzle system with cooling pipes and a gas turbine having the blade pre-swirl nozzle system with cooling pipes. Background Technology

[0002] Gas turbines are mainly used in power generation and marine applications. In power grid systems dominated by renewable energy, power generation gas turbines need to have the ability to start up quickly and change loads rapidly. In the marine sector, the operating conditions of marine gas turbines often change to meet different speed requirements.

[0003] The pre-swirl nozzle system of a gas turbine supplies cooling airflow to the moving blades through nozzles on the stationary disk. These nozzles guide the cooling airflow into the pre-swirl chamber between the stationary and moving disks. Receiving orifices on the moving disk further guide the cooling airflow to the moving blades to cool them, ensuring the gas turbine's service life and reliability. To improve gas turbine efficiency, the turbine inlet temperature is increasing, making the cooling airflow supply to the moving blades even more crucial.

[0004] In related technologies, the air source for the pre-swirl nozzle of the gas turbine comes from the high-pressure compressor. Taking the F-class gas turbine as an example, the temperature of the air drawn from the high-pressure compressor is usually 300-400℃, and the temperature difference with the surface of the high-pressure turbine blade is about 900℃. Although it is much lower than the surface temperature of the blade, it still has a high temperature and the cooling effect on the surface of the blade is limited. Summary of the Invention

[0005] The present invention aims to at least solve one of the technical problems existing in the prior art. To this end, the present invention proposes an airfoil pre-swirl nozzle system with cooling pipes. This airfoil pre-swirl nozzle system with cooling pipes can reduce the temperature of the cooling airflow, reduce the amount of cooling gas used, and has the advantages of good cooling effect and improved gas turbine operating efficiency.

[0006] The present invention also proposes a gas turbine having the aforementioned gas turbine.

[0007] To achieve the above objectives, according to an embodiment of the first aspect of the present invention, a blade pre-swirl nozzle system with cooling pipes is provided. The blade pre-swirl nozzle system with cooling pipes includes: a casing; a turntable rotatably disposed within the casing with its outer peripheral surface spaced apart from the inner peripheral surface of the casing, the turntable having a moving blade inlet chamber and a turntable receiving hole communicating with the moving blade inlet chamber; and a stationary disc disposed within the casing with its outer peripheral surface spaced apart from the inner peripheral surface of the casing, a main flow channel forming between the turntable and the casing, and between the stationary disc and the casing, and a flow path forming between the turntable and the stationary disc. The device comprises: a disc cavity and a pre-swirl cavity, wherein the pre-swirl cavity is located radially inside the disc cavity of the casing, the turntable receiving hole communicates with the pre-swirl cavity, and the stationary disc is provided with a nozzle communicating with the pre-swirl cavity; a guide vane, wherein the guide vane is disposed within the nozzle; a cooling pipe, wherein the cooling pipe passes through the guide vane; a cooling medium driving device, wherein the cooling medium driving device is connected to the cooling pipe and drives the cooling medium within the cooling pipe to flow; a moving blade, wherein the moving blade is disposed on the outer circumferential surface of the turntable and spaced apart from the casing, and at least a portion of the moving blade extends into the moving blade inlet cavity; and a stationary blade, wherein the stationary blade is disposed on the outer circumferential surface of the stationary disc and connected to the inner circumferential surface of the casing.

[0008] The blade-shaped pre-swirl nozzle system with cooling pipes according to embodiments of the present invention can reduce the temperature of the cooling gas flow and reduce the amount of cooling gas used, and has the advantages of good cooling effect and improved gas turbine operating efficiency.

[0009] In addition, the blade-shaped pre-swirl nozzle system with cooling pipes according to the above embodiments of the present invention may also have the following additional technical features:

[0010] According to one embodiment of the present invention, the air guide vane is provided with a plurality of spaced through holes, and the cooling pipe passes through the plurality of through holes.

[0011] According to one embodiment of the invention, the via extends radially along the casing.

