Multi-level cooling structure for turbine blade of aero-engine

Abstract

The invention discloses an aero-engine turbine blade multi-level cooling structure, and belongs to the technical field of cooling blades, the aero-engine turbine blade multi-level cooling structure comprises a blade basin and a blade back, a cavity is arranged between the blade basin and the blade back, a first diversion trench and a second diversion trench which are communicated with each other are arranged in the blade basin, and a first air inlet hole is formed in the outer wall of the blade basin; the first air inlet is communicated with the first flow guide groove, and a second air inlet is formed in the inner wall of the blade basin and communicated with the second flow guide groove. According to the multi-level cooling structure for the turbine blade of the aero-engine, the first flow guide groove and the second flow guide groove are formed, and a cooling medium enters the first flow guide groove and the second flow guide groove through the first air inlet holes, so that the entering cooling medium can be quickly diffused to cool the blade basin; and meanwhile, the cooling medium enters the cavity through the second air inlet hole for cooling.

Description

Technical Field

[0001] This invention relates to the field of cooling blade technology, and in particular to a multi-stage cooling structure for aero-engine turbine blades. Background Technology

[0002] Turbine blades are one of the core components of aero-engines, enduring intense scouring from high-temperature exhaust gases and high thermal loads during operation. With the continuous increase in the thrust-to-weight ratio of aero-engines, the turbine inlet temperature has also risen significantly, placing higher demands on the high-temperature resistance and cooling efficiency of turbine blades.

[0003] Currently, existing cooling structures for aero-engine turbine blades mainly include single or combined cooling methods such as film cooling, impingement cooling, and convection cooling. However, these cooling structures have some shortcomings: on the one hand, the flow path design of the cooling medium inside the blade is not reasonable enough, resulting in low cooling efficiency and difficulty in uniformly and effectively cooling various high-temperature areas of the blade; on the other hand, some cooling structures are too complex, difficult to manufacture, and have a certain impact on the structural strength of the blade, reducing its service life. Summary of the Invention

[0004] The purpose of this invention is to provide a multi-stage cooling structure for aero-engine turbine blades. By setting a first guide channel and a second guide channel, the cooling medium enters the first guide channel and the second guide channel through the first air inlet, so that the entering cooling medium can diffuse rapidly and cool the blade housing. At the same time, the cooling medium enters the cavity through the second air inlet for cooling. By setting baffles with protrusions and grooves on the ribs, the heat exchange area is increased, the turbulence effect is enhanced, and the heat exchange rate is improved.

[0005] To achieve the above objectives, the present invention provides a multi-stage cooling structure for aero-engine turbine blades, including a blade basin and a blade back. The blade basin is connected to the blade back, and a cavity is provided between the blade basin and the blade back. A first guide groove and a second guide groove are provided inside the blade basin, and the first guide groove and the second guide groove are connected. A first air inlet is provided on the outer wall of the blade basin, and the first air inlet is connected to the first guide groove. A second air inlet is provided on the inner wall of the blade basin, and the second air inlet is connected to the second guide groove.

[0006] Preferably, a rib is provided inside the cavity, the top end of the rib is connected to the leaf basin, and the bottom end of the rib is connected to the back of the leaf.

[0007] Preferably, the sidewall of the rib is provided with baffles to increase the heat exchange area.

[0008] Preferably, the baffle is provided with protrusions for increasing the heat exchange area.

[0009] Preferably, the baffle is provided with a groove for increasing the heat exchange area.

[0010] Preferably, the outer wall of the leaf basin is provided with a flow guide strip.

[0011] Preferably, a connecting frame is provided around the leaf basin, and the bottom end of the inner side wall of the connecting frame is connected to the back of the leaf.

[0012] Preferably, an air vent is provided on the rear end of the connecting frame.

[0013] Preferably, both the first guide channel and the second guide channel have a serpentine structure.

[0014] Preferably, both the leaf base and the leaf back are arc-shaped structures.

[0015] Therefore, the present invention adopts the above-mentioned multi-stage cooling structure for aero-engine turbine blades. By setting a first guide channel and a second guide channel, the cooling medium enters the first guide channel and the second guide channel through the first air inlet, so that the entering cooling medium can diffuse rapidly and cool the blade basin. At the same time, the cooling medium enters the cavity through the second air inlet for cooling. By setting baffles with protrusions and grooves on the ribs, the heat exchange area is increased, the turbulence effect is enhanced, and the heat exchange rate is improved.

[0016] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0017] Figure 1 This is a frontal view of the overall structure of the multi-stage cooling structure for aero-engine turbine blades in this invention.

