Turbine moving blade cooling structure with self-cleaning capacity and turbine moving blade

Abstract

The invention belongs to the field of turbine blades, and discloses a turbine moving blade cooling structure with self-cleaning capacity and a turbine moving blade, the turbine moving blade cooling structure comprises a U-shaped cooling channel and a rotational flow cavity; the U-shaped cooling channel is arranged from the blade bottom to the blade top of the turbine rotor plate; a plurality of turbulent flow ribs are arranged on the pressure surface of the U-shaped cooling channel to form an inter-rib area; the rotational flow cavity is arranged at the front edge position of the turbine rotor plate and is communicated with the U-shaped cooling channel through the nozzle; the inlet end of the nozzle is communicated with the turbulent flow rib, and the outlet end is communicated with the air inlet of the rotational flow cavity; the rotational flow cavity is gradually converged from bottom to top, and a contraction section is formed at the top; a blade top air film hole is formed in the top of the contraction section and is used for discharging particulate pollutants from the turbine rotor and cooling the blade; by the adoption of the structure, the particulate pollutant self-cleaning function of the cooling channel in the blade is achieved, particulate pollutants are effectively prevented from entering the turbine rotor through a secondary air system and forming sediments on the inner wall face of the cooling channel, and the cooling effect of the interior of the turbine rotor is improved.

Description

Technical Field

[0001] The present invention belongs to the field of turbine blades, and in particular relates to a turbine blade cooling structure and a turbine blade with self-cleaning capability. Background Art

[0002] In the process of pursuing higher cycle efficiency for aircraft engines, the temperature at the turbine inlet continues to rise, even exceeding the heat resistance limit of the metal material of the turbine blades. In order to prevent the blades from being burned by high-temperature airflow, a large number of cooling structures are usually arranged inside the blades, including serpentine channels, impact holes, air film holes, spoiler ribs and spoiler columns. Through these structures, the low-temperature cold air from the compressor can take away the heat by forced convection heat exchange, thereby protecting the blades. The normal operation of aircraft engines is closely related to their own structure and operating environment. Just as long-term unprotected exposure to particulate pollutants in humans can cause particulate pollutants to invade the respiratory system and cause obstructive pulmonary disease (OPD), the long-term operation of aircraft engines in an environment with high particulate pollutant concentrations will also seriously damage their gas-thermal performance.

[0003] Particulate pollutants will enter the turbine rotor through the secondary air system. On the one hand, due to the low temperature and the interaction of multiple cooling structures, particulate pollutants form a unique deposition mechanism, making it difficult to use mature high-temperature deposition theories to predict their harm. On the other hand, the narrow internal space amplifies the impact of particulate deposits on blade performance and is difficult to remove. For the ribbed cooling channel inside the turbine rotor where particulate pollutants first arrive, particulate pollutants will adhere to the inner wall of the cooling channel, and their low thermal conductivity prevents the cold air from taking away the heat in the blade. In addition, deposits will accumulate in the corner area of ​​the rib wall, thereby weakening the enhanced heat exchange effect of the spoiler ribs. In severe cases, the deposits will block the cooling channel and increase flow losses.

[0004] It can be seen that in the existing internal structure of the turbine blade, particulate pollutants can easily enter the interior of the turbine blade through the secondary air system and adhere to the inner wall of the cooling channel to form deposits, which weakens the cooling effect inside the turbine blade and increases flow losses. Summary of the invention

[0005] The present invention provides a turbine blade cooling structure and a turbine blade with self-cleaning capability, so as to solve the technical problem that particulate pollutants in the internal structure of the existing turbine blade can easily enter the interior of the turbine blade through the secondary air system, and adhere to the inner wall of the cooling channel to form deposits, thereby weakening the cooling effect inside the turbine blade and causing increased flow losses.

[0006] In order to achieve the above object, the present invention adopts the following technical contents: A turbine blade cooling structure with self-cleaning capability, wherein the turbine blade cooling structure is arranged inside the turbine blade and comprises a U-shaped cooling channel and a swirl cavity; The U-shaped cooling channel is arranged from the blade bottom to the blade top of the turbine rotor blade; A plurality of spoiler ribs are arranged on the pressure surface of the U-shaped cooling channel to form an inter-rib area, and the inter-rib area is used to guide the particulate pollutants; The swirl chamber is arranged at the leading edge of the turbine rotor and is connected to the U-shaped cooling channel through a nozzle; The inlet end of the nozzle is communicated with the spoiler rib, and the outlet end is communicated with the air inlet of the swirl chamber; The swirl chamber gradually converges from bottom to top and forms a contraction section at the top; A blade tip air film hole is opened at the top of the contraction section to discharge particulate pollutants from the turbine blades and cool the turbine blades.