[0012] According to one embodiment of the present invention, there are two vias, namely a first via and a second via, and the cooling pipeline has a first cooling section, a second cooling section and a connecting section. The first cooling section is fitted into the first via and the second cooling section is fitted into the second via. The connecting section is connected to the first cooling section and the second cooling section respectively.

[0013] According to one embodiment of the present invention, the cooling medium driving device is disposed outside the casing, and the cooling pipe extends out of the casing and is connected to the cooling medium driving device.

[0014] According to one embodiment of the present invention, the wind guide blade has a windward convex arc surface, a wind guide convex surface and a wind guide concave surface parallel to the rotation axis. The wind guide convex surface and the wind guide concave surface extend arcuately from both sides of the windward convex arc surface in a direction away from the windward convex arc surface and gradually approach each other.

[0015] According to one embodiment of the present invention, the first through hole is adjacent to the windward convex surface than the second through hole, the first cooling section is connected to the inlet of the cooling pipe, and the second cooling section is connected to the outlet of the cooling pipe.

[0016] According to one embodiment of the present invention, the turntable is provided with an outer sealing edge and an inner sealing edge, and the stationary disk is provided with an outer sealing edge and an inner sealing edge. An outer sealing gap is provided between the outer sealing edge of the turntable and the outer sealing edge of the stationary disk, and the outer sealing gap communicates with the main flow channel and the disk cavity respectively. An inner sealing gap is provided between the inner sealing edge of the turntable and the inner sealing edge of the stationary disk, and the inner sealing gap communicates with the disk cavity and the pre-rotation cavity respectively.

[0017] According to one embodiment of the present invention, there are multiple moving blades, stationary blades and guide vanes, which are arranged at circumferential intervals along the casing.

[0018] According to an embodiment of a second aspect of the invention, a gas turbine is provided, the gas turbine including the blade-shaped pre-swirl nozzle system with cooling lines as described in an embodiment of a first aspect of the invention.

[0019] The gas turbine according to embodiments of the present invention, by utilizing the blade-shaped pre-swirl nozzle system with cooling pipes as described in the first aspect of the present invention, has advantages such as good cooling effect and high operating efficiency.

[0020] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0021] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0022] Figure 1 This is a partial structural schematic diagram of a blade-shaped pre-swirl nozzle system with cooling pipes according to an embodiment of the present invention.

[0023] Figure 2 This is a schematic diagram of the structure of the air guide blade of the blade-shaped pre-swirl nozzle system with cooling pipes according to an embodiment of the present invention.

[0024] Figure 3This is a schematic diagram of the structure of the air guide blade of the blade-shaped pre-swirl nozzle system with cooling pipes according to an embodiment of the present invention.

[0025] Reference numerals: 1. Blade-type pre-swirl nozzle system with cooling pipes; 2. Casing; 3. Main channel; 4. Disc cavity; 5. Pre-swirl cavity; 6. Rotary disc; 7. Rotary disc with cooling pipes. Detailed Implementation

[0026] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0027] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, features defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0028] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0029] The following description, with reference to the accompanying drawings, describes an embodiment of the blade-shaped pre-swirl nozzle system 1 having cooling conduits according to the present invention.

[0030] like Figures 1-3 As shown, the blade-shaped pre-swirl nozzle system 1 with cooling pipes according to an embodiment of the present invention includes a casing 10, a turntable 20, a stationary disc 30, a guide vane 40, a cooling pipe 50, a cooling medium driving device, a moving blade 60, and a stationary blade 70.

