Turbine moving blade, cooling runner of turbine moving blade, turbine and engine

Abstract

The utility model discloses a turbine moving blade and a cooling runner thereof. The turbine moving blade comprises a radial outer flow section, a radial inner flow section and a connecting section, wherein the radial outer flow section and the radial inner flow section extend in the same direction and are spaced from each other, and the connecting section is connected with the radial outer flow section and the radial inner flow section and located at the same side end. The radial outer flow section is arranged to allow the cooling fluid to flow outwards in the radial direction of the blade body, and the radial inner flow section is arranged to allow the cooling fluid to flow inwards in the radial direction of the blade body.

Description

Technical Field

[0001] The utility model relates to a turbine moving blade, and more specifically to a turbine moving blade and a cooling flow channel thereof, a turbine and an engine. Background Art

[0002] In the field of cooling of turbine blades of aircraft engines and gas turbines, efficient blade cooling structure is the key design to ensure that blades can withstand high-temperature combustion gases. The first-stage turbine blades currently withstand the highest combustion gas temperatures among all blades, but the design efficiency of the first-stage turbine blade cooling structure is low, which affects the thermal efficiency of aircraft engines and gas turbines. Utility Model Content

[0003] The utility model provides a turbine blade and its cooling channel, as well as a turbine and an engine, which have high heat dissipation efficiency.

[0004] The embodiment of the utility model provides a cooling flow channel of a turbine moving blade, comprising: a radial outer flow section and a radial inner flow section;

[0005] The radially outer flow section is configured to allow the cooling fluid to flow radially outward along the blade body of the turbine moving blade, and the radially inner flow section is configured to allow the cooling fluid to flow radially inward along the blade body of the turbine moving blade;

[0006] The distance between the radial outer flow section and the pressure surface of the turbine blade is smaller than the distance between the radial inner flow section and the pressure surface of the turbine blade, and the distance between the radial inner flow section and the suction surface of the turbine blade is smaller than the distance between the radial outer flow section and the suction surface of the turbine blade.

[0007] In an exemplary embodiment, the radially outer flow section and the radially inner flow section both extend in the radial direction of the blade body, and / or the radially outer flow section and the radially inner flow section are parallel to each other.

[0008] In an exemplary embodiment, the cooling channel has a flat cross-section, including a long side and a short side, and the long sides of the radially outer flow section and the radially inner flow section are opposite to each other.

[0009] In an exemplary embodiment, the cooling flow channel further includes a connecting section, which extends along the thickness direction of the blade body and connects the radial outer flow section and the radial inner flow section, so that the cooling flow channel forms a U-shaped channel.

[0010] In an exemplary embodiment, a height of the connecting section along the radial direction of the blade body is less than or equal to twice the hydraulic diameter of the inlet of the U-shaped channel.

[0011] In an exemplary embodiment, the cooling channel is a smooth channel.

[0012] In an exemplary embodiment, the inner wall surface of the cooling flow channel is provided with spoiler ribs; the spoiler ribs include a plurality of first ribs provided on the inner wall surface of the radial outer flow section and spaced apart along the length direction of the radial outer flow section, and a plurality of second ribs provided on the inner wall surface of the radial inner flow section and spaced apart along the length direction of the radial inner flow section.

[0013] In an exemplary embodiment, the spoiler ribs extend along the width direction of the cooling channel and form an obtuse angle with the flow direction of the cooling fluid; or the spoiler ribs extend along the width direction of the cooling channel and are V-shaped, and the opening direction of the spoiler ribs is opposite to the flow direction of the cooling fluid.

[0014] In an exemplary embodiment, the first rib is provided on a wall surface of the radially outer flow section close to the pressure surface, and the second rib is provided on a wall surface of the radially inner flow section close to the suction surface; and / or

[0015] Along the flow direction of the cooling fluid, a plurality of the first ribs are arranged in a rear half region of the radial outer flow section, and a plurality of the second ribs are arranged in at least a front half region of the radial inner flow section.

[0016] In an exemplary embodiment, the spoiler ribs include at least one of the following: spoiler grooves recessed on the inner wall surface of the cooling channel, and spoiler ribs convexly disposed on the inner wall surface of the cooling channel.

[0017] In an exemplary embodiment, the cooling channel is provided with a partition, and the partition divides the cooling channel into the radial outer flow section and the radial inner flow section;

[0018] A gap is provided between the partition and the closed end of the cooling channel to allow the radially outer flow section to communicate with the radially inner flow section.

[0019] An embodiment of the utility model also provides a turbine moving blade, comprising: a blade body, the blade body comprising a pressure surface and a suction surface arranged opposite to each other along its thickness direction, and a radial inner end and a radial outer end arranged opposite to each other along its radial direction, and the blade body is provided with a cooling flow channel as described in any one of the above items.