[0007] Furthermore, a plurality of spoiler ribs are arranged on the suction surface of the U-shaped cooling channel; and the inlet end of the nozzle is communicated with the spoiler ribs located on the pressure surface of the U-shaped cooling channel.

[0008] Furthermore, the spoiler ribs are arranged at an angle; the spoiler ribs on the pressure inlet air flow path of the U-shaped cooling channel point toward the swirl chamber along the flow direction of the cold air, and the angle between the extension direction of the spoiler ribs and the flow direction of the cold air in the cold air flow path is between 20° and 70°.

[0009] Furthermore, the nozzle is arranged at an angle, and the angle of the nozzle is consistent with the angle of the corresponding spoiler rib.

[0010] Furthermore, the nozzle is tangentially connected to the ribbed surface on the pressure surface side of the U-shaped cooling channel.

[0011] Furthermore, the nozzle is tangentially connected to the swirl chamber.

[0012] Furthermore, the nozzle adopts a square structure and is provided in plurality, and each nozzle is arranged between every two adjacent spoiler ribs.

[0013] Furthermore, every two nozzles are separated by a partition; the flow direction dimension of the partition is the same as the flow direction cross section of the corresponding spoiler rib, and the height of the partition is 0.5 to 3 times the rib height.

[0014] Furthermore, the nozzles are arranged one by one from between the first spoiler rib and the second spoiler rib of the air intake path, and the number is 4 to 7.

[0015] A turbine rotor blade comprises the above-mentioned turbine rotor blade cooling structure with self-cleaning capability.

[0016] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a turbine blade cooling structure with self-cleaning capability. The cooling structure is provided with a U-shaped cooling channel and a swirl cavity inside the turbine blade. The U-shaped cooling channel is connected with the swirl cavity through a nozzle and spoiler ribs arranged on the pressure surface of the U-shaped cooling channel. The swirl cavity is designed to gradually converge from bottom to top and form a contraction section at the top, and finally discharge particulate pollutants from the turbine blade through the blade top air film hole. The structure can make the particulate pollutants deflect to the opposite side of the blade rotation direction under the driving of the Coriolis force and gather in the inter-rib area on the pressure surface side. Under the guidance of the inclined ribs, particulate pollutants enter the swirl chamber through the nozzle; the cold air containing particulate pollutants is injected into the swirl chamber tangentially, and a swirl is formed therein that spirals forward toward the blade tip, bringing a larger wall tangential velocity to the inner wall of the swirl chamber, which not only enhances the heat exchange and cooling capacity of the cold air on the leading edge of the blade, but also reduces the possibility of particulate pollutants being deposited in the swirl chamber; the top of the swirl chamber gradually converges at the blade tip to form a contraction section, and finally discharges the particulate pollutants from the blade through the blade tip air film hole, realizing the self-cleaning function of the particulate pollutants in the cooling channel inside the blade. The use of this structure can effectively prevent particulate pollutants from entering the turbine rotor through the secondary air system and forming deposits on the inner wall of the cooling channel, thereby improving the cooling effect, and can also use the centrifugal force generated by the swirl to promote the discharge of particulate pollutants, thereby reducing the impact of particulate deposits on blade performance, reducing flow losses, and enhancing the reliability and durability of the turbine rotor.

[0017] Preferably, in the present invention, spoiler ribs are also provided on the suction surface of the U-shaped cooling channel. This design further enhances the turbulence effect in the cooling channel, improves the cooling efficiency, and helps to guide the particulate pollutants more evenly to the vortex chamber for discharge.

[0018] Preferably, in the present invention, the spoiler ribs are arranged at an angle and form an angle of 20° to 70° with the flow direction of the cold air in the cold air flow path. This design can more effectively guide the flow of cold air, improve the heat exchange efficiency, and help guide the particulate pollutants to the vortex chamber in a specific direction, thereby enhancing the self-cleaning effect.

