A water corrugated wall cooling structure for gas turbine

Abstract

The present invention provides a water corrugated wall cooling structure for a gas turbine, comprising an impact wall with an impact jet hole and an impact target wall with an air film overflow hole, a cold air flow channel is formed between the impact wall and the impact target wall, the impact jet hole and the air film overflow hole are both in communication with the cold air flow channel, and the air film overflow hole is in communication with the gas channel, and a corrugated surface is provided on the surface of the impact target wall facing the impact wall. Since the corrugated surface is provided on the surface of the impact target wall facing the impact wall in the present invention, when the cold air jet flows through the cold air flow channel, the equivalent impact distance is reduced, the effective scouring area is increased, and the flow dead zone area is reduced, so that the cold air organization utilization efficiency is improved, and the cooling effect is improved; compared with the traditional plane wall cooling structure, the water corrugated wall cooling structure adopted by the present invention can improve the cooling effect by about 20% and reduce the flow loss by about 15%.

Description

Technical Field

[0001] The invention relates to the technical field of gas turbine turbine cooling, in particular to a water corrugated wall cooling structure for gas turbine turbines. Background Art

[0002] Gas turbine is a thermal power mechanical device that uses air as the working medium. It is widely used in many industrial fields such as aircraft, ship propulsion and power generation. Figure 1 As shown in the figure, the core components of the gas turbine include the compressor 1, the combustion chamber 2 and the turbine 3. Among them, the turbine is directly affected by high-temperature and high-pressure gas, and the operating temperature is far beyond the temperature resistance limit of the material used to manufacture the turbine. In order to ensure its safe, stable and long-life operation, the turbine must be cooled. The cooling medium of the turbine is generally low-temperature air drawn from the compressor. Obviously, insufficient cooling air supply will cause high-temperature turbine parts to burn, and excessive cooling air will cause the overall thermal efficiency of the gas turbine to decrease. Therefore, how to use as little cold air as possible to achieve the greatest cooling effect, that is, whether the efficient and reasonable use of cold air can be organized, is a key technical indicator for measuring an advanced turbine cooling structure.

[0003] The wall cooling structure is a cooling structure used in high-temperature turbines. The cold air passes through the impingement jet, rough element turbulence and air film hole overflow in the turbine wall cooling channel in sequence. On the one hand, the heat of the inner wall is taken away by the forced impingement turbulence, and on the other hand, the heat load of the outer wall is reduced by air film insulation, which not only makes the turbine wall sufficiently cooled, but also realizes the effective organization and utilization of cooling air. Figure 2 As shown, the traditional wall cooling structure is a double-wall combined cooling form of a plane impact wall 4 and a plane impact target wall 5. Due to its large flow loss, low cooling uniformity and poor cooling effect, its application scope is greatly limited. Summary of the invention

[0004] In view of the above-mentioned shortcomings of the prior art, the technical problem to be solved by the present invention is to provide a water corrugated wall cooling structure for a gas turbine turbine with better cooling effect.

[0005] To achieve the above-mentioned purpose, the present invention provides a water corrugated wall cooling structure for a gas turbine turbine, comprising an impact wall with an impact jet hole, and an impact target wall with an air film overflow hole, a cold air flow channel is formed between the impact wall and the impact target wall, the impact jet hole and the air film overflow hole are both connected to the cold air flow channel, and the air film overflow hole is connected to the gas channel, and a corrugated surface is provided on the surface of the impact target wall facing the impact wall.

[0006] Furthermore, the impact wall and the impact target wall are connected via a support column.

[0007] Furthermore, a plurality of the air film overflow holes distributed in a rectangular array are provided on the impact target wall.

[0008] Furthermore, a plurality of impact target portions distributed in a rectangular array are provided on the impact target wall, the corrugated surface is provided on the impact target portion, and the air film overflow hole is provided between every four adjacent impact target portions distributed in a rectangular array.