[0020] In an exemplary embodiment, the radially outer flow section is provided with a cooling fluid input port, and the radially inner flow section is provided with a cooling fluid output port;

[0021] The cooling fluid inlet and the cooling fluid outlet are both located at the radial inner end of the turbine moving blade, and the connecting section of the cooling flow channel is arranged at the radial outer end so that the radial outer flow section is connected with the radial inner flow section at the radial outer end.

[0022] In an exemplary embodiment, the blade body is provided with a plurality of the cooling channels, and the plurality of the cooling channels are arranged along the axial direction of the turbine moving blade.

[0023] In an exemplary embodiment, the pressure surface, the radially outer flow section, the radially inner flow section, and the suction surface are arranged in sequence along the thickness direction of the blade body;

[0024] At the same radius of the turbine moving blade, a line connecting the cross-sectional center of the radial outer flow section and the cross-sectional center of the radial inner flow section is perpendicular to the rotation axis of the turbine moving blade.

[0025] An embodiment of the utility model further provides a turbine, comprising: an impeller, and turbine blades as described in any of the above embodiments and arranged on the impeller.

[0026] An embodiment of the utility model further provides an engine, comprising: an engine body, and a turbine as described in any of the above embodiments and arranged on the engine body.

[0027] The radial outer flow section and the radial inner flow section of the cooling flow channel in the embodiment of the utility model can generate Coriolis forces in different directions, acting on the opposite sides of the radial outer flow section and the radial inner flow section, so as to push the cooling fluid inside the cooling flow channel to act on the suction surface and the pressure surface flowing toward the turbine moving blade, thereby improving the heat dissipation efficiency of the suction surface and the pressure surface.

[0028] Other features and advantages of the utility model will be described in the following description, and partly become apparent from the description, or understood by implementing the utility model. The purpose and other advantages of the utility model can be realized and obtained through the structures particularly pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The accompanying drawings are used to provide a further understanding of the technical solution of the utility model and constitute a part of the specification. Together with the embodiments of the utility model, they are used to explain the technical solution of the utility model and do not constitute a limitation on the technical solution of the utility model.

[0030] Figure 1 This is an overall three-dimensional view of a cooling channel in one embodiment of the utility model;

[0031] Figure 2 for Figure 1 A top view of a cooling channel of an embodiment;

[0032] Figure 3 A schematic diagram of a turbine moving blade according to an embodiment of the utility model;

[0033] Figure 4This is an overall three-dimensional view of a cooling channel in another embodiment of the utility model;

[0034] Figure 5 for Figure 4 A top view of a cooling channel of an embodiment;

[0035] Figure 6 A schematic diagram of a turbine moving blade according to another embodiment of the utility model;

[0036] Figure 7 It is a schematic diagram of another spoiler rib of a cooling channel according to another embodiment of the utility model;

[0037] Figure 8 For this utility model Figure 1 Averaged overall Nusselt diagram of suction and pressure surfaces of a turbine bucket of an embodiment;

[0038] Fig. 9 For this utility model Figure 1 A diagram of pressure loss coefficient of a turbine blade according to an embodiment;

[0039] Fig.10 For this utility model Figure 6 A diagram showing the ratio of the average Nusselt number of the rib surface of the turbine moving blade to the pressure surface in the embodiment;

[0040] Fig.11 For this utility model Figure 6 A diagram showing the ratio of the average Nusselt number of the rib surface to the suction surface of a turbine moving blade according to an embodiment. DETAILED DESCRIPTION

[0041] In order to make the purpose, technical solution and advantages of the utility model more clear, the embodiments of the utility model will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments and features in the embodiments of the utility model can be combined with each other arbitrarily without conflict.

[0042] like Figure 1 As shown, the cooling flow channel 2 of the embodiment of the utility model includes a radial outer flow section 21 and a radial inner flow section 22. The radial outer flow section 21 is configured to allow the cooling fluid to flow radially outward along the turbine blade 100, and the radial inner flow section 22 is configured to allow the cooling fluid to flow radially inward along the turbine blade 100. The distance between the radial outer flow section 21 and the pressure surface of the turbine blade 100 is smaller than the distance between the radial inner flow section 22 and the pressure surface 11 of the turbine blade 100, and the distance between the radial inner flow section 22 and the suction surface 12 of the turbine blade 100 is smaller than the distance between the radial outer flow section 21 and the suction surface 11 of the turbine blade 100.

[0043] like Figure 2As shown in FIG. 1 , the turbine moving blade 100 generates a Coriolis force F on the cooling fluid in the cooling flow channel 2 under the condition of rotation. The direction of the Coriolis force F is related to the rotation angle direction of the turbine moving blade 100 and the flow direction of the cooling fluid. According to the judgment principle of the Coriolis force F, the direction of the Coriolis force F of the radial outer flow section 21 and the radial inner flow section 22 is obtained. As shown in the figure, the suction surface 11 and the pressure surface 12 of the turbine moving blade 100 are respectively acted on the radial outer flow section 21 and the radial inner flow section 22 (refer to FIG. 1 ). Figure 3 ), so that the cooling channel 2 of the embodiment of the present application can improve the heat dissipation efficiency of the suction surface 11 and the pressure surface 12 of the turbine moving blade 100.