[0019] Preferably, in the present invention, the nozzle is arranged at an angle and is consistent with the inclination direction of the corresponding connected spoiler ribs. This design reduces flow losses on the one hand, and makes it easier to form a cold air vortex pointing to the blade top direction in the vortex chamber on the other hand. This design can ensure that the cold air enters the nozzle smoothly from the spoiler ribs and flows along the tangential direction of the vortex chamber, forming a strong vortex effect, which is conducive to the discharge of particulate pollutants.

[0020] Preferably, in the present invention, the nozzle is tangentially connected to the ribbed surface on the pressure surface side of the U-shaped cooling channel, which reduces the flow loss of the cold air and makes it easier to guide the particulate pollutants into the swirl chamber.

[0021] Preferably, in the present invention, the nozzle is tangentially connected to the swirl chamber so that the cold air is tangentially injected into the swirl chamber and forms a swirl therein. This design can ensure that a strong swirl effect is formed when the cold air enters the swirl chamber from the nozzle, which helps to discharge particulate pollutants from the inside of the blade and improve the reliability and durability of the turbine blade.

[0022] Preferably, in the present invention, the nozzle adopts a square structure and is provided in plurality, with each nozzle being arranged between every two adjacent spoiler ribs. This design can more evenly distribute the cold air flow, improve cooling efficiency, and help guide particulate pollutants from multiple directions to the vortex chamber for discharge.

[0023] Preferably, in the present invention, every two nozzles are separated by a partition, the flow direction dimension of the partition is the same as the flow direction cross-section of the corresponding spoiler rib, and the height of the partition is 0.5 to 3 times the rib height; the presence of the partition increases the stability of the structure and reduces the probability of particles escaping from the vortex chamber.

[0024] Preferably, in the present invention, the nozzles are arranged one by one between the first spoiler rib and the second spoiler rib in the air intake path, with a number of 4 to 7; in this way, the particulate pollutants begin to be separated in the area between the first spoiler rib and the second spoiler rib, thereby minimizing the probability of the particulate pollutants being deposited in the internal cooling channel; this design can ensure that the cold air forms a continuous turbulence effect in the cooling channel, improve the heat exchange efficiency, and help to more effectively guide the particulate pollutants to the vortex chamber for discharge; at the same time, a reasonable number of nozzles can also ensure a balance between the cooling effect and the self-cleaning ability.

[0025] The present invention also provides a turbine blade, including the above-mentioned turbine blade cooling structure with self-cleaning ability. The turbine blade utilizes the relative position relationship of the internal ribbed U-shaped cooling channel, the leading edge swirl cavity and the nozzle. Under the guidance of the rotating and inclined spoiler ribs, the inertia difference between the particulate pollutants and the cold air is utilized to separate the two and discharge the particulate pollutants out of the turbine blade, thereby realizing the self-cleaning function of the particulate pollutants inside the turbine blade. The turbine blade has a simple structure, does not require special processing and additional cold air consumption, has a strong self-cleaning ability and a good cooling effect, and has a good value for promotion and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 A schematic structural diagram of a turbine blade cooling structure with self-cleaning capability provided by an embodiment of the present invention; Figure 2A top view of a turbine blade cooling structure with self-cleaning capability provided by an embodiment of the present invention; Figure 3 Migration trajectories of particulate contaminants in a conventional internal cooling channel with dust removal holes provided for an embodiment of the invention; Figure 4 The migration trajectory of particulate pollutants in the internal cooling channel of the turbine blade cooling structure with self-cleaning capability provided by the embodiment of the invention; Figure 5 The concentration reduction of particulate pollutants and the consumption of cold air in the channel provided by the embodiment of the invention; Figure 6 A surface Nusselt number distribution of an internal cooling channel of a turbine blade cooling structure with self-cleaning capability provided in an embodiment of the invention.

[0027] Reference numerals: 1. U-shaped cooling channel; 2. spoiler ribs; 3. nozzle; 4. swirl chamber; 5. contraction section; 6. blade tip air film hole; 7. turbine rotor. DETAILED DESCRIPTION

[0028] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention more clearly understood, the present invention is further described in detail in the following specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0029] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0030] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0031] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0032] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0033] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0034] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] Example 1 As mentioned in the background technology, particulate pollutants will enter the interior of the turbine rotor through the secondary air system. On the one hand, due to the low temperature and the interaction of multiple cooling structures, particulate pollutants form a unique deposition mechanism, making it difficult to use mature high-temperature deposition theory to predict its harm. On the other hand, the narrow internal space amplifies the impact of particulate deposits on blade performance and is difficult to remove. For the ribbed cooling channel inside the turbine rotor where particulate pollutants first arrive, particulate pollutants will adhere to the inner wall of the cooling channel, and their low thermal conductivity prevents the cold air from taking away the heat in the blade. In addition, deposits will accumulate in the corner area of ​​the rib wall, thereby weakening the enhanced heat exchange effect of the spoiler ribs. In severe cases, the deposits will block the cooling channel and increase flow losses.

