Turbine guide vane cooling structure and turbine guide vane

Abstract

The turbine guide vane cooling structure comprises a front cavity and a rear cavity which are divided by a cavity dividing partition plate located in a vane body, the front cavity comprises a front cavity double-layer wall cooling unit, the front cavity double-layer wall cooling unit comprises an outer layer wall, an inner layer wall, a plurality of partition plates and gap through holes, and outer layer air film holes are formed in the outer layer wall; a double-layer wall separation cavity is defined by the inner layer wall and the outer layer wall, and an inner layer impact hole is formed in the inner layer wall; a plurality of partition plates are connected with the inner layer wall and the outer layer wall and divide the double-layer wall partition cavity into a plurality of chambers; the gap through holes are formed in the partition plate close to the blade throat part and used for communicating the adjacent cavities, and then cold air in the cavities is guided to the blade throat part. The cooling structure can effectively cool the throat part of the blade. The invention further provides the turbine guide vane comprising the turbine guide vane cooling structure.

Description

Technical Field

[0001] This invention relates to the field of turbine guide vanes, and more specifically to the field of guide vane cooling structures. Background Technology

[0002] The temperature range of turbine guide vanes is generally around 2000K to 2200K. Different parts have different heat load distribution characteristics, and the current cooling structure has failed to effectively cool the blade throat. Summary of the Invention

[0003] One object of the present invention is to provide a turbine guide vane cooling structure that can effectively cool the throat of the turbine guide vane.

[0004] To achieve the above objectives, the turbine guide vane cooling structure includes a front cavity and a rear cavity divided by a partition plate located inside the blade body. The front cavity includes a front cavity double-wall cooling unit, which includes: an outer wall with outer film perforations; an inner wall that defines a double-walled cavity with the outer wall and has inner impact holes; multiple partition plates that connect the inner wall and the outer wall and divide the double-walled cavity into multiple chambers; and a clearance through hole disposed on the partition plate near the blade throat for connecting adjacent chambers and guiding the cool air in the chamber to the blade throat.

[0005] In one or more embodiments, the gap through-hole is arranged laterally relative to the blade.

[0006] In one or more embodiments, a plurality of the gap through holes are disposed on the partition along the blade span.

[0007] In one or more embodiments, at least a portion of the inner impact pores and the outer air film pores are irregularly shaped pores.

[0008] In one or more embodiments, the outer film pores on the leading edge of the blade of the double-walled structure are conical film pores, the outer film pores on the pressure side are scoop-shaped film pores, and one or more rows of outer film pores on the suction side near the throat of the blade are W-shaped film pores.

[0009] In one or more embodiments, the ratio of the impact distance of the double-walled channel to the diameter of the inner impact hole ranges from (0.8 to 0.9):1.

[0010] In one or more embodiments, the ratio of the impact distance of the double-walled channel to the pore diameter of the outer air film is in the range of (1 to 1.5):1.

[0011] In one or more embodiments, the ratio of the distance from the W-shaped film air hole to the throat to the blade cascade height is (0.3-0.5):1, and the ratio of the distribution length of the W-shaped film air hole to the blade cascade height is (0.65-0.75):1.

[0012] In one or more embodiments, the ratio of the aperture of the gap through hole to the aperture of the inner layer impact hole is (0.5 to 0.6):1, and / or the ratio of the spacing between the gap through holes to the aperture of the gap through hole is (2.5 to 4.5):1.

[0013] In one or more embodiments, the rear cavity includes a rear cavity double-walled cooling unit, the rear cavity double-walled cooling unit including an inner wall, an outer wall, and air film pores located on the inner wall and the outer wall.

[0014] In one or more embodiments, the inner wall located on the leaf base and the back of the leaf connects at the tail of the leaf to form a tail edge septum, dividing the rear cavity into a tail edge cavity.

[0015] In one or more embodiments, a trailing edge baffle column is provided within the trailing edge cavity.

[0016] In one or more embodiments, the diameter of the trailing edge spoiler column ranges from 1 mm to 1.8 mm.