[0044] The radial outer flow section 21 and the radial inner flow section 22 of the cooling channel 2 of the embodiment of the utility model can generate Coriolis forces F in different directions, which act on the suction surface 11 and the pressure surface 12 of the corresponding turbine blade 100 of the radial outer flow section 21 and the radial inner flow section 22, and can push the cooling fluid inside the cooling channel 2 to flow to the suction surface 11 and the pressure surface 12 of the turbine blade 100, thereby improving the heat dissipation efficiency of the suction surface 11 and the pressure surface 12.

[0045] like Figure 1 As shown, the radial outer flow section 21 and the radial inner flow section 22 extend in the same direction and are spaced from each other. The radial outer flow section 21 is provided with a cooling fluid input port 210, and the radial inner flow section 22 is provided with a cooling fluid output port 220. The cooling fluid input port 210 and the cooling fluid output port 220 are located on the same side, so that the same cooling fluid flows in opposite directions in the radial outer flow section 21 and the radial inner flow section 22, generating Coriolis forces F in different directions, respectively pushing the fluid acting on the pressure surface 11 and the suction surface 12 to dissipate heat.

[0046] like Figure 1 , Figure 2 As shown, the cooling channel 2 also includes a connecting section 23, which is located between the radial outer flow section 21 and the radial inner flow section 22. The connecting section 23 extends along the thickness direction of the blade body 1 and connects the radial outer flow section 21 and the radial inner flow section 22, so that the cooling channel forms a U-shaped channel.

[0047] The height h of the connecting section 23 along the radial direction of the blade body 1 is less than or equal to twice the hydraulic diameter of the cooling fluid inlet 210 of the U-shaped channel. The hydraulic diameter refers to the ratio of four times the flow cross-sectional area to the circumference. In fluid mechanics calculations, the diameter is taken as the characteristic length for a circular tube, and the hydraulic diameter is taken as the characteristic length for a non-circular tube. The height h of the connecting section 23 along the radial direction of the blade body 1 is set to be less than or equal to twice the hydraulic diameter of the cooling fluid inlet 210 of the U-shaped channel, so as to ensure that the cooling fluid in the radial outer flow section 21 can smoothly enter the radial inner flow section 22 after passing through the connecting section 23 near the radial outer end 14.

[0048] The connecting section 23 of the embodiment of the present application is used to connect the radial outer flow section 21 and the radial inner flow section 22, which can simplify the structural design of the cooling channel 2 and the structural design of the cooling fluid supply device and the external fluid pipeline (not shown). It can be understood that the connecting section 23 can be located on the side of the radial outer end 14 or on the side of the radial inner end 13, and both can achieve the effect of the cooling fluid in the cooling channel 2 flowing to the outer surface of the blade body 1 under the action of the Coriolis force, which is within the protection scope of the present application.

[0049] like Figure 1 , Figure 2 As shown, the cross-section of the cooling channel 2 of the embodiment of the utility model is flat, including a long side and a short side, and the long sides of the radial outer flow section 11 and the radial inner flow section 12 are opposite, so that the heat exchange area with the pressure surface 11 and the suction surface 12 is increased.

[0050] The radial outer flow section 21 and the radial inner flow section 22 in this embodiment are parallel to each other and extend radially along the blade body 1. With this design, the cooling fluid flows faster in the cooling channel 2, so that the heat exchange efficiency between the cooling fluid and the blade body 1 is higher, and the cooling effect of the blade body 1 is better. It is worth noting that the cross-sectional shape of the radial outer flow section 21 and the radial inner flow section 22 is not limited to a rectangle, but can be a rectangle, and can maintain a sufficient heat exchange area with the pressure surface 11 and the suction surface 12. Of course, the cross-section of the cooling channel 2 can also be any shape such as a circle, a trapezoid, etc., which is not limited here; at the same time, the distribution positions of the radial outer flow section 21 and the radial inner flow section 22 in the blade body 1 are not limited to the above positions.

[0051] The cooling channel 2 of the embodiment of the utility model is a smooth channel, which can facilitate the smooth circulation of the cooling fluid in the cooling channel 2, and facilitate the rapid entry and exit of the cooling fluid to take away the heat.

[0052] like Figure 3 As shown, the embodiment of the utility model provides a turbine moving blade 100, including a blade body 1, the blade body 1 including a pressure surface 11 and a suction surface 12 opposite to each other along its rotation direction. The blade body 1 includes a radial inner end 13 and a radial outer end 14 opposite to each other along its radial direction. The blade body 1 is provided with a cooling flow channel 2 as described in any of the above embodiments, for inputting a cooling fluid to dissipate heat from the turbine moving blade 100.