[0036] In order to solve the above problems, the present embodiment provides a turbine blade cooling structure with self-cleaning capability. The turbine blade cooling structure rearranges the relative position relationship of the ribbed U-shaped cooling channel, the swirl chamber and the nozzle connecting the two inside the turbine blade, so that the internal cooling structure of the turbine blade has the function of self-cleaning of particulate contaminants.

[0037] like Figure 1As shown, this embodiment provides a turbine blade cooling structure with self-cleaning capability, which is arranged inside the turbine blade 7 and specifically includes the following structure: The U-shaped cooling channel 1 and the swirl chamber 4; wherein the U-shaped cooling channel 1 is arranged from the blade bottom to the blade top of the turbine blade 7, and is also located between the pressure surface and the suction surface of the turbine blade 7; the U-shaped cooling channel 1 also has a pressure surface side and a suction surface side; a plurality of spoiler ribs 2 are arranged on the pressure surface of the U-shaped cooling channel 1, and the plurality of spoiler ribs 2 form an inter-rib area; The swirl chamber 4 is arranged at the leading edge of the turbine rotor 7 where the heat load of the blades is the largest; The inlet end of the nozzle 3 is connected to the outlet end of the corresponding spoiler rib 2, and the outlet end of the nozzle 3 is connected to the air inlet of the swirl chamber 4, that is, the nozzle 3 connects the swirl chamber 4 with the U-shaped cooling channel 1; The swirl chamber 4 gradually converges from bottom to top, that is, it is gradually contracted from top to bottom, and finally forms a contraction section 5 at its top, and a blade top film hole 6 is opened at the top of the contraction section 5, and finally the particulate pollutants are discharged from the turbine blade 7 through the blade top film hole 6.

[0038] The cooling structure of the present invention is provided with a U-shaped cooling channel 1 and a swirl cavity 4 inside the turbine rotor, and the U-shaped cooling channel 1 is connected with the swirl cavity 4 through the nozzle 3 and the spoiler ribs 2 arranged on the pressure surface of the U-shaped cooling channel 1; the design of the swirl cavity 4 gradually converges from bottom to top, and forms a contraction section 5 at the top, and finally discharges the particle pollutants from the turbine rotor 7 through the blade top air film hole 6; the present structure can make the particle pollutants deflect to the opposite side of the rotation direction under the driving of the Coriolis force and gather in the inter-rib area on the pressure surface side; under the guidance of the spoiler ribs 2, the particle The pollutants enter the swirl chamber through the nozzle 3; the cold air containing particulate pollutants is injected into the swirl chamber 4 tangentially, and a swirl is formed therein that spirals forward toward the blade tip, which brings a larger wall tangential velocity to the inner wall of the swirl chamber, which not only enhances the heat exchange and cooling capacity of the cold air on the leading edge of the blade, but also reduces the possibility of particulate pollutants being deposited in the swirl chamber; the top of the swirl chamber 4 gradually converges at the blade tip to form a contraction section 5, and finally discharges the particulate pollutants from the blade through the blade tip air film hole 6, realizing the self-cleaning function of the particulate pollutants in the cooling channel inside the blade. The use of this structure can effectively prevent particulate pollutants from entering the turbine rotor through the secondary air system and forming deposits on the inner wall of the cooling channel, thereby improving the cooling effect, and can also use the centrifugal force generated by the swirl to promote the discharge of particulate pollutants, thereby reducing the impact of particulate deposits on blade performance, reducing flow losses, and enhancing the reliability and durability of the turbine rotor.