[0009] Furthermore, the impact target portion is circular, the corrugated surface is a circular corrugated structure that spreads from the center of the impact target portion to the surrounding areas, and a plurality of impact jet holes are provided on the impact wall, every four impact jet holes correspond to one impact target portion, and every four impact jet holes are evenly distributed along the circumferential direction of the impact target portion.

[0010] Furthermore, the diameter of the impact jet hole is Dj, the thickness Jz of the impact wall is 1 to 3Dj, the spacing Jr between two adjacent impact jet holes corresponding to the same impact target portion is 3 to 10Dj, and the jet angle γ of the impact jet hole is 30° to 90°.

[0011] Furthermore, the thickness Tz of the impact target wall is 3-6Dj, the diameter Fj of the air film overflow hole is 1-3Dj, the distance Tr between two adjacent air film overflow holes is 5-15Dj, and the overflow angle θ of the air film overflow hole is 30°-90°.

[0012] Furthermore, the impact distance Hz between the impact wall and the impact target wall is 1 to 3Dj.

[0013] Furthermore, the wavelength Cr of the corrugated surface is 2 to 6Dj, and the amplitude Cz is 0.5 to 1.5Dj.

[0014] Furthermore, the diameter Dj of the impact jet hole is 0.3-1.5 mm.

[0015] As described above, the water corrugated wall cooling structure for gas turbine turbine according to the present invention has the following beneficial effects:

[0016] The water corrugated wall cooling structure used for the gas turbine turbine of the present invention has a corrugated surface on the surface of the impact target wall facing the impact wall. After the cold air jet flows into the cold air flow channel through the impact jet hole of the impact wall and forms a jet, the cold air jet will effectively flush the corrugated surface of the impact target wall, take away heat by forced convection, and then be sucked into the gas channel through the air film overflow hole on the impact target wall, and form a heat-insulating air film on the surface of the impact target wall, and the cooling effect is achieved by utilizing the heat absorption effect of the cold air and the heat-insulating effect of the heat-insulating air film. Moreover, since the corrugated surface is provided on the surface of the impact target wall facing the impact wall in the present invention, when the cold air jet flows through the cold air flow channel, the equivalent impact distance is reduced, the effective flushing area is increased, and the flow dead zone area is reduced, so that the utilization effectiveness of the cold air organization is improved, and the cooling effect is improved. Compared with the traditional plane wall cooling structure, the water corrugated wall cooling structure adopted by the present invention can improve the cooling effect by about 20% and reduce the flow loss by about 15%. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the structure of a gas turbine in the prior art.

[0018] Figure 2 It is a structural schematic diagram of a wall cooling structure in the prior art.

[0019] Figure 3 The schematic diagram of the water corrugated wall cooling structure used for the gas turbine turbine in the embodiment of the present invention.

[0020] Figure 4 The figure is a top view of a water corrugated wall cooling structure for a gas turbine in an embodiment of the present invention.

[0021] Figure 5 It is a front view of a water corrugated wall cooling structure for a gas turbine turbine in an embodiment of the present invention.

[0022] Figure 6 Schematic diagram of the structure of the corrugated surface in an embodiment of the present invention.

[0023] Figure 7 The present invention is a diagram showing the use status of a water corrugated wall cooling structure for a gas turbine in an embodiment of the present invention.

[0024] Figure 8 Schematic diagram of the structure of the turbine in the embodiment of the present invention.

[0025] Fig. 9 It is a flow loss comparison diagram of the water corrugated wall cooling structure located at the blade end wall in the embodiment of the present invention and the traditional plane wall cooling structure.

[0026] Fig.10 This is a comparison diagram of the cooling effects of the water corrugated wall cooling structure located at the blade end wall in an embodiment of the present invention and the traditional plane wall cooling structure.

[0027] Component number description

[0028] 1 Compressor

[0029] 2 Combustion chamber

[0030] 3 turbine

[0031] 4 Impact wall

[0032] 5 Impact on target wall

[0033] 51 Impact target

[0034] 511 Corrugated surface

[0035] 6 Impact jet hole

[0036] 7 Air film overflow hole

[0037] 8 Support columns

[0038] 9 Cold air jet

[0039] 11 Cold air flow duct

[0040] 12 Gas channel

[0041] 13 Blade end wall

[0042] 14 Leaf blade

[0043] 15 Blade top casing DETAILED DESCRIPTION

[0044] The following is a description of the implementation of the present invention by means of specific embodiments. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification.