[0053] The cooling channel 2 extends from the radial inner end 13 to the radial outer end 14 and then bends back from the radial outer end 14 to the radial inner end 11. The radial outer flow section 21 of the cooling channel 2 corresponds to the pressure surface 11, and the radial inner flow section 22 of the cooling channel 2 corresponds to the suction surface 12.

[0054] The radial outer flow section 21 and the radial inner flow section 22 of the turbine blade 100 of the embodiment of the utility model are arranged side by side along the thickness direction of the turbine blade 100. At the same radius of the turbine blade 100, the line connecting the cross-sectional center of the radial outer flow section 21 and the cross-sectional center of the radial inner flow section 22 is perpendicular to the rotation axis of the turbine blade 100, so that the turbine blade 100 is stressed and heat exchange is uniform.

[0055] The radial outer flow section 21 and the radial inner flow section 22 of the turbine blade 100 of the embodiment of the utility model are both flat and extend along the elongation directions of the pressure surface 11 and the suction surface 11 respectively, thereby increasing the heat exchange area with the pressure surface 11 and the suction surface 12 of the turbine blade 100.

[0056] The cooling fluid inlet 210 and the cooling fluid outlet 220 are both located at the radial inner end 13 of the turbine blade 100 , and the connecting section 23 of the cooling channel 2 is provided at the radial outer end 14 so that the radial outer flow section 21 is connected to the radial inner flow section 22 at the radial outer end 14 .

[0057] The blade body 1 of the embodiment of the utility model is provided with a plurality of cooling channels 2, which are arranged along the axial direction of the turbine moving blade 100 and arranged at intervals, so as to increase the heat dissipation area. The pressure surface 11, the radial outer flow section 21, the radial inner flow section 22, and the suction surface 12 are arranged in sequence along the thickness direction of the blade body 1.

[0058] The cooling fluid inlet 210 and the cooling fluid outlet 220 of the cooling channel 2 are both arranged at the radial inner end 13, and the connecting section 23 is arranged at the radial outer end 14, so that the radial outer flow section 21 and the radial inner flow section 22 are connected at the radial outer end 14, which is beneficial to the arrangement of the cooling fluid supply device and makes the distribution range of the cooling channel 2 in the blade body 1 larger, which is more beneficial to the heat exchange cooling of the blade body 1.

[0059] like Figure 8 As shown, the heat transfer effect of the suction surface 11 and the pressure surface 12 of the turbine moving blade 100 of the embodiment of the utility model changes with the increase of the rotation number. From the figure, it can be seen that as the rotation number increases, the overall heat exchange effect of the suction surface 11 and the pressure surface 12 of the cooling flow channel 2 is enhanced (Nussell number ratio is a dimensionless parameter used to indicate the size of the heat transfer capacity. The larger the Nusselt number ratio, the better the heat transfer effect). Figure 8 Each data point is the average value of the heat transfer effect of the suction surface 11 and the pressure surface 12 of the cooling channel 2. Among them, rotation 1 and rotation 2 represent the degree of heat transfer enhancement brought by rotation compared with static state; 1.1 and 6.8 represent the degree of heat transfer enhancement brought by rotation compared with static state.

[0060] like Fig. 9As shown, the pressure loss coefficient between the input port 210 and the output port 220 of the cooling channel 2 of the turbine moving blade 100 of the embodiment of the utility model. The pressure loss coefficient is also a dimensionless parameter, which is used to indicate the pressure loss or resistance loss of the channel. The lower the pressure loss coefficient, the less pressure loss and resistance loss of the cooling channel 2. It can be seen from the figure that as the number of rotations increases, the resistance loss of the cooling channel 2 decreases. Among them, -3.13 and -4.63 represent the degree of reduction in pressure loss caused by rotation compared to static.

[0061] like Figure 4-Figure 5 As shown, another embodiment of the cooling channel 2a provided in the embodiment of the present application, in this embodiment, the cooling channel 2a includes a radial outer flow section 21a and a radial inner flow section 22a, the radial outer flow section 21a is configured to allow the cooling fluid to flow radially outward along the turbine blade 100a, and the radial inner flow section 22a is configured to allow the cooling fluid to flow radially inward along the turbine blade 100a. The distance between the radial outer flow section 21a and the pressure surface 11a of the turbine blade 100a is smaller than the distance between the radial inner flow section 22a and the pressure surface 11a of the turbine blade 100a, and the distance between the radial inner flow section 22a and the suction surface 12a of the turbine blade 100a is smaller than the distance between the radial outer flow section 21a and the suction surface of the turbine blade 100a. The radial outer flow section 21a and the radial inner flow section 22a in this embodiment extend in the same direction and are spaced apart from each other.

