Turbine guide vane structure with staggered rib turbulating reinforcement

Abstract

This invention relates to the field of turbine guide vane cooling technology, specifically disclosing a turbine guide vane structure with a staggered rib turbulence enhancement structure. The turbine blade has an inner cavity at its center, into which a guide vane sleeve is inserted. Cooling gas impacts the inner cavity of the turbine blade through the guide vane sleeve. Air vents are provided on the blade crown, communicating with the inner cavity through a first ribbed channel located on the leading edge wall of the inner cavity. Staggered ribs are provided on the middle wall of the inner cavity, positioned between the guide vane sleeve and the inner cavity wall. One end of each staggered rib communicates with the first ribbed channel. The trailing edge of the inner cavity has a turbulence column structure and a slit connected sequentially. A second ribbed channel is provided on the trailing edge wall between the other end of the staggered rib and the turbulence column structure, communicating with the turbulence column structure through the second ribbed channel. This invention achieves turbulence enhancement without increasing the amount of cooling gas, thus improving the cooling effect on the turbine blade and the turbine.

Description

Technical Field

[0001] This invention relates to the field of turbine guide vane cooling technology, specifically a turbine guide vane structure with an interlaced rib turbulence-enhancing structure. Background Technology

[0002] As a core component of the hot-end of an aero-engine, the turbine guide vane operates under extreme conditions of high temperature, high pressure, and high speed, making it a critical safety component that withstands the most demanding thermal and mechanical loads. The turbine inlet temperature directly determines the engine's thermal efficiency and thrust-to-weight ratio; therefore, continuously increasing the turbine inlet temperature is one of the core driving forces behind the development of aero-engine technology. The ever-increasing turbine inlet temperature leads to increased cooling load requirements for the turbine guide vane. To ensure the structural stability of the turbine blades in the high-temperature combustion gases, cooling airflow is typically drawn from the compressor for heat dissipation. However, cooling air entering the main combustion gas stream causes mixing losses, thereby weakening the overall engine performance. Therefore, minimizing the amount of cooling air used while improving cooling efficiency has become a critical problem that urgently needs to be solved in this technological field.

[0003] In existing technologies, turbine guide vanes generally employ a cooling system combining an internal ribbed channel with external film cooling holes. The trailing edge region often incorporates a baffle structure that works in conjunction with the slits for cooling. While this composite cooling method can meet the heat dissipation requirements of turbine blades to some extent, as the turbine inlet temperature further increases, the cooling airflow must be increased to maintain the necessary cooling intensity. Practical applications show that the improvement in cooling effect is not proportional to the cooling airflow; once the flow exceeds a certain critical value, the improvement in cooling efficiency is extremely limited. This phenomenon restricts the applicability of traditional cooling structures under higher temperature conditions. Therefore, the main problem faced by existing technologies is that turbine guide vanes based on traditional cooling methods struggle to adapt to continuously rising turbine inlet temperatures without a significant increase in cooling air volume, thus failing to achieve an effective improvement in overall cooling performance. Summary of the Invention

[0004] The purpose of this invention is to provide a turbine guide vane structure with a staggered rib turbulence reinforcement structure, which solves the problem that existing turbine blade cooling design technology relies on increasing the amount of cooling air to cope with higher turbine inlet temperatures, but the cooling effect is not linearly related to the cooling air flow rate, and there is a significant point of diminishing returns.

[0005] The objective of this invention can be achieved through the following technical solutions: A turbine guide vane structure with a staggered ribbed turbulence-enhancing structure includes a blade crown, a blade root, turbine blades, and a guide vane sleeve. The turbine blades are connected directly to the blade crown and blade root. The blade crown connects the upper ends of adjacent turbine blades, and the blade root mounts the turbine blades to the casing. The turbine blades have an inner cavity at their center, and the guide vane sleeve is inserted into the inner cavity. Cooling gas impacts the inner cavity of the turbine blades through the guide vane sleeve. The blade crown has air holes that communicate with the inner cavity through a first ribbed channel located at the leading edge wall of the inner cavity. The wall surface is provided with staggered ribs, which are located between the guide vane sleeve and the wall surface of the inner cavity. One end of the staggered rib is connected to the first ribbed channel. The trailing edge of the inner cavity has a turbulence column structure and a slit connected in sequence. The other end of the staggered rib is provided on the wall surface of the trailing edge of the inner cavity between the turbulence column structure and the turbulence column structure. The other end of the staggered rib is connected to the turbulence column structure through the second ribbed channel. The first ribbed channel, the channel between the staggered rib and the guide vane sleeve, the second ribbed channel, the turbulence column structure and the slit sequentially guide the airflow entering from the air hole.