[0017] In one or more embodiments, the rear cavity double-walled cooling unit is further provided with a turbulence column.

[0018] In one or more embodiments, the front cavity double-wall cooling unit further includes a turbulence column located within the double-wall cavity.

[0019] Another object of the present invention is to provide a turbine guide vane including the turbine guide vane cooling structure described above.

[0020] Based on the characteristics of the heat load distribution of the turbine guide vane and the film coverage characteristics of different shaped film orifices after thin-walled outflow, the above-mentioned turbine guide vane cooling structure sets gap through holes in the blade throat. With the help of gap through holes and air pressure, the cooling airflow directed to the blade throat is increased, thereby improving the cooling effect on the turbine guide vane throat. Attached Figure Description

[0021] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0022] Figure 1 This is a schematic diagram of the blade basin of a turbine guide vane;

[0023] Figure 2 This is a schematic diagram of the back surface of a turbine guide vane;

[0024] Figure 3 It is along Figure 2 Cross-sectional view along the AA direction;

[0025] Figure 4 This is a cross-sectional view of the front cavity flow channel along the blade spanwise.

[0026] Figure 5 This is a cross-sectional view of the back cavity flow channel along the blade spanwise.

[0027] Figure 6 This is a schematic diagram of the front cavity double-wall cooling unit structure;

[0028] Figure 7 It is along Figure 6 A schematic diagram of the BB direction;

[0029] Figures 8A-8B This is a schematic diagram of a conical air film orifice;

[0030] Figures 9A-9B This is a schematic diagram of a sieve-shaped air film vent.

[0031] Figures 10A-10B This is a schematic diagram of a W-shaped air film vent;

[0032] Figure 11A-11B This is a schematic diagram of an expanded film pore;

[0033] Figure 12 This is a schematic diagram of a double-walled structure with gaps and through holes;

[0034] Figure 13 It is along Figure 12 Cross-sectional view along the CC direction;

[0035] Figure 14 This is a schematic diagram of a double-walled structure with turbulence-inducing columns;

[0036] Figure 15 It is along Figure 14 Cross-sectional view along the DD direction. Detailed Implementation

[0037] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0038] It should be noted that these and other accompanying drawings are merely examples and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention.

[0039] Reference Figures 1 to 3 As shown, the turbine guide vane 1 includes a leading edge 11, a pressure surface 12, and a suction surface 13. A partition 14 located inside the blade body divides it into a front chamber I and a rear chamber II, which are supplied with cooling air by two separate channels. The blade throat G is the area with the smallest cross-sectional area between two circumferentially adjacent turbine guide vanes. The turbine guide vane cooling structure described in this disclosure can effectively cool the inner wall G of the blade throat.

[0040] The front cavity I includes a front cavity double-wall cooling unit, specifically including an outer wall 15, an inner wall 16, multiple partitions 17, and a gap through hole 151.

[0041] The outer wall 15 has outer film cooling holes 150, and the inner wall 16 has inner impact holes 19. The inner wall 16 and the outer wall 15 define a double-walled cavity 18. Multiple baffles 17 connect the inner wall 16 and the outer wall 15, dividing the double-walled cavity 18 into multiple chambers 180. Cooling gas enters the double-walled cavity 18 through the inner impact holes 19 and then flows out of the blade through the outer film cooling holes 150.

[0042] A gap through-hole 151 is disposed on the septum 17 near the blade throat G, for connecting adjacent chambers 180, thereby guiding the cold air in chamber 180 to the blade throat G. In some embodiments, a plurality of gap through-holes 151 are distributed along the blade spanwise on the septum 17, connecting adjacent chambers 180. Figure 3 The diagram shows that the two septa 17 closest to the blade throat G have gap through holes 151. It can be understood that the number of septa 17 near the blade throat G can be adjusted according to specific operating conditions.