[0062] The main difference between the cooling channel 2a of this embodiment and the cooling channel 2 of the above embodiment is that the inner wall surface of the cooling channel 2a of this embodiment is provided with spoiler ribs 15. The rest can be referred to the cooling channel 2 of the above embodiment and will not be repeated here.

[0063] The spoiler ribs 15 include a plurality of first ribs 151 disposed on the inner wall surface of the radial outer flow section 21a and spaced apart along the length direction of the radial outer flow section 21a, and a plurality of second ribs 152 disposed on the inner wall surface of the radial inner flow section 22a and spaced apart along the length direction of the radial inner flow section 22a.

[0064] The first ribs 151 are arranged on the wall surface of the radial outer flow section 21a close to the pressure surface 11a, and the second ribs 152 are arranged on the wall surface of the radial inner flow section 22a close to the suction surface 12a. Along the flow direction of the cooling fluid, the plurality of first ribs 151 are arranged at least in the rear half area of ​​the radial outer flow section 21a, and the plurality of second ribs 152 are arranged at least in the front half area of ​​the radial inner flow section 22a.

[0065] The first rib 151 can disturb the cooling fluid in the radial outer flow section 21a and generate a secondary flow, increase the speed of the cooling fluid reattachment, enhance the mixing of the wall fluid and the mainstream, and improve the heat exchange cooling effect of the inner wall surface of the radial outer flow section 21a. Similarly, the second rib 152 can disturb the cooling fluid in the radial inner flow section 22a and generate a secondary flow, and improve the heat exchange cooling effect of the inner wall surface of the radial inner flow section 162.

[0066] By arranging the first rib 151 on the wall surface of the radial outer flow section 21a close to the pressure surface 11a, and arranging the second rib 152 on the wall surface of the radial inner flow section 22a close to the suction surface 12, the cooling fluid in the radial outer flow section 21a flows toward the inner wall surface close to the pressure surface 11 under the action of the Coriolis force, and the cooling fluid flowing toward the pressure surface 11a is further disturbed by the first rib 151 close to the pressure surface 11a, thereby enhancing the heat exchange effect, so that the heat exchange effect between the cooling fluid in the radial outer flow section 21a and the pressure surface 11a is better.

[0067] Similarly, the second rib 152 is arranged on the wall surface of the radial inner flow section 22a close to the suction surface 12a, so that the cooling fluid in the radial inner flow section 22a flows toward the inner wall surface close to the suction surface 12a under the action of the Coriolis force, and the cooling fluid is simultaneously affected by the turbulent flow separation effect of the second rib close to the suction surface 12a, thereby further enhancing the heat exchange cooling effect between the cooling fluid in the radial inner flow section 22a and the suction surface 12a.

[0068] The first rib 151 is at least located in a region of the radially outer flow section 21a close to the radially outer end 14a, and the second rib 152 is at least located in a region of the radially inner flow section 22a close to the radially outer end 14a.

[0069] The connecting section 23a of the present embodiment is arranged at the radial outer end 14a. The cooling fluid forms a rotating and turning airflow when passing through the connecting section 23. According to the Coriolis force formula, the Coriolis force of the cooling fluid passing through the connecting section 23a is reduced or even disappears, so that the cooling and heat exchange effect of the cooling fluid in the connecting section 23a on the blade body 1a is weakened. By setting the spoiler ribs 15, the problem of weakened heat exchange and cooling of the cooling fluid near the radial outer end 14a due to the weakened Coriolis force on the cooling fluid passing through the connecting section 23a can be compensated.

[0070] The spoiler ribs 15 include at least one of the following: spoiler grooves recessed on the inner wall surface of the cooling channel 2a, and spoiler ribs convexly disposed on the inner wall surface of the cooling channel 2a.

[0071] The turbine moving blade 100 of the embodiment of the present application is provided with spoiler ribs 15 on the inner wall surface of the cooling channel 2a, and the spoiler ribs 15 have the function of strengthening the cooling effect of the cooling channel 2a of the blade body 1a. The spoiler ribs 15 are provided inside the cooling channel 2a to expand the contact area between the cooling fluid and the blade body 1, and the repeated arrangement of multiple spoiler ribs 15 causes the cooling fluid in the cooling channel 2a to produce flow separation and secondary flow, and then reattaches the new boundary layer to the heat transfer surface, thereby enhancing the heat exchange effect between the cooling fluid and the blade body 1. In addition, the separated boundary layer enhances the mixing of the wall fluid and the mainstream, and the heat from the near wall surface can be more effectively transferred to the mainstream, thereby further enhancing the heat exchange effect.

[0072] like Figure 6 As shown, the spoiler rib 15 of the turbine moving blade 100a of the embodiment of the present application extends along the width direction of the cooling flow channel 2a and forms an obtuse angle with the flow direction of the cooling fluid, which can improve the spoiler effect. Figure 7 As shown, the spoiler rib 15 is V-shaped, and the V-shaped opening is opposite to the flow direction of the cooling fluid.