[0045] It should be noted that the structures, proportions, sizes, etc. illustrated in the drawings of this specification are only used to match the contents disclosed in the specification for people familiar with this technology to understand and read, and are not used to limit the limiting conditions for the implementation of the present invention, so they have no substantial technical significance. Any modification of the structure, change in the proportion relationship, or adjustment of the size should still fall within the scope of the technical content disclosed by the present invention without affecting the effects and purposes that can be achieved by the present invention. At the same time, the terms such as "upper", "lower", "left", "right", "middle" and "one" quoted in this specification are only for the convenience of description, and are not used to limit the scope of the implementation of the present invention. The change or adjustment of their relative relationship should also be regarded as the scope of the implementation of the present invention without substantially changing the technical content.

[0046] like Figures 3 to 8As shown, the present invention provides a water corrugated wall cooling structure for a gas turbine, comprising an impact wall 4 having an impact jet hole 6, and an impact target wall 5 having an air film overflow hole 7, a cold air flow channel 11 is formed between the impact wall 4 and the impact target wall 5, the impact jet hole 6 and the air film overflow hole 7 are both connected to the cold air flow channel 11, and the air film overflow hole 7 is connected to the gas channel 12, and a corrugated surface 511 is provided on the surface of the impact target wall 5 facing the impact wall 4. The water corrugated wall cooling structure used for the gas turbine of the present invention has a corrugated surface 511 on the surface of the impact target wall 5 facing the impact wall 4. After the cold air jet 9 flows into the cold air flow channel 11 through the impact jet hole 6 of the impact wall 4 and forms a jet, the cold air jet 9 will effectively flush the corrugated surface 511 of the impact target wall 5, take away heat by forced convection, and then be sucked to the gas channel 12 through the air film overflow hole 7 on the impact target wall 5, and form a heat-insulating air film on the surface of the impact target wall 5, and the cooling effect is achieved by utilizing the heat absorption effect of the cold air and the heat-insulating effect of the heat-insulating air film; and because the corrugated surface 511 is provided on the surface of the impact target wall 5 facing the impact wall 4 in the present invention, when the cold air jet 9 flows through the cold air flow channel 11, the equivalent impact distance is reduced, the effective flushing area is increased, and the flow dead zone area is reduced, so that the cold air organization utilization efficiency is improved; compared with the traditional plane wall cooling structure, the water corrugated wall cooling structure adopted by the present invention can improve the cooling effect by about 20% and reduce the flow loss by about 15%.

[0047] like Figure 3 and Figure 5 As shown, in this embodiment, the impact wall 4 and the impact target wall 5 are connected by a support column 8, so as to utilize the connecting effect of the support column 8 to enhance the overall stiffness of the water corrugated wall cooling structure, thereby ensuring that the water corrugated wall cooling structure has sufficient geometric stability under the action of the high-pressure jet.

[0048] like Figure 3 and Figure 4 As shown, in this embodiment, the impact target wall 5 is provided with a plurality of air film overflow holes 7 distributed in a rectangular array. At the same time, as shown in the figure, in this embodiment, the impact target wall 5 is provided with a plurality of impact target portions 51 distributed in a rectangular array, and the impact target portion 51 is provided with the corrugated profile 51, and an air film overflow hole 7 is provided between every four adjacent impact target portions 51 distributed in a rectangular pattern. As shown in the figure, in this embodiment, the impact target portion 51 is circular, and the corrugated profile 511 is a circular corrugated structure that spreads from the center of the impact target portion 51 to the surroundings. The impact wall 4 is provided with a plurality of the impact jet holes 6, and every four impact jet holes 6 correspond to one impact target portion 51, that is, the cold air jets 9 ejected from every four impact jet holes 6 will directly impact the same impact target portion 51, and every four impact jet holes 6 are evenly distributed along the circumferential direction of the impact target portion 51. This distribution form can effectively increase the scouring area and reduce the flow dead zone area.