[0043] Because the pressure varies in each row of chambers 180 along the transverse direction of the blade, the pressure decreases towards the rear and closer to the blade throat G, resulting in poor cooling effect of the cooling airflow on the blade throat G in this area. By setting the gap through-hole 151, the cooling airflow introduced into the chambers 180 near the blade throat G can be increased. On the one hand, this can enhance the crossflow effect inside the double-walled structure and improve internal heat transfer; on the other hand, it can increase the air film outlet flow rate of the double-walled cooling unit in this area, thereby improving the air film coverage effect and ultimately enhancing the cooling effect on the blade throat G.

[0044] In some embodiments, the gap through-hole 151 is arranged laterally relative to the blade body, such as... Figure 3 As shown in Figure 11, adjacent chambers 180 are connected. In other embodiments, the gap through-hole 151 may also connect adjacent chambers 180 at an inclined angle, as long as it serves to guide the cooling airflow toward the side of the blade throat G.

[0045] For the leading edge 11, pressure surface 12 and suction surface 13 of the front cavity I, the use of a double-wall structure unit can improve the internal heat transfer. Furthermore, at least some of the inner impact holes 19 and the outer air film holes 150 are set as irregular holes, so that the air film coverage characteristics of the irregular air film holes with different hole types can be further utilized to improve the overall air film cooling efficiency of the blade.

[0046] For example, such as Figures 1 to 3 As shown, in some embodiments, considering that the external film cooling at the leading edge 11 mainly relies on the spray effect of the film, the outer film cooling holes at the leading edge 11 of the double-walled structure are set as conical film cooling holes 111. At the pressure surface 12, where there are more film cooling hole rows, the outer film cooling holes on the pressure surface side use scoop-shaped film cooling holes 121 with better short-range coverage characteristics. At the suction surface 13, where there are more film cooling hole rows, scoop-shaped film cooling holes 121 are still used, but at the last row or a few rows of film cooling holes, W-shaped film cooling holes 131 with better long-range coverage characteristics are used, which can increase the flow rate in the near-throat region and further improve the film cooling coverage effect at that location. To reduce aerodynamic losses caused by the blade outflow, the last row of W-shaped film cooling holes on the blade back is kept at a certain distance from the blade throat G position.

[0047] Reference Figure 4 As shown, for the cooling of the front cavity I, the cooling airflow N enters the double-walled partition cavity 18 through the inner impact hole 19. Part of it flows into the gap of the adjacent double-walled unit 180 through the gap through hole 151 to perform impact cooling on the blade throat, and the other part flows out of the blade through the outer air film hole 150.

[0048] Preferred, such as Figure 12 and Figure 13 As shown, the ratio of the impact distance p of the double-walled channel to the diameter d1 of the inner impact hole 19 ranges from (0.8 to 0.9):1; the ratio of the impact distance p of the double-walled channel to the diameter of the outer air film hole 150 (the diameter c2 of the scoop-type air film hole 121, or the diameter c3 of the W-type air film hole) ranges from (1 to 1.5):1. Furthermore, the ratio of the diameter c1 of the conical air film hole 111 or the diameter c2 of the scoop-type air film hole 121 to the diameter d1 of the impact hole is (0.55 to 0.8):1.

[0049] like Figure 13 As shown, the ratio of the diameter d2 of the gap through hole 151 to the diameter d1 of the impact hole is (0.5~0.6):1; the ratio of the hole spacing m2 of the gap through hole 151 to the diameter d2 of the gap through hole 151 is (2.5~4.5):1.

[0050] Back Figure 2As shown, in some embodiments, the ratio of the distance f from the throat of the last row of W-shaped air film holes 131 to the blade height h is (0.3-0.5):1, and the ratio of the distribution length l to the blade height h is (0.65-0.75):1.

[0051] like Figures 8A-8B As shown, the diameter c1 of the conical air film hole 111 of the leading edge 11 is about 0.5 mm to 0.55 mm, the yaw angle α1 is about 50° to 60°, and the expansion angle β1 is about 8° to 12°. The ratio of the length s1 of the expansion section 113 to the length l1 of the straight hole section 112 is (1.2-1.9):1.