[0006] Furthermore, the interlaced ribs guide and disturb the cooling air, generating vortices and secondary flows.

[0007] Furthermore, the staggered ribs include two sets of rib structures arranged vertically, with turbulence space inside each set of rib structures. Each set of rib structures includes multiple parallel and spaced ribs, and the two sets of ribs have interlaced ribs.

[0008] Furthermore, the staggered ribs and the turbine blade cavity share the same normal in the direction perpendicular to the inner cavity wall. In the axial direction, the ribs form an angle α1 with the axial direction ranging from 30 to 60°, and the included angle α2 between the two sets of staggered ribs ranges from 80 to 100°.

[0009] Furthermore, the width between adjacent ribs is equal to the width of a single rib.

[0010] Furthermore, the first ribbed channel is provided with obliquely placed ribs, one end of which faces the air hole and the other end of which faces the interlaced ribs. The ribs at the bottom of the first ribbed channel extend through the channel outlet to the lower end of the interlaced ribs. The ribs in the first ribbed channel do not contact the ribs of the interlaced ribs.

[0011] Furthermore, the first ribbed channel is L-shaped.

[0012] Furthermore, the second ribbed channel is provided with obliquely placed ribs, one end of which faces the interlaced ribs and the other end of which faces the turbulence column structure. The ribs at the bottom of the second ribbed channel extend through the channel outlet to the lower end of the turbulence column structure. The ribs in the second ribbed channel are not in contact with the ribs of the interlaced ribs.

[0013] Furthermore, the second ribbed channel is Z-shaped.

[0014] Furthermore, a first gap is provided between the end of the staggered rib near the first channel and the upper end of the first channel to guide the airflow from the airflow outlet of the first channel to the airflow inlet at the upper end of the staggered rib; a second gap is provided between the end of the staggered rib near the second channel and the lower end of the second channel to guide the airflow from the airflow outlet at the lower end of the staggered rib to the airflow inlet of the second channel; and a third gap is provided between the end of the second channel near the turbulence column structure and the turbulence column structure to guide the airflow from the airflow outlet of the second channel to the airflow inlet at the upper end of the turbulence column structure.