[0073] Of course, the inclination angle of the blade body 1a is not limited, and whether it is symmetrically distributed is not limited. The spoiler ribs 15 can be set to various spoiler structures such as column ribs, micro ribs, triangular ribs, pits, etc., all of which fall within the protection scope of this patent.

[0074] In an exemplary embodiment, the cooling channel 2, 2a is provided with a partition (not shown), which divides the cooling channel into a radial outer flow section 21, 21a and a radial inner flow section 22, 22a. A gap is provided between the partition and the closed end of the cooling channel 2, 2a to allow the radial outer flow section 21, 21a to communicate with the radial inner flow section 22, 22a.

[0075] In an exemplary embodiment, an inner cavity is provided in the blade body 1, 1a, and the inner cavity is open along one radial end of the blade body 1, 1a. The partition of the turbine moving blade is provided in the inner cavity, and divides the inner cavity into a radial outer flow section 21, 21a and a radial inner flow 22, 22a, and a gap is provided between the partition and the closed end of the inner cavity to connect the radial outer flow section 21, 21a and the radial inner flow section. The radial outer flow section 21, 21a, the radial inner flow section 22, 22a and the connecting section 23, 23a are formed in the blade body 1, 1a by the partition and the inner cavity. The structural design is simple and easy to manufacture, wherein the partition and the blade body 1, 1a can be an integral part made of the same material.

[0076] like Figure 6As shown, another embodiment of the turbine impeller 100a provided in the embodiment of the present application comprises: a blade body 1a, the blade body 1a comprises a pressure surface 11a and a suction surface 12a arranged opposite to each other along its thickness direction, and a radial inner end 13a and a radial outer end 14a arranged opposite to each other along its radial direction, and the blade body 1a is provided with a cooling channel 2a as described in any of the above embodiments. The main difference between the turbine impeller 100a of this embodiment and the turbine impeller 100 of the above embodiment is that the shape and the cooling channel 2a are different from the cooling channel 2, and the rest can refer to the turbine impeller 100, which will not be repeated here.

[0077] The radial outer flow section 21a of the cooling flow channel 2a is configured to allow the cooling fluid to flow in a direction from the radial inner end 13a (blade root) to the radial outer end 14a (blade top), and the radial inner flow section 22a is configured to allow the cooling fluid to flow in a direction from the radial outer end 14a to the radial inner end 13a; the pressure surface 11a, the radial outer flow section 21a, the radial inner flow section 22a, and the suction surface 12 are arranged in sequence along the thickness direction of the blade body 1.

[0078] The turbine impellers 100 and 100a of the above-mentioned embodiments of the present application involve Coriolis force, which is referred to as Coriolis force for short, and is a description of the displacement of the linear motion of a particle in a rotating system due to inertia relative to the rotating system. The Coriolis force formula is Fcor=2mΩ×U, where Fcor is the Coriolis force on the fluid, Ω is the channel rotation angular velocity, U is the fluid motion velocity, and the direction of the Coriolis force depends on the direction of rotation and the direction of the cooling fluid.

[0079] When the blade body 1, 1a rotates around the rotation axis M on the radial inner end 13, 13a side, a pressure surface 11, 11a and a suction surface 12, 12a are formed. A cooling flow channel 2, 2a is provided in the blade body 1, 1a, and the cooling fluid in the cooling flow channel 2, 2a has the function of cooling the turbine moving blade, so that the blade body 1, 1a can be prevented from deformation and damage in a high temperature environment.

[0080] During the rotation of the blade body 1, 1a, the cooling fluid in the cooling flow channel 2, 2a is in a rotating system and generates Coriolis force due to inertia. The radial outflow section 21, 21a is configured to allow the cooling fluid to flow in a direction from the radial inner end 13, 13a to the radial outer end 14, 14a. The radial outflow section 21, 21a is configured close to the pressure surface 11, 11a. According to the Coriolis force formula, the cooling fluid in the radial outflow 21, 21a is subjected to the Coriolis force in the direction from the suction surface 12, 12a to the pressure surface 11, 11a.

[0081] The radial inner flow sections 22, 22a are configured to allow the cooling fluid to flow in a direction from the radial outer ends 14, 14a to the radial inner ends 13, 13a. The radial inner flow sections 22, 22a are configured close to one side of the suction surfaces 12, 12a. According to the Coriolis force formula, the cooling fluid in the radial inner flow sections 22, 22a is subjected to a Coriolis force in a direction from the pressure surfaces 11, 11a to the suction surfaces 12, 12a.

[0082] As a result, the blade body 1, 1a is in a rotating state, and the cooling fluid in the cooling channel 2, 2a is affected by the Coriolis force, so that the radial outer flow section 21, 21a is offset toward the pressure surface 11, and the cooling fluid in the radial inner flow section 22, 22a is offset toward the suction surface 12, 12a, thereby enhancing the heat exchange cooling effect of the suction surface 12, 12a and the pressure surface 11, 11a of the blade body 1, 1a.