[0039] Example 2 Another example Figure 1As shown, this embodiment also provides a turbine blade cooling structure with self-cleaning capability, which is further optimized and improved on the basis of embodiment 1, as follows: The turbine blade cooling structure includes a U-shaped cooling channel 1 with spoiler ribs 2 arranged inside the turbine blade 7 and a swirl chamber 4 located at the leading edge of the blade, and the two are tangentially connected through a nozzle 3 arranged on the pressure surface side of the U-shaped cooling channel 1; the top of the swirl chamber 4 gradually converges to form a contraction section 5, and is connected to the blade top air film hole 6.

[0040] In this embodiment, the turbine rotor 7 rotates together with the cooling structure inside it, and the nozzle 3 is arranged on the pressure surface of the U-shaped cooling channel 1 on the side opposite to the rotation direction.

[0041] In this embodiment, the swirl chamber 4 is arranged at the leading edge of the turbine blade 7 where the heat load is the largest, and the flow path of the U-shaped cooling channel 1 close to the leading edge is set as the air intake side, and the two are connected through the nozzle 3.

[0042] In this embodiment, the spoiler ribs 2 in the U-shaped cooling channel 1 are arranged at an angle, pointing toward the swirl chamber 4 along the cold air flow direction in the inlet air flow path, and the angle between the extension direction of the spoiler ribs 2 and the flow direction of the cold air in the cold air flow path is between 20° and 70°.

[0043] In this embodiment, the nozzle 3 is tangentially connected to the ribbed surface of the U-shaped cooling channel 1 on the pressure surface side of the U-shaped cooling channel 1, which reduces the flow loss of the cold air and makes it easier to guide the particulate pollutants into the swirl chamber 4.

[0044] In this embodiment, the nozzle 3 is tangentially connected to the swirl chamber 4 so that the cold air is tangentially injected into the swirl chamber 4 and forms a swirl therein.

[0045] In this embodiment, the nozzle 3 is square, and its inclination direction is consistent with the spoiler rib 2.

[0046] In this embodiment, the nozzles 3 are not continuous but separated by a plurality of partitions. The flow direction size and position of the partitions are consistent with the flow direction cross-section of the corresponding inclined spoiler ribs 2 , and the height is 0.5 to 3 times that of the spoiler ribs 2 .

[0047] In this embodiment, the top of the swirl cavity 4 at the leading edge of the blade, namely the contraction section 5 gradually contracts to the size of the blade top air film hole 6 .

[0048] In this embodiment, the nozzles 3 are arranged one by one from between the first spoiler rib 2 and the second spoiler rib 2 in the air intake path, and the number of the nozzles 3 is between 4 and 7.

[0049] It can be seen that the turbine blade cooling structure with self-cleaning capability provided in this embodiment has the following beneficial effects: First, the cooling channel and swirl structure are common cooling structures inside the turbine blades. Therefore, this embodiment does not need to redesign a new cooling structure or increase additional cooling air consumption. The particulate contaminant self-cleaning function can be added by redesigning the relative position relationship of each cooling structure.

[0050] Second, this embodiment utilizes rotation and spoiler ribs to induce secondary flow, and guides particulate pollutants having a higher Stokes number than the cold air to a specific area through inertia, thereby facilitating separation.

[0051] Third, for the particulate pollutants that have just entered the internal U-shaped cooling channel, this embodiment begins to separate them in the area between the first and second spoiler ribs, thereby reducing the probability of the particulate pollutants being deposited in the internal cooling channel as much as possible.

[0052] Fourth, by adjusting the size of the blade tip air film holes, the efficiency of blade leading edge swirl cooling, blade tip air film cooling and particle pollutant separation can be increased or decreased at the same time.

[0053] Fifth, the swirl formed by the cold air in the swirl cavity gives the inner wall of the swirl cavity at the leading edge of the blade a higher near-wall tangential velocity, reducing the possibility of particle deposition therein.

[0054] The turbine blade cooling structure with self-cleaning capability provided by this embodiment is explained in more detail below with reference to the accompanying drawings: like Figure 2 As shown, the leading edge of the turbine blade 7 facing the high-temperature combustion gas is usually subjected to a high heat load, and a swirl chamber 4 is usually arranged here to protect the leading edge through swirl cooling. The nozzle 3 is tangentially connected to the internal cooling channel 1 to minimize flow loss; the nozzle 3 is also tangentially connected to the swirl chamber 4, so that the cold air forms a swirl in the swirl chamber 4 pointing to the blade top air film hole 6, cooling the leading edge of the blade and reducing the deposition of particulate pollutants inside the swirl chamber 4.