[0015] The beneficial effects of this invention are: In this invention, the cooling gas at the compressor passes sequentially through air holes, a first ribbed channel, a channel between the staggered ribs and the guide vane sleeve, a second ribbed channel, a turbulence column structure, and a slit for guidance and flow. Together with the cooling gas introduced into the bottom of the turbine blade cavity through the guide vane sleeve structure, it is repeatedly disturbed and guided at the staggered ribs. The staggered ribs efficiently disrupt the boundary layer of the cooling gas, enhance fluid disturbance and turbulence, and greatly strengthen the convective heat transfer between the cooling gas and the inner wall of the turbine blade cavity, thereby improving the heat transfer capacity per unit of cooling gas. Without increasing the amount of cooling air used, a better cooling effect can be achieved, thus directly improving the utilization efficiency of the cooling medium and realizing turbulence enhancement. This invention is suitable for solving the cooling problem of turbine guide vanes when the turbine inlet temperature is increasing. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of a turbine guide vane structure with an interlaced rib deflection enhancement structure according to an embodiment of the present invention; Figure 2 This is a cross-sectional schematic diagram of the inner cavity of the turbine blade in an embodiment of the present invention; Figure 3 yes Figure 1 A top view of a turbine guide vane structure with an interlaced rib baffle reinforcement structure; Figure 4 yes Figure 3 Comparison diagram of the turbine blade's internal cavity after cross-section at point AA; Figure 5 yes Figure 3 A comparative schematic diagram of the turbine blade's internal cavity after a cross-sectional view at the middle BB section; Figure 6 It is a three-dimensional view of the fluid domain obtained based on the connection structure of the turbine blade cavity with interlaced ribs in the transition section; Reference numerals: 1. Turbine guide vane structure; 2. Blade crown; 3. Blade root; 4. Turbine blade; 5. Guide vane sleeve; 6. Orifice; 7. Interlocking ribs; 8. Inner wall of turbine blade without interlocking ribs; 9. First ribbed channel; 10. Turbine column structure; 11. Slit; 12. First gap; 13. Second gap; 14. Third gap; 15. Inner cavity; 16. Second ribbed channel; 6B. Fluid region of orifice; 7B. Fluid region at interlocking ribs; 9B. Fluid region at first ribbed channel; 10B. Fluid region at turbulence column structure; 11B. Fluid region at slit; 16B. Fluid region at second ribbed channel. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] like Figure 1 As shown, a turbine guide vane structure with an interlaced rib baffle reinforcement structure is disclosed. The turbine guide vane structure 1 includes a blade crown 2, a blade root 3, turbine blades 4, and a guide vane sleeve 5. The turbine blades 4 are connected directly to the blade crown 2 and the blade root 3. The blade crown 2 is used to connect the upper ends of adjacent turbine blades 4, and the blade root 3 is used to mount the turbine blades 4 to the casing. Figure 2 As shown, the turbine blade 4 has an inner cavity 15, and the guide vane sleeve 5 is inserted into the inner cavity 15. Cooling gas impacts the inner cavity 15 of the turbine blade 4 through the guide vane sleeve 5. The blade crown 2 is provided with air holes 6, which communicate with the inner cavity 15 through a first ribbed channel 9. The first ribbed channel 9 is located at the leading edge wall of the inner cavity 15. Interlaced ribs 7 are provided at the middle wall of the inner cavity 15, and are located between the guide vane sleeve 5 and the wall of the inner cavity 15. One end of the interlaced ribs 7 communicates with the first ribbed channel 9. The trailing edge of the inner cavity 15 has a turbulence-disrupting column structure 10 and a slit 11 arranged sequentially, wherein the turbulence-disrupting column structure 10 is as follows: Figure 2 As shown, the turbulence-enhancing column structure 10 and the slit 11 are connected. A second ribbed channel 16 is provided on the trailing edge wall of the inner cavity 15 between the other end of the staggered rib 7 and the turbulence-enhancing column structure 10. The other end of the staggered rib 7 is connected to the turbulence-enhancing column structure 10 through the second ribbed channel 16. The first ribbed channel 9, the channel between the staggered rib 7 and the guide vane sleeve 5, the second ribbed channel 16, the turbulence-enhancing column structure 10, and the slit 11 sequentially guide the airflow entering from the air hole 6. For ease of comparison, one turbine blade 4 has a turbulence-enhancing structure with staggered ribs 7 in its inner cavity 15, while the other does not have staggered ribs 7.

[0020] Its working principle is as follows: the blade crown 2 is used to stabilize the turbine blade 4, the blade root 3 installs the turbine blade 4 onto the casing, and the guide vane sleeve 5 forms the cooling airflow channel inside the turbine blade 4. The guide vane sleeve 5 usually has airflow ducts and other devices arranged inside, which is the space for cooling. The air hole 6 is used to introduce the cold air drawn from the compressor into the first ribbed channel 9. The airflow first flows through the first ribbed channel 9 at the front for preliminary cooling, and then enters the area with staggered ribs 7. This area actively disturbs the flow state of the cooling airflow, such as the cooling air that enters the bottom of the inner cavity 15 of the turbine blade 4 and is guided by the guide vane sleeve 5, as well as the cooling air that enters through the air hole 6 and the first ribbed channel 9. After being intersected by the staggered ribs 7, the diffusion intensity of the cooling air is improved. The cooling gas is repeatedly disturbed and guided by the staggered ribs 7, and the flow direction is constantly changed, generating strong vortices and secondary flows. This highly turbulent flow state significantly disrupts the thermal boundary layer near the wall, allowing the cooler gas to contact the high-temperature inner cavity wall more frequently and effectively, thereby enhancing the intensity of convective heat transfer. Therefore, compared to the smooth inner wall of a turbine blade or a conventionally structured inner cavity, this significantly improves the convective heat transfer efficiency. Figure 4 The turbine blade inner wall surface 8 shown is without interlaced ribs. The present invention can extract and remove more heat while consuming the same amount of cooling air, which significantly improves the cooling efficiency and the utilization rate of cold air.

[0021] In some embodiments, the staggered ribs 7 guide and disturb the cooling air, generating vortices and secondary flows. The generated vortices and secondary flows can produce more diffuse turbulent diffusion, which is more destructive to the thermal boundary layer of crude oil.

[0022] In some embodiments, such as Figure 2 As shown, the staggered rib 7 includes two sets of rib structures arranged vertically. The two sets of rib structures have turbulence space inside. Each set of rib structures includes multiple parallel and spaced ribs. The two sets of ribs have ribs that are staggered with each other.