[0031] A turntable 20 is rotatably disposed within a casing 10, with its outer circumferential surface spaced apart from the inner circumferential surface of the casing 10. The turntable 20 contains a moving blade inlet chamber 22 and a turntable receiving hole 21 communicating with the moving blade inlet chamber 22. A stationary disc 30 is disposed within the casing 10, with its outer circumferential surface spaced apart from the inner circumferential surface of the casing 10. A main flow channel 11 is formed between the turntable 20 and the casing 10, and between the stationary disc 30 and the casing 10. A disc cavity 12 and a pre-swirl cavity 13 are formed between the turntable 20 and the stationary disc 30. The pre-swirl cavity 13 is located radially within the disc cavity 12 of the casing 10, and the turntable receiving hole 21 communicates with the pre-swirl cavity 13. The stationary disc 30 has a nozzle 31 communicating with the pre-swirl cavity 13. A guide vane 40 is disposed within the nozzle 31. A cooling pipe 50 passes through the guide vane 40. The cooling medium driving device is connected to the cooling pipe 50 and drives the cooling medium to flow within the cooling pipe 50. The moving blade 60 is disposed on the outer peripheral surface of the turntable 20 and spaced apart from the casing 10, with at least a portion of the moving blade 60 extending into the moving blade intake chamber 22. The stationary blade 70 is disposed on the outer peripheral surface of the stationary plate 30 and connected to the inner peripheral surface of the casing 10.

[0032] Specifically, the radial direction of the casing 10, i.e. the inward and outward directions, is shown by arrow A in the figure, and the axial direction of the casing 10 is shown by arrow B in the figure.

[0033] What needs to be understood here is that... Figure 1 Only a schematic diagram of a cross section of the passive adjustment structure 1 for the turbine rim sealing gap is shown in the circumferential direction of the casing 10. The casing 10, turntable 20, and stationary plate 30 are all rotating bodies passing through this cross section.

[0034] According to an embodiment of the present invention, the blade pre-swirl nozzle system 1 with cooling pipes can supply cooling airflow to the pre-swirl chamber 13 by providing a nozzle 31, a turntable receiving hole 21 and a moving blade inlet chamber 22, and guide the cooling airflow in the pre-swirl chamber 13 to the moving blade 60 through the turntable receiving hole 21 and the moving blade inlet chamber 22 to cool the moving blade 60.

[0035] Furthermore, by configuring the air guide vane 40, cooling pipe 50, and cooling medium driving device, the cooling pipe 50 is inserted inside the air guide vane 40, and the cooling medium inside the cooling pipe 50 is driven to flow using the cooling medium driving device. This allows the cooling pipe 50 to cool the air guide vane 40. When the airflow in the nozzle 31 passes through the air guide vane 40, the airflow is cooled, resulting in a greater temperature difference between the cooling airflow exiting the nozzle 31 and the surface of the moving blade 60, thus improving the cooling effect on the moving blade 60.

[0036] In addition, by cooling the guide vanes 40 to reduce the temperature of the cooling gas ejected from the nozzles 31, the flow rate of the cooling gas required to cool the moving blades 60 can be reduced, thereby reducing the flow loss caused by the extraction of air from the compressor and improving the operating efficiency of the gas turbine.

[0037] Therefore, the blade-shaped pre-swirl nozzle system 1 with cooling pipes according to the present invention can reduce the temperature of the cooling airflow and reduce the amount of cooling gas used, and has the advantages of good cooling effect and improved gas turbine operating efficiency.

[0038] The following description, with reference to the accompanying drawings, describes a blade-shaped pre-swirl nozzle system 1 with cooling conduits according to a specific embodiment of the present invention.

[0039] In some specific embodiments of the present invention, such as Figures 1-3 As shown, the blade-shaped pre-swirl nozzle system 1 with cooling pipes according to an embodiment of the present invention includes a casing 10, a turntable 20, a stationary disc 30, a guide vane 40, a cooling pipe 50, a moving blade 60, and a stationary blade 70.

[0040] Specifically, such as Figures 1-3 As shown, the air guide vane 40 is provided with multiple spaced-apart through holes, through which the cooling pipe 50 passes. This increases the contact area between the cooling pipe 50 and the air guide vane 40, improves the cooling effect of the cooling pipe 50 on the air guide vane 40, and further enhances the cooling effect on the cooling gas passing through the air guide vane 40.

[0041] More specifically, such as Figure 1 and Figure 2 As shown, the through hole extends radially along the casing 10. This facilitates the placement of the through hole and avoids interfering with the air guiding effect of the guide vanes 40.