[0055] like Figure 3 As shown, Figure 3 The migration trajectory of particulate pollutants in the traditional internal cooling channel with dust removal holes. Under the influence of the inclined ribs, a pair of vortices with opposite rotation directions are formed in the internal cooling channel, carrying particulate pollutants to hit the channel wall multiple times, increasing the possibility of particulate pollutants being deposited in the cooling channel; it can be observed at the dust removal holes on the blade top that only a very small number of small-sized particles will be discharged from the blade with the cold air, while most of the particulate pollutants are still retained in the internal cooling channel.

[0056] like Figure 4 As shown, Figure 4The figure shows the migration trajectory of particulate contaminants in the internal cooling channel with a particle self-cleaning cooling structure. After the particulate contaminants enter the internal U-shaped cooling channel 1, they are continuously separated and enter the swirl chamber 4 starting from the first nozzle 3, and then spirally move toward the blade tip under the influence of the cold air swirl. Finally, they converge at the contraction section 5 at the top of the swirl chamber 4 and are discharged from the turbine blade 7 through the blade tip air film hole 6, thus realizing the self-cleaning function of the particulate contaminants.

[0057] like Figure 5 As shown, Figure 5 When the diameter of the blade top air film hole 5 is equal to that of the conventional dust removal hole, the concentration of particulate pollutants in the U-shaped cooling channel 1 decreases and the cooling air consumption is determined. Through quantitative analysis, it can be found that the particle separation efficiency of the conventional dust removal hole is very low, and 99.17% of the particulate pollutants remain in the cooling channel after passing through the dust removal hole, with almost no change. When the turbine blade 7 adopts a turbine blade cooling structure with self-cleaning ability, the concentration of particulate pollutants in the U-shaped cooling channel 1 can be reduced to 52.33% with only a 1% increase in cooling air consumption, providing a significant self-cleaning effect of particulate pollutants for the internal cooling channel.

[0058] like Figure 6 As shown, Figure 6 The surface Nusselt number distribution of the internal cooling channel with a particle self-cleaning cooling structure shows that the flow paths of the ribbed U-shaped cooling channel 1 away from the side of the swirl chamber 4 and the nozzle 3 become high heat exchange areas, and obvious cold air swirl trajectories are observed on the surface of the swirl chamber 4; the tangentially incident cold air forms a swirl inside the swirl chamber 4, and the protection ability of the cold air inside the leading edge of the blade is enhanced with a larger near-wall tangential velocity; in addition, by increasing the blade top air film hole 6, the amount of cold air entering the swirl chamber 4 can be increased, thereby increasing the cooling capacity of the leading edge swirl chamber 4.

[0059] The present invention also provides a turbine blade, including the above-mentioned turbine blade cooling structure with self-cleaning ability. The turbine blade utilizes the relative position relationship of the internal ribbed U-shaped cooling channel, the leading edge swirl cavity and the nozzle. Under the guidance of the rotating and inclined spoiler ribs, the inertia difference between the particulate pollutants and the cold air is utilized to separate the two and discharge the particulate pollutants out of the turbine blade, thereby realizing the self-cleaning function of the particulate pollutants inside the turbine blade. The turbine blade has a simple structure, does not require special processing and additional cold air consumption, has a strong self-cleaning ability and a good cooling effect, can be effectively applied to aircraft engines or heavy-duty gas turbines, and has good promotion and application value.

[0060] In summary, the present invention provides a turbine blade cooling structure and a turbine blade with self-cleaning capability, which have the following advantages over the existing turbine blade cooling structure: The turbine blade cooling structure includes a U-shaped cooling channel with spoiler ribs arranged inside the turbine blade and a leading edge swirl cavity, which are connected by a nozzle. The top of the swirl cavity gradually shrinks and is connected to the blade top air film hole. In the rotating blade, the particulate pollutants enter the ribbed U-shaped channel and gather on the opposite side of the rotation direction, and enter the nozzle on the pressure surface under the guidance of the inclined spoiler ribs. Then the cold air carries the particulate pollutants into the leading edge swirl cavity; the tangentially incident cold air forms a swirl in it, which increases the airflow shear force near the wall of the cavity, on the one hand, strengthening the convective heat exchange of the leading edge, and on the other hand, preventing the particulate pollutants from forming deposits in the swirl cavity. The particles finally gather at the top of the swirl cavity and are discharged through the blade top air film hole. The present invention realizes the self-cleaning function of the particulate pollutants inside the turbine rotor by designing the arrangement of the ribbed U-shaped cooling channel and the leading edge vortex cavity inside the turbine rotor, utilizing the inertia difference between particles and cold air to separate the two and discharge the particulate pollutants out of the turbine rotor. The present invention has a simple structure, does not require special processing and additional cold air consumption, and can be achieved by adopting the currently commonly used turbine rotor cooling structure processing technology and conventional vortex cooling cold air consumption. When using the present invention, a trade-off can be made among the cold air consumption, the cold air cleanliness requirement and the heat exchange requirement of the blade leading edge, and the appropriate nozzle opening size, the number of nozzles and the size of the dust removal hole on the blade top can be selected.