[0052] like Figures 9A-9B As shown, the diameter c2 of the scoop-shaped air film hole 121 located on the pressure surface 12 and the suction surface 13 is about 0.5 mm to 0.7 mm, the inclination angle θ2 is about 30° to 50°, the back inclination angle ψ2 is about 9° to 12°, the expansion angle β2 is about 10° to 13°, and the ratio of the length s2 of the expansion section 123 to the length l2 of the straight hole section 122 is (1.0-1.5):1.

[0053] like Figures 10A-10B As shown, the diameter c3 of the W-shaped air film hole 131 of the suction surface 13 is about 0.6 mm to 0.7 mm, the tilt angle θ3 is about 30° to 40°, the back tilt angle ψ3 is about 10° to 15°, the expansion angle β3 is about 10° to 13°, the V-shaped included angle is about 120° to 140°, and the ratio of the length s3 of the expansion section 133 to the length l3 of the straight hole section 132 is (1.2 to 1.7):1.

[0054] like Figure 7 As shown, the inner impact holes 19 are preferably arranged in a staggered pattern, with the ratio of the hole spacing m1 to the hole diameter d1 being (3.5~5.5):1, and the ratio of the hole row spacing n1 to the hole diameter d1 being (2.0~2.7):1.

[0055] In other embodiments, the front cavity double-wall cooling unit also includes a turbulence column (not shown) located within the double-wall cavity.

[0056] Continue to refer to Figure 3 and Figure 5 As shown, the rear cavity II includes a rear cavity double-walled cooling unit, which includes an inner wall 16, an outer wall 15, and inner and outer air film pores located on the inner and outer walls. In some embodiments, it also includes gap turbulence columns 20. Figure 5 As shown, the cooling gas Y enters the double-walled partition cavity 18 through the rear cavity II via the rear cavity inlet 22 and the inner impact hole 19. After being turbulent by the turbulence column 20, it flows out of the blade through the outer air film hole 150.

[0057] like Figures 14-15 As shown, for the double-walled cooling unit combining the impact, turbulence column, and air film in the rear cavity II, the ratio of the impact distance p of the double-walled channel to the diameter of the impact hole is (0.8~0.9):1; the ratio of the diameter c2 of the scoop-type air film hole 121 or the diameter c3 of the W-type air film hole 131 to the diameter d1 of the impact hole is (0.5~0.9):1.

[0058] The impact holes 19 are arranged in a staggered pattern, and turbulence columns 20 are arranged between the rows of impact holes 19. The ratio of the impact hole spacing m1 to the impact hole diameter d1 is (3~5):1, the ratio of the impact hole row spacing n1 to the impact hole diameter d1 is (3~6):1, and the ratio of the turbulence column spacing m3 to the turbulence column diameter d3 is (2.5~4.5):1.

[0059] In some embodiments, the pressure surface 12 of the rear cavity II is provided with a scoop-shaped air film hole 121, and the suction surface 13 is provided with a W-shaped air film hole 131.

[0060] Furthermore, the rear cavity II is divided into a trailing edge cavity III by a trailing edge septum. The inner walls located on the blade base and blade back side connect at the blade trailing edge to form a trailing edge septum 6. Trailing edge cavity III is equipped with trailing edge baffles 21 and a trailing edge slit 141 located on the trailing edge. The diameter of the trailing edge baffles 21 ranges from 1 mm to 1.8 mm, and the specific number of rows and columns can be determined according to the actual blade size and airflow distribution.

[0061] As a further improvement to the above technical solution, the aforementioned scoop-shaped air film pore 121 can be replaced with, for example... Figure 11A-11B The expansion-type air film orifice shown has an orifice diameter c4 of approximately 0.5 mm to 0.7 mm, an inclination angle θ4 of approximately 30° to 40°, an expansion angle β4 of approximately 10° to 15°, and a ratio of the length l4 of the straight section 142 to the length s4 of the expansion section 142 of (1.2 to 1.7):1. The specific parameters and quantities can be selected according to the air film cooling effect.