[0042] Optionally, such as Figures 1-3As shown, there are two through holes, namely a first through hole 41 and a second through hole 42. The cooling pipe 50 has a first cooling section, a second cooling section, and a connecting section. The first cooling section fits into the first through hole 41, and the second cooling section fits into the second through hole 42. The connecting section is connected to both the first and second cooling sections. In other words, the cooling pipe 50 can be constructed as a U-shaped pipe. This facilitates the installation of the cooling pipe 50.

[0043] In other embodiments, the first cooling section and the second cooling section may also be connected through a gas storage chamber.

[0044] Furthermore, such as Figure 1 As shown, the cooling medium drive device is located outside the casing 10, and the cooling pipe 50 extends out of the casing 10 and is connected to the cooling medium drive device. This avoids the high-temperature environment inside the casing 10 from affecting the operation of the cooling medium drive device.

[0045] Advantageously, such as Figure 3 As shown, the guide vane 40 has a convex arc surface 46, a guide convex surface 47, and a guide concave surface 48 parallel to the rotation axis. The guide convex surface 47 and the guide concave surface 48 extend arcuately from both sides of the convex arc surface 46 away from the convex arc surface 46 and gradually approach each other. Specifically, the cross-section of the guide vane 40 perpendicular to the rotation axis can be shaped like a magatama. This can improve the guiding effect of the guide vane 40 on the airflow.

[0046] More advantageously, such as Figure 3 As shown, the first through-hole 41 is adjacent to the windward convex surface 46 compared to the second through-hole 42. The first cooling section is connected to the inlet of the cooling pipe 50, and the second cooling section is connected to the outlet of the cooling pipe 50. This allows the cooling medium to first pass through the windward portion of the guide vane 40, and then through the guiding portion of the guide vane 40, thereby further improving the cooling effect on the cooling airflow.

[0047] Figure 1 An adjustable exit angle blade pre-swirl nozzle system 1 is shown according to some examples of the present invention. For example... Figure 1 As shown, the turntable 20 is provided with an outer sealing edge 23 and an inner sealing edge 24, and the stationary plate 30 is provided with an outer sealing edge 34 and an inner sealing edge 35. An outer sealing gap exists between the outer sealing edge 23 and the outer sealing edge 34, which communicates with the main flow channel 11 and the plate cavity 12, respectively. An inner sealing gap exists between the inner sealing edge 24 and the inner sealing edge 35, which communicates with the plate cavity 12 and the pre-swirl cavity 13, respectively. This design reduces the intrusion of high-temperature combustion gases from the main flow channel 11 into the plate cavity 12 and the pre-swirl cavity 13 while ensuring the turntable 20 can rotate.

[0048] Specifically, there are multiple moving blades 60, stationary blades 70, and guide vanes 40 arranged at circumferential intervals along the casing 10. This improves the airflow guidance effect.

[0049] Those skilled in the art will understand that the bending direction of the adjusting blade 40 is related to the rotation direction of the turntable, and can be set according to actual needs.

[0050] Specifically, based on the temperature at the combustion chamber outlet, the temperature upstream of the guide vane 40 is determined, and the minimum enthalpy drop required for cooling the moving blade 60 during variable load processes is calculated using a formula. The temperature of the cold air in the compressor extraction line and the temperature at the inlet of the cooling medium channel are measured, and the heat transfer coefficient between the jet inside the nozzle 31 and the cooled guide vane 40 is obtained using a formula, thus yielding the functional relationship between the cold air inlet temperature, the nozzle inlet temperature, and the nozzle outlet temperature. Based on this, the minimum amount of cold air required to meet the cooling requirements is determined. The valve opening in the extraction line upstream of the nozzle 31 is reduced to decrease the amount of cold air used while still meeting cooling requirements, thereby improving gas turbine efficiency. Calculations show that reducing the temperature of the pre-swirling jet by 20K can reduce the amount of cold air by approximately 3.8%, and reducing it by 50K can reduce it by approximately 7.8%.