[0061] The above embodiment is only one of the implementation methods that can realize the technical solution of the present invention. The scope of protection claimed by the present invention is not limited only to this embodiment, but also includes changes, replacements and other implementation methods that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention.

Claims

1. A turbine blade cooling structure with self-cleaning capability, characterized in that: The turbine rotor cooling structure is arranged inside the turbine rotor (7), and comprises a U-shaped cooling channel (1) and a swirl cavity (4); The U-shaped cooling channel (1) is arranged from the blade bottom to the blade top of the turbine rotor (7); A plurality of spoiler ribs (2) are arranged on the pressure surface of the U-shaped cooling channel (1) to form an inter-rib area, wherein the inter-rib area is used to guide the particle pollutants; The swirl chamber (4) is arranged at the leading edge of the turbine rotor (7) and is connected to the U-shaped cooling channel (1) through a nozzle (3); The inlet end of the nozzle (3) is in communication with the spoiler rib (2), and the outlet end is in communication with the air inlet of the swirl chamber (4); The swirl chamber (4) gradually converges from bottom to top and forms a contraction section (5) at the top; A blade tip air film hole (6) is provided at the top of the contraction section (5) for discharging particulate pollutants from the turbine rotor (7) and cooling the turbine rotor (7).

2. The turbine blade cooling structure with self-cleaning capability according to claim 1, characterized in that: A plurality of spoiler ribs (2) are provided on the suction surface of the U-shaped cooling channel (1); and an inlet end of the nozzle (3) is in communication with the spoiler ribs (2) located on the pressure surface of the U-shaped cooling channel (1).

3. The turbine blade cooling structure with self-cleaning capability according to claim 1 or 2, characterized in that: The spoiler ribs (2) are all arranged obliquely; the spoiler ribs (2) located on the pressure inlet air flow path of the U-shaped cooling channel (1) point toward the swirl cavity (4) along the cold air flow direction, and the angle between the extension direction of the spoiler ribs (2) and the flow direction of the cold air in the cold air flow path is between 20° and 70°.

4. The turbine blade cooling structure with self-cleaning capability according to claim 3, characterized in that: The nozzle (3) is arranged in an inclined manner and is consistent with the inclination direction of the correspondingly connected spoiler rib (2).

5. The turbine blade cooling structure with self-cleaning capability according to claim 1, characterized in that: The nozzle (3) is tangentially connected to the ribbed surface on the pressure surface side of the U-shaped cooling channel (1).

6. The turbine blade cooling structure with self-cleaning capability according to claim 1, characterized in that: The nozzle (3) is tangentially connected to the swirl chamber (4).

7. The turbine blade cooling structure with self-cleaning capability according to claim 1, characterized in that: The nozzle (3) adopts a square structure and is provided in plurality, with each nozzle (3) being arranged between every two adjacent spoiler ribs (2).

8. The turbine blade cooling structure with self-cleaning capability according to claim 7, characterized in that: Every two nozzles (3) are separated by a partition; the flow direction dimension of the partition is the same as the flow direction cross section of the corresponding spoiler rib (2), and the height of the partition is 0.5 to 3 times the rib height.

9. The turbine blade cooling structure with self-cleaning capability according to claim 7, characterized in that: The nozzles (3) are arranged one by one in sequence between the first spoiler rib (2) and the second spoiler rib (2) of the air intake path, and the number of the nozzles (3) is 4 to 7.

10. A turbine rotor, characterized in that: A turbine blade cooling structure with self-cleaning capability as claimed in any one of claims 1 to 9.

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