[0023] In some embodiments, the staggered ribs 7 and the inner cavity 15 of the turbine blade 4 share the same normal in the direction perpendicular to the wall of the inner cavity 15. In the axial direction, the angle α1 between the ribs and the axial direction ranges from 30° to 60°, and the included angle α2 between the two sets of staggered ribs ranges from 80° to 100°. This can improve the cooling efficiency of the turbine blade 4 and the turbine guide vanes.

[0024] In some embodiments, the width of the ribs of the staggered ribs 7 is 3-4 mm, and the spacing between adjacent ribs is also 3-4 mm. In some embodiments, the thickness of a single layer of ribs of the staggered ribs 7 is 1-2 mm. In order to ensure smooth flow and structural integrity, the thickness of the double layer of ribs of the staggered ribs 7 should not exceed the distance between the guide vane sleeve 5 and the wall surface, i.e., 5 mm.

[0025] In some embodiments, the width between adjacent ribs is equal to the width of a single rib. This ensures sufficient convective heat transfer within the staggered ribs 7, preventing uneven heating and cooling convection due to rib width and the width between ribs, thus maximizing heat transfer.

[0026] In some embodiments, the first ribbed channel 9 is provided with obliquely placed ribs, one end of which faces the air vent 6 and the other end of which faces the staggered ribs 7. The ribs at the bottom of the first ribbed channel 9 extend through the channel outlet to the lower end of the staggered ribs 7, and the ribs in the first ribbed channel 9 do not contact the ribs of the staggered ribs 7. This ensures the integrity of the entire cooling system and smooth airflow. This arrangement ensures that the staggered ribs 7 can independently perform their enhanced heat exchange function, while avoiding adverse interference with the airflow characteristics of the first ribbed channel 9, thus maintaining the performance and reliability of the overall cooling structure.

[0027] In some embodiments, the first ribbed channel 9 is L-shaped. This ensures that the cooling air can fully enter the lower end of the interlaced ribs 7 of the inner cavity 15, improving the cooling effect on the interlaced ribs 7, the guide vane sleeve 5, and the inner wall.

[0028] In some embodiments, the second ribbed channel 16 is provided with obliquely placed ribs, one end of which faces the staggered ribs 7 and the other end of which faces the baffle structure 10. The ribs at the bottom of the second ribbed channel 16 extend through the channel outlet to the lower end of the baffle structure 10. The ribs in the second ribbed channel 16 do not contact the ribs of the staggered ribs 7. This ensures the independence of the airflow on the second ribbed channel 16 and the staggered ribs 7, avoiding adverse interference between their airflow characteristics.

[0029] In some embodiments, the second ribbed channel 16 is Z-shaped. The second ribbed channel 16 ensures that the cooling gas, after being further cooled by the turbulent flow of the staggered ribs 7, can flow out completely.

[0030] In some embodiments, a first gap 12 is provided between the end of the staggered rib 7 near the first channel and the upper end of the first channel to guide airflow from the airflow outlet of the first channel to the airflow inlet at the upper end of the staggered rib 7. A second gap 13 is provided between the end of the staggered rib 7 near the second channel and the lower end of the second channel to guide airflow from the airflow outlet at the lower end of the staggered rib 7 to the airflow inlet at the second channel. A third gap 14 is provided between the end of the second channel near the turbulence column structure 10 and the turbulence column structure 10 to guide airflow from the airflow outlet of the second channel to the airflow inlet at the upper end of the turbulence column structure 10. The first gap 12, the second gap 13, and the third gap 14 provide diffusion channels for the large-scale and rapid entry and exit of cooling air into the relevant components. A reasonable design of the gap dimensions can achieve better cooling performance.

[0031] In some embodiments, such as Figure 3 As shown, by performing cross-sections along sections AA and BB in the figure, the turbine guide vane 1 with the turbine sleeve removed can be obtained respectively. Figure 4 and Figure 5 A sectional view, such as Figure 5 As shown, the blade crown 2 and blade root 3 are both arc-shaped structures that bulge to one side, and the turbine blade 4 is a wedge-shaped structure.

[0032] In some embodiments, staggered ribs can be designed and installed in large, unused areas within the turbine blade cavity. This invention is applicable to, for example... Figure 1 The ultra-compact transition section turbine guide vane 1 shown is as follows: Figure 6 As shown, the fluid domain obtained based on the connection structure of the turbine blade cavity with staggered ribs includes the following sequentially arranged fluid domains: 6B of the air hole, 16B of the first ribbed channel, 7B of the staggered rib, 9B of the second ribbed channel, 10B of the turbulence column structure, and 11B of the slit.