[0049] In this embodiment, the diameter of the impact jet hole 6 is Dj, the thickness Jz of the impact wall 4 is 1 to 3Dj, the spacing Jr between two adjacent impact jet holes 6 corresponding to the same impact target portion 51 is 3 to 10Dj, and the jet angle γ of the impact jet hole 6 is 30° to 90°. In this embodiment, the thickness Tz of the impact target wall 5 is 3 to 6Dj, the diameter Fj of the air film overflow hole 7 is 1 to 3Dj, the spacing Tr between two adjacent air film overflow holes 7 is 5 to 15Dj, and the overflow angle θ of the air film overflow hole 7 is 30° to 90°. As shown in the figure, the impact distance Hz between the impact wall 4 and the impact target wall 5 in this embodiment is 1 to 3Dj. In this embodiment, the wavelength Cr of the corrugated profile 511 is 2 to 6Dj, and the amplitude Cz is 0.5 to 1.5Dj. The peak of the corrugated profile 511 is located on the central axis of the impact jet hole 6. In this embodiment, the support column 8 is cylindrical in shape, and its diameter Hr is 1 to 3Dj. In addition, in this embodiment, the diameter Dj of the impact jet hole 6 is in the range of 0.3 to 1.5 mm.

[0050] In this embodiment, the water corrugated wall cooling structure is used to cool the turbine 3 of the gas turbine, and is specifically a water corrugated wall cooling structure for a high-temperature turbine of a gas turbine, belonging to the technical field of high-temperature turbine cooling of gas turbines, and can be applied to the efficient cooling of the blade body 14, blade end wall 13 and blade tip casing 15 of the turbine 3. In this embodiment, the turbine 3 is specifically a high-temperature turbine. Figure 8 As shown, in this embodiment, the water corrugated wall cooling structure is provided at both the blade end wall 13 and the blade tip casing 15 of the turbine 3. In other embodiments, the water corrugated wall cooling structure may be provided only at the blade end wall 13 or the blade tip casing 15.

[0051] In this embodiment, both surfaces of the impact wall 4 are smooth planes or curved surfaces, which are in contact with the cold air. All impact jet holes 6 are evenly distributed on the impact wall 4 to form a multi-hole array jet. All air film overflow holes 7 are evenly distributed on the impact target wall 5. The surface of the impact target wall 5 facing away from the impact wall 4 is a smooth plane or curved surface, which is in contact with the combustion gas. In this embodiment, the impact wall 4 and the impact target wall 5 are multiple periodic unit structures in the turning and circumferential directions of the high-temperature turbine. The corrugated surface 511 on the impact target wall 5 is a cosine wave shape in the axial direction and a circular ring shape in the circumferential direction. Compared with the traditional plane wall cooling structure, the alternating concave and convex corrugated surface 511 does not increase the weight of the components and is easy to design, process and manufacture.

[0052] In the water corrugated wall cooling structure located at the blade end wall 13 of the present embodiment, the diameter Dj of the impact jet hole 6 is specifically 0.5 mm, the thickness Jz of the impact wall 4 is specifically 2Dj, the impact distance Hz is specifically 2.5Dj, the spacing Jr is specifically 6Dj, the jet angle γ is specifically 90°, the diameter Hr of the support column 8 is specifically 1Dj, the thickness Tz of the impact target wall 5 is specifically 4Dj, the diameter Fj of the air film overflow hole 7 is specifically 2Dj, the spacing Tr is specifically 12Dj, and the overflow angle θ is specifically 90°; the corrugated surface 511 is a cosine wave shape along the axial direction, the wavelength Cr is 2Dj, and the amplitude Cz is 1Dj. The cold air jet 9 from the inner ring rotating disk cavity of the turbine 3 flows into the cold air flow channel 11 through the impact wall 4 located inside the blade end wall 13, that is, the impact jet hole 6 on the impact baffle, to form a porous array jet, which effectively flushes the impact target wall 5, that is, the inner surface of the blade end wall 13, and removes the heat of the inner surface of the blade end wall 13 through forced convection, and then is sucked into the fuel gas channel 12 through the air film overflow hole 7 on the impact target wall 5, adheres to the outer surface of the blade end wall 13 and forms a heat-insulating air film, thereby achieving effective cooling of the blade end wall 13 of the high-temperature turbine through the joint action of the inside and the outside.