[0051] The following describes a gas turbine according to an embodiment of the present invention. The gas turbine according to an embodiment of the present invention includes a blade-shaped pre-swirl nozzle system 1 with cooling pipes according to the above-described embodiment of the present invention.

[0052] The gas turbine according to the embodiments of the present invention has advantages such as good cooling effect by utilizing the blade-shaped pre-swirl nozzle system 1 with cooling pipes according to the above embodiments of the present invention.

[0053] Other configurations and operations of the gas turbine according to embodiments of the present invention are known to those skilled in the art and will not be described in detail here.

[0054] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0055] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A blade-shaped pre-swirl nozzle system with cooling pipes, characterized in that, include: Casing; A turntable is rotatably disposed within the casing, with its outer peripheral surface spaced apart from the inner peripheral surface of the casing. The turntable has a moving blade air intake chamber and a turntable receiving hole that communicates with the moving blade air intake chamber. A stationary disc is disposed within the housing, with its outer circumferential surface spaced apart from the inner circumferential surface of the housing. A main channel is formed between the turntable and the housing, and between the stationary disc and the housing. A disc cavity and a pre-rotation cavity are formed between the turntable and the stationary disc. The pre-rotation cavity is located radially inside the disc cavity of the housing. The turntable receiving hole communicates with the pre-rotation cavity. A nozzle communicating with the pre-rotation cavity is provided on the stationary disc. A guide vane, wherein the guide vane is disposed within the nozzle; Cooling pipes, which are installed inside the air guide vanes; A cooling medium driving device, wherein the cooling medium driving device is connected to the cooling pipeline and drives the cooling medium to flow in the cooling pipeline; A moving blade is disposed on the outer peripheral surface of the turntable and spaced apart from the casing, and at least a portion of the moving blade extends into the moving blade intake chamber. A stationary blade is disposed on the outer peripheral surface of the stationary plate and connected to the inner peripheral surface of the casing.

2. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 1, characterized in that, The air guide vane is provided with multiple spaced through holes, and the cooling pipe passes through the multiple through holes.

3. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 2, characterized in that, The via extends radially along the casing.

4. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 2, characterized in that, There are two vias, namely a first via and a second via. The cooling pipe has a first cooling section, a second cooling section and a connecting section. The first cooling section fits into the first via and the second cooling section fits into the second via. The connecting section is connected to the first cooling section and the second cooling section respectively.

5. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 1, characterized in that, The cooling medium drive device is located outside the casing, and the cooling pipe extends out of the casing and is connected to the cooling medium drive device.

6. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 4, characterized in that, The wind guide blade has a windward convex arc surface, a wind guide convex surface, and a wind guide concave surface parallel to the rotation axis. The wind guide convex surface and the wind guide concave surface extend in an arc shape from both sides of the windward convex arc surface away from the windward convex arc surface and gradually approach each other.

7. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 6, characterized in that, The first through hole is closer to the windward convex surface than the second through hole. The first cooling section is connected to the inlet of the cooling pipe, and the second cooling section is connected to the outlet of the cooling pipe.

8. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 1, characterized in that, The turntable is provided with an outer sealing edge and an inner sealing edge, and the stationary plate is provided with an outer sealing edge and an inner sealing edge. There is an outer sealing gap between the outer sealing edge of the turntable and the outer sealing edge of the stationary plate. The outer sealing gap is connected to the main channel and the plate cavity respectively. There is an inner sealing gap between the inner sealing edge of the turntable and the inner sealing edge of the stationary plate. The inner sealing gap is connected to the plate cavity and the pre-rotation cavity respectively.

9. The blade-shaped pre-swirl nozzle system with cooling pipes according to claim 1, characterized in that, The moving blades, the stationary blades, and the guide blades are all multiple and are spaced apart along the circumference of the casing.

10. A gas turbine, characterized in that, Includes a blade-shaped pre-swirl nozzle system with cooling conduits according to any one of claims 1-9.

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