[0083] The turbine moving blade 100a of the embodiment of the present application has a reasonable arrangement of the structure of the cooling channel 2a, and can change the flow direction of the cooling fluid in the cooling channel 2a by using the Coriolis force of the cooling fluid in the rotating state and the spoiler ribs 15, thereby accelerating the cooling and heat exchange process of the turbine moving blade and affecting the heat transfer coefficient distribution on the surface of the blade body 1. In addition, the turbine moving blade structure provided by the embodiment of the present application is reasonably simple in design, has low processing difficulty, and is easy to promote and apply.

[0084] For the turbine moving blades in the embodiment of the present application, under the condition that the cooling fluid inlet 210 of the radial outward flow section 21a has the same Reynolds number, the faster the rotation speed of the blade body 1, according to the Coriolis force formula, the greater the strength of the Coriolis force exerted on the cooling fluid in the cooling channel 2a, and the stronger the heat exchange and cooling of the pressure surface 11 and the suction surface 12 of the blade body 1.

[0085] The turbine moving blade provided in the embodiment of the present application is simulated and calculated. The turbine moving blade is selected from a turbine turbine moving blade middle section geometric parameters to stretch the entire blade body. A plurality of straight rib-shaped spoiler ribs 15 are arranged on the radial outer flow section 21a and the radial inner flow 22a near the radial outer end 14a. The connecting section 23a is arranged on the radial outer end 14a side. The simulation calculation is performed to obtain Figure 10-11 The fluid simulation results of the blade body 1a are shown.

[0086] Fig.10 The abscissa is the rotation number, and the ordinate is the average Nusselt number ratio of the pressure surface 11a. The Nusselt number ratio is used to indicate the heat transfer intensity. Fig.11 The abscissa is the rotation number, and the ordinate is the average Nusselt number ratio of the suction surface 12a.

[0087] Depend on Fig.10 and Fig.11It can be seen from the displayed linear data that during the rotation of the turbine moving blade, the Coriolis force in the cooling channel 2 increases the heat transfer intensity of the pressure surface 11a and the suction surface 12a of the blade body 1. Therefore, the structural design of the cooling channel 2a and the spoiler rib 15 of the turbine moving blade provided in the embodiment of the present application enhances the heat exchange capacity of the cooling channel 2 and has a better cooling effect.

[0088] The present application provides a turbine, including an impeller and turbine blades 100, 100a arranged on the impeller as described in any of the above exemplary embodiments. The turbine blades 100, 100a are connected to the rotating shaft through the impeller, and the cooling channel 2 is not directly connected to the rotating shaft.

[0089] An embodiment of the present application provides an engine, comprising an engine body and a turbine as described in the above embodiment connected to the engine body.

[0090] Specifically, the turbine and engine provided in the present application include the turbine blades described in any one of the above exemplary embodiments, and therefore have the structural features and advantages of the turbine blades described in the above exemplary embodiments, which will not be elaborated here.

[0091] The turbine blades 100, 100a provided in the embodiments of the present application can be applied to gas turbines, aerospace engines and various types of turbine engines, and have certain application prospects.

[0092] The cooling channels 2 and 2a of the embodiment of the present application have simple structures and low processing difficulty. The experimental results show that Figure 4 As shown, under rotating conditions, the overall heat exchange of the suction surfaces 21, 21a and the pressure surfaces 22, 22a of the smooth cooling flow channels 2, 2a that utilize the Coriolis force to enhance heat exchange and reduce drag is improved; the results of numerical simulation show that, under rotating conditions, the pressure loss of the smooth cooling flow channel 2 that utilizes the Coriolis force to enhance heat exchange and reduce drag is reduced.

[0093] In the description of the present invention, it should be noted that the terms "upper", "lower", "one side", "the other side", "one end", "the other end", "side", "relative", "four corners", "periphery", "'mouth'-shaped structure" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the structure referred to has a specific orientation, is constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0094] In the description of the embodiments of the present utility model, unless otherwise clearly specified and limited, the terms "connection", "direct connection", "indirect connection", "fixed connection", "installation", and "assembly" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; the terms "installation", "connection", and "fixed connection" can be a direct connection, or an indirect connection through an intermediate medium, or the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0095] Although the implementation methods disclosed in the utility model are as above, the above contents are only implementation methods adopted to facilitate the understanding of the utility model, and are not used to limit the utility model. Any technician in the field to which the utility model belongs can make any modifications and changes in the form and details of implementation without departing from the spirit and scope disclosed in the utility model, but the scope of patent protection of the utility model shall still be defined by the attached claims.