[0033] It should be noted that the terms "first," "second," etc., used in this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this application described herein.

[0034] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0035] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed invention.

Claims

1. A turbine guide vane structure with an interlaced rib baffle reinforcement structure, comprising a blade crown (2), a blade root (3), turbine blades (4), and a guide vane sleeve (5), wherein the turbine blades (4) are connected directly to the blade crown (2) and the blade root (3), the blade crown (2) is used to connect the upper ends of adjacent turbine blades (4), and the blade root (3) is used to mount the turbine blades (4) onto the casing, characterized in that, The turbine blade (4) has an inner cavity (15) at its center. The guide vane sleeve (5) is inserted into the inner cavity (15). Cooling gas impacts the inner cavity (15) of the turbine blade (4) through the guide vane sleeve (5). The blade crown (2) is provided with air holes (6). The air holes (6) are connected to the inner cavity (15) through a first ribbed channel (9). The first ribbed channel (9) is located at the leading edge wall of the inner cavity (15). The middle wall of the inner cavity (15) is provided with staggered ribs (7). The staggered ribs (7) are located between the guide vane sleeve (5) and the wall of the inner cavity (15). One end of the staggered ribs (7) is connected to the first ribbed channel (9). The inner cavity (15) is connected, and the trailing edge of the inner cavity (15) has a turbulence column structure (10) and a split slit (11) arranged in sequence. The turbulence column structure (10) and the split slit (11) are connected. The other end of the staggered rib (7) and the turbulence column structure (10) are provided with a second ribbed channel (16) on the trailing edge wall of the inner cavity (15). The other end of the staggered rib (7) is connected to the turbulence column structure (10) through the second ribbed channel (16). The first ribbed channel (9), the channel between the staggered rib (7) and the guide vane sleeve (5), the second ribbed channel (16), the turbulence column structure (10) and the split slit (11) guide the airflow entering from the air hole (6) in sequence.

2. The turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 1, characterized in that, The interlaced ribs (7) guide and disturb the cooling air, causing vortices and secondary flows.

3. The turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 1, characterized in that, The staggered ribs (7) include two sets of rib structures arranged vertically. The two sets of rib structures have turbulence space inside. Each set of rib structures includes multiple parallel and spaced ribs. The two sets of ribs have intersecting ribs.

4. A turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 3, characterized in that, The interlaced ribs (7) and the inner cavity (15) of the turbine blade (4) share the same normal in the direction perpendicular to the wall of the inner cavity (15). In the axial direction, the ribs form an angle α1 with the axial direction ranging from 30 to 60°, and the included angle α2 between the two sets of interlaced ribs (7) ranges from 80 to 100°.

5. A turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 4, characterized in that, The width between adjacent ribs is equal to the width of a single rib.

6. A turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 1, characterized in that, The first ribbed channel (9) is provided with oblique ribs, one end of which faces the air hole (6) and the other end of which faces the intersecting rib (7). The ribs at the bottom of the first ribbed channel (9) extend through the channel outlet to the lower end of the intersecting rib (7). The ribs in the first ribbed channel (9) do not contact the ribs of the intersecting rib (7).

7. A turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 6, characterized in that, The first ribbed channel (9) is L-shaped.

8. A turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 1, characterized in that, The second ribbed channel (16) is provided with oblique ribs, one end of which faces the interlaced ribs (7) and the other end of which faces the turbulence column structure (10). The ribs at the bottom of the second ribbed channel (16) extend through the channel outlet to the lower end of the turbulence column structure (10). The ribs in the second ribbed channel (16) are not in contact with the ribs of the interlaced ribs (7).

9. A turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 8, characterized in that, The second ribbed channel (16) is Z-shaped.

10. A turbine guide vane structure with staggered ribs for enhanced aerodynamics according to claim 1, characterized in that, A first gap (12) is provided between the end of the staggered rib (7) near the first channel and the upper end of the first channel to guide the airflow from the airflow outlet of the first channel to the airflow inlet of the upper end of the staggered rib (7). A second gap (13) is provided between the end of the staggered rib (7) near the second channel and the lower end of the second channel to guide the airflow from the airflow outlet of the lower end of the staggered rib (7) to the airflow inlet of the second channel. A third gap (14) is provided between the end of the second channel near the turbulence column structure (10) and the turbulence column structure (10) to guide the airflow from the airflow outlet of the second channel to the airflow inlet of the upper end of the turbulence column structure (10).

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