[0062] Therefore, under certain cooling gas volume constraints, by employing a zoned design at different locations on the guide vane surface, and utilizing double-walled cooling units with combinations of "impact combined with film cooling," "impact, gap through-hole, and film cooling," and "impact, turbulence column, and film cooling," along with irregularly shaped film cooling holes with different orifice parameters, the heat load on the guide vane surface can be addressed by enhancing internal heat transfer while simultaneously improving film cooling efficiency at different locations on the guide vane surface, significantly reducing the guide vane's heat load. Under a cooling gas usage limit of 11% W25, experimental results show that the high-pressure turbine guide vane using this technical solution achieves a comprehensive cooling efficiency of 0.78–0.79, demonstrating superior cooling performance.

[0063] For ease of description, the foregoing uses spatial relative terms such as "above," "on top of," "on the upper surface of," and "above" to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0064] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0065] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A turbine guide vane cooling structure, comprising a front cavity and a rear cavity divided by a partition plate located inside the blade body, characterized in that, The front cavity includes a front cavity double-wall cooling unit, the front cavity double-wall cooling unit comprising: The outer wall has outer air film pores. The inner wall, together with the outer wall, defines a double-walled cavity, on which an inner impact hole is provided; Multiple partitions connect the inner wall and the outer wall, dividing the double-walled cavity into multiple chambers; and A gap through-hole is provided on the partition plate near the blade throat to connect the adjacent chambers and guide the cold air to the blade throat.

2. The turbine guide vane cooling structure as described in claim 1, characterized in that, The gap through-hole is arranged laterally relative to the blade body.

3. The turbine guide vane cooling structure as described in claim 1, characterized in that, Multiple gap through holes are arranged along the blade span on the partition plate.

4. The turbine guide vane cooling structure as described in claim 1, characterized in that, At least some of the inner layer impact holes and the outer layer air film holes are irregularly shaped holes.

5. The turbine guide vane cooling structure as described in claim 4, characterized in that, The double-wall structure has conical air film pores on the outer edge of the blade, scoop-shaped air film pores on the pressure side, and one or more rows of W-shaped air film pores on the suction side near the blade throat.

6. The turbine guide vane cooling structure as described in claim 4, characterized in that, The ratio of the impact distance of the double-walled channel to the diameter of the inner impact hole ranges from (0.8 to 0.9):

1.

7. The turbine guide vane cooling structure as described in claim 4, characterized in that, The ratio of the impact distance of the double-walled channel to the pore diameter of the outer air film is in the range of (1~1.5):

1.

8. The turbine guide vane cooling structure as described in claim 5, characterized in that, The ratio of the distance from the W-shaped film air vent to the throat to the blade height is (0.3-0.5):

1. The ratio of the distribution length of the W-shaped air film vents to the height of the blade cascade is (0.65-0.75):

1.

9. The turbine guide vane cooling structure as described in claim 1, characterized in that, The ratio of the diameter of the gap through-hole to the diameter of the inner impact hole is (0.5~0.6):1, and / or The ratio of the hole spacing to the hole diameter of the gap through hole is (2.5~4.5):

1.

10. The turbine guide vane cooling structure as described in claim 1, characterized in that, The rear cavity includes a rear cavity double-wall cooling unit, which includes an inner wall, an outer wall, and air film pores located on the inner wall and the outer wall.

11. The turbine guide vane cooling structure as described in claim 10, characterized in that, The inner wall located on the leaf base and the back of the leaf connects at the tail of the leaf to form a tail edge septum, which is used to divide the rear cavity into a tail edge cavity.

12. The turbine guide vane cooling structure as described in claim 11, characterized in that, The trailing edge cavity is provided with a trailing edge turbulence column.

13. The turbine guide vane cooling structure as described in claim 12, characterized in that, The diameter of the trailing edge spoiler column ranges from 1 mm to 1.8 mm.

14. The turbine guide vane cooling structure as described in claim 10, characterized in that, The rear cavity double-wall cooling unit is also equipped with a turbulence column.

15. The turbine guide vane cooling structure as described in claim 1, characterized in that, The front cavity double-wall cooling unit also includes a turbulence column located within the double-wall partition cavity.

16. A turbine guide vane, characterized in that, Includes the turbine guide vane cooling structure as described in any one of claims 1-15.

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