[0053] Fig. 9 : is a flow loss comparison diagram of the water corrugated wall cooling structure located at the blade end wall 13 and the traditional plane wall cooling structure in the embodiment of the present invention, which shows the flow loss comparison of the water corrugated wall cooling structure located at the blade end wall 13 and the traditional plane wall cooling structure under the same aerodynamic boundary conditions. In the figure, the flow loss value is the ordinate, and the aerodynamic boundary value is the abscissa. The lines with triangular points in the figure are the change lines corresponding to the water corrugated wall cooling structure, and the lines with dots in the figure are the change lines corresponding to the traditional plane wall cooling structure; Fig.10 The figure is a comparison diagram of the cooling effect of the water corrugated wall cooling structure located at the blade end wall 13 and the traditional plane wall cooling structure in the embodiment of the present invention. The figure shows the comparison of the cooling effect of the water corrugated wall cooling structure located at the blade end wall 13 and the traditional plane wall cooling structure under the same aerodynamic boundary conditions. In the figure, the cooling effect value is the ordinate, the aerodynamic boundary value is the abscissa, the line with triangular points in the figure is the change line corresponding to the water corrugated wall cooling structure, and the line with dots in the figure is the change line corresponding to the traditional plane wall cooling structure. The water corrugated wall cooling structure of the blade end wall 13 used for the high-temperature turbine in the present embodiment reduces the flow loss by 2-5% compared with the traditional plane wall cooling structure, and improves the cooling effect by 16-18%, that is, the water corrugated wall cooling structure in the embodiment of the present invention has the beneficial performance of reducing flow resistance and significantly enhancing the cooling effect. At the same time, the support column 8 ensures that the water corrugated wall cooling structure has sufficient rigidity under the action of the high-pressure jet; the concave and convex impact target wall 5 does not increase the weight of the cooling component compared with the traditional plane target wall; it is easy to design, process and manufacture.

[0054] At the same time, in the water corrugated wall cooling structure located at the blade top casing 15 in the present embodiment, the diameter Dj of the impact jet hole 6 is specifically 0.65 mm, the thickness Jz of the impact wall 4 is specifically 2Dj, the impact distance Hz is specifically 2.5Dj, the spacing Jr is specifically 6Dj, the jet angle γ is specifically 90°, the diameter Hr of the support column 8 is specifically 1Dj, the thickness Tz of the impact target wall 5 is specifically 4Dj, the diameter Fj of the air film overflow hole 7 is specifically 2Dj, the spacing Tr is specifically 12Dj, and the overflow angle θ is specifically 90°; the corrugated surface 511 is a cosine wave shape along the axial direction, with a wavelength Cr of 4.5Dj and an amplitude Cz of 1.5Dj. The cold air jet 9 from the cold air cavity of the outer ring cylinder of the turbine 3 flows into the cold air flow channel 11 through the impact wall 4 inside the blade tip casing 15, that is, the impact jet hole 6 on the annular baffle, forming a multi-hole array jet, effectively flushing the impact target wall 5, that is, the inner surface of the blade tip casing 15, and taking away the heat of the inner surface of the blade tip casing 15 through forced convection, and then sucked to the gas channel 12 through the air film overflow hole 7 on the impact target wall 5, attached to the outer surface of the blade tip casing 15 and forming a heat-insulating air film, thereby achieving effective cooling of the blade tip casing 15 of the high-temperature turbine through the combined action of the inside and outside. The water corrugated wall cooling structure used for the blade tip casing 15 of the high-temperature turbine in this embodiment reduces the flow loss by 8-12% compared with the traditional plane wall cooling structure, and improves the cooling effect by 2-3%.