Claims

1. A cooling channel for a turbine blade, characterized in that: include: A radially outer flow section and a radially inner flow section; The radially outer flow section is configured to allow the cooling fluid to flow radially outward along the blade body of the turbine moving blade, and the radially inner flow section is configured to allow the cooling fluid to flow radially inward along the blade body of the turbine moving blade; The distance between the radial outer flow section and the pressure surface of the turbine blade is smaller than the distance between the radial inner flow section and the pressure surface of the turbine blade, and the distance between the radial inner flow section and the suction surface of the turbine blade is smaller than the distance between the radial outer flow section and the suction surface of the turbine blade.

2. The cooling channel of the turbine blade according to claim 1, characterized in that: The radially outer flow section and the radially inner flow section both extend in the radial direction of the blade body, and / or the radially outer flow section and the radially inner flow section are parallel to each other.

3. The cooling channel of the turbine blade according to claim 1, characterized in that: The cooling channel has a flat cross section, including a long side and a short side, and the long sides of the radial outer flow section and the radial inner flow section are opposite to each other.

4. The cooling channel of the turbine blade according to claim 1, characterized in that: The cooling flow channel also includes a connecting section, which extends along the thickness direction of the blade body and connects the radial outer flow section and the radial inner flow section, so that the cooling flow channel forms a U-shaped channel.

5. The cooling channel of the turbine blade according to claim 4, characterized in that: A height of the connecting section along the radial direction of the blade body is less than or equal to twice the hydraulic diameter of the inlet of the U-shaped channel.

6. The cooling channel of a turbine blade according to any one of claims 1 to 5, characterized in that: The cooling channel is a smooth channel.

7. The cooling channel of a turbine blade according to any one of claims 1 to 5, characterized in that: The inner wall surface of the cooling flow channel is provided with spoiler ribs; the spoiler ribs include a plurality of first ribs arranged on the inner wall surface of the radial outer flow section and spaced apart along the length direction of the radial outer flow section, and a plurality of second ribs arranged on the inner wall surface of the radial inner flow section and spaced apart along the length direction of the radial inner flow section.

8. The cooling channel of the turbine blade according to claim 7, characterized in that: The spoiler ribs extend along the width direction of the cooling channel and form an obtuse angle with the flow direction of the cooling fluid; or the spoiler ribs extend along the width direction of the cooling channel and are V-shaped, and the opening direction of the spoiler ribs is opposite to the flow direction of the cooling fluid.

9. The cooling channel of the turbine blade according to claim 8, characterized in that: The first rib is provided on a wall surface of the radial outer flow section close to the pressure surface, and the second rib is provided on a wall surface of the radial inner flow section close to the suction surface; and / or Along the flow direction of the cooling fluid, a plurality of the first ribs are arranged in the rear half region of the radial outer flow section, and a plurality of the second ribs are arranged in at least the front half region of the radial inner flow section.

10. The cooling channel of the turbine blade according to claim 8, characterized in that: The spoiler ribs include at least one of the following: spoiler grooves recessed on the inner wall surface of the cooling channel, and spoiler ribs convexly disposed on the inner wall surface of the cooling channel.

11. The cooling channel of a turbine blade according to any one of claims 1 to 5, characterized in that: The cooling channel is provided with a partition, and the partition divides the cooling channel into the radial outer flow section and the radial inner flow section; A gap is provided between the partition and the closed end of the cooling channel to allow the radially outer flow section to communicate with the radially inner flow section.

12. A turbine moving blade, characterized in that: include: A blade body, comprising a pressure surface and a suction surface arranged opposite to each other along its thickness direction, and a radial inner end and a radial outer end arranged opposite to each other along its radial direction, and the blade body is provided with a cooling channel as described in any one of claims 1-11.

13. The turbine moving blade according to claim 12, characterized in that: The radial outer flow section is provided with a cooling fluid input port, and the radial inner flow section is provided with a cooling fluid output port; The cooling fluid inlet and the cooling fluid outlet are both located at the radial inner end of the turbine moving blade, and the connecting section of the cooling flow channel is arranged at the radial outer end so that the radial outer flow section is connected with the radial inner flow section at the radial outer end.

14. The turbine moving blade according to claim 12, characterized in that: The blade body is provided with a plurality of cooling channels, and the plurality of cooling channels are arranged along the axial direction of the turbine moving blade.

15. The turbine moving blade according to claim 12, characterized in that: The pressure surface, the radial outer flow section, the radial inner flow section, and the suction surface are arranged in sequence along the thickness direction of the blade body; At the same radius of the turbine moving blade, a line connecting the cross-sectional center of the radial outer flow section and the cross-sectional center of the radial inner flow section is perpendicular to the rotation axis of the turbine moving blade.

16. A turbine, characterized in that: include: An impeller, and a turbine moving blade according to any one of claims 12 to 15 and arranged on the impeller.

17. An engine, characterized in that: include: An engine body, and a turbine according to claim 16 provided on the engine body.

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