[0055] By comparing the water corrugated wall cooling structure located at the blade end wall 13 and the blade top casing 15 in this embodiment, it can be found that the enhanced cooling effect of the short-wavelength and small-amplitude water corrugated wall cooling structure is more significant, and the flow resistance reduction effect of the long-wavelength and large-amplitude water corrugated wall cooling structure is more significant.

[0056] The water corrugated wall cooling structure used for the gas turbine in this embodiment improves the cooling effect of the blade body 14, blade end wall 13 and blade top casing 15 of the high-temperature turbine, reduces the flow loss generated when the airflow passes through the wall cooling structure, and at the same time, compared with the traditional wall cooling structure, does not increase the weight of the components, the structure has sufficient rigidity, and is easy to design, process and manufacture.

[0057] In summary, the present invention effectively overcomes various shortcomings of the prior art and has high industrial utilization value.

[0058] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A water corrugated wall cooling structure for a gas turbine, characterized in that: It comprises an impact wall (4) having an impact jet hole (6) and an impact target wall (5) having an air film overflow hole (7), a cold air flow channel (11) is formed between the impact wall (4) and the impact target wall (5), the impact jet hole (6) and the air film overflow hole (7) are both in communication with the cold air flow channel (11), and the air film overflow hole (7) is in communication with a gas channel (12), and a corrugated surface (511) is provided on the surface of the impact target wall (5) facing the impact wall (4); The impact target wall (5) is provided with a plurality of impact target portions (51) distributed in a rectangular array, the impact target portion (51) is provided with the corrugated profile (511), and the air film overflow hole (7) is provided between every four adjacent impact target portions (51) distributed in a rectangular array; The impact target portion (51) is circular, the corrugated profile (511) is a circular corrugated structure that spreads from the center of the impact target portion (51) to the surroundings, and a plurality of impact jet holes (6) are provided on the impact wall (4), each four impact jet holes (6) correspond to one impact target portion (51), and each four impact jet holes (6) are evenly distributed along the circumferential direction of the impact target portion (51).

2. The water corrugated wall cooling structure for gas turbine according to claim 1, characterized in that: The impact wall (4) and the impact target wall (5) are connected via a support column (8).

3. The water corrugated wall cooling structure for gas turbine according to claim 1, characterized in that: The impact target wall (5) is provided with a plurality of air film overflow holes (7) distributed in a rectangular array.

4. The water corrugated wall cooling structure for gas turbine according to claim 1, characterized in that: The diameter of the impact jet hole (6) is Dj, the thickness Jz of the impact wall (4) is 1 to 3Dj, the spacing Jr between two adjacent impact jet holes (6) corresponding to the same impact target portion (51) is 3 to 10Dj, and the jet angle γ of the impact jet hole (6) is 30° to 90°.

5. The water corrugated wall cooling structure for gas turbine according to claim 4, characterized in that: The thickness Tz of the impact target wall (5) is 3 to 6Dj, the diameter Fj of the air film overflow hole (7) is 1 to 3Dj, the spacing Tr between two adjacent air film overflow holes (7) is 5 to 15Dj, and the overflow angle θ of the air film overflow hole (7) is 30° to 90°.

6. The water corrugated wall cooling structure for gas turbine according to claim 4, characterized in that: The impact distance Hz between the impact wall (4) and the impact target wall (5) is 1 to 3Dj.

7. The water corrugated wall cooling structure for gas turbine according to claim 4, characterized in that: The wavelength Cr of the corrugated surface (511) is 2 to 6Dj, and the amplitude Cz is 0.5 to 1.5Dj.

8. The water corrugated wall cooling structure for a gas turbine according to any one of claims 4 to 7, characterized in that: The diameter Dj of the impact jet hole (6) is 0.3-1.5 mm.

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