[0018] Figure 2 This is a cross-sectional view of the internal structure of the multi-stage cooling structure for aero-engine turbine blades in this invention.

[0019] Figure 3 This is a cross-sectional view of the internal structure of the leaf basin in this invention;

[0020] Figure 4 This is a schematic diagram of the specific structure of the rib and baffle in this invention;

[0021] Figure 5 This is an enlarged view of point A in this invention.

[0022] Figure Labels

[0023] 1. Leaf basin; 2. Leaf back; 3. Cavity; 4. First guide groove; 5. Second guide groove; 6. First air inlet; 7. Second air inlet; 8. Rib; 9. Baffle; 10. Protrusion; 11. Groove; 12. Guide strip; 13. Connecting frame; 14. Air outlet. Detailed Implementation

[0024] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0025] Unless otherwise defined, the technical or scientific terms used in this invention shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0026] like Figures 1-5 As shown, a multi-stage cooling structure for an aero-engine turbine blade includes a blade basin 1 and a blade back 2. The blade basin 1 and the blade back 2 are connected to each other, and a cavity 3 is provided between the blade basin 1 and the blade back 2. Preferably, both the blade basin 1 and the blade back 2 are arc-shaped structures. A first guide groove 4 and a second guide groove 5 are provided inside the blade basin 1. The first guide groove 4 and the second guide groove 5 are perpendicular to each other inside the blade basin 1. The bottom surface of the first guide groove 4 is in contact with the top surface of the second guide groove 5, and the first guide groove 4 and the second guide groove 5 are connected. Preferably, both the first guide groove 4 and the second guide groove 5 are serpentine structures. A plurality of first air inlets 6 are evenly spaced on the outer wall of the blade basin 1. The bottom end of the first air inlet 6 is connected to the top surface of the first guide groove 4. A plurality of second air inlets 7 are evenly spaced on the inner wall of the blade basin 1. The top end of the second air inlet 7 is connected to the bottom surface of the second guide groove 5.

[0027] The cooling medium enters the interior of the first guide groove 4 and the second guide groove 5 through the first air inlet 6 in sequence, so that the cooling medium can diffuse rapidly and cool the blade 1. At the same time, the cooling medium diffuses to the second air inlets 7 in various parts through the first guide groove 4 and the second guide groove 5, so that the second air inlets 7 in various parts can deliver the cooling medium into the cavity 3, so that the cavity 3 is cooled evenly and the heat exchange rate is improved.

[0028] The cavity 3 has several ribs 8 welded inside. The top of the ribs 8 is welded to the inner wall of the blade basin 1, and the bottom of the ribs 8 is welded to the inner wall of the blade back 2. The ribs 8 divide the cavity 3 into multiple chambers. The top of each chamber corresponds to several second air inlets 7, ensuring that the cooling medium enters the interior of each chamber evenly.

[0029] The sidewall of the rib plate 8 is welded with several baffles 9 at even intervals. The baffles 9 are used to increase the heat exchange area. The sidewall of the baffles 9 is also welded with several protrusions 10 and several grooves 11 at even intervals. Both the protrusions 10 and the grooves 11 are used to increase the heat exchange area, enhance the turbulence effect, and improve the heat exchange rate.

[0030] Several guide strips 12 are welded evenly at intervals on the outer wall of the blade basin 1 near the air inlet. The guide strips 12 are used to guide the cooling medium into the first air inlet 6.

[0031] A connecting frame 13 is welded between the blade basin 1 and the blade back 2. The top of the inner side wall of the connecting frame 13 is welded to the blade basin 1, and the bottom of the inner side wall of the connecting frame 13 is welded to the blade back 2. Several air outlet holes 14 are evenly spaced at the rear end of the connecting frame 13, so that a complete cooling circuit is formed inside the cavity 3 to avoid heat accumulation.

[0032] Working principle:

[0033] The cooling medium is first guided by several guide strips 12 welded to the outer wall of the blade basin 1, and then enters the several first air inlets 6 evenly spaced on the outer wall of the blade basin 1 with precision and efficiency. Then, the cooling medium enters the first guide groove 4 opened inside the blade basin 1 through the bottom end of the first air inlet 6. Since the first guide groove 4 is connected to the second guide groove 5 arranged vertically below it, the cooling medium extends the flow path under the guidance of the serpentine structure, and at the same time achieves rapid diffusion, forming a comprehensive enveloping cooling of the internal structure of the blade basin 1, and fully removing the heat of the blade basin 1.

[0034] The cooling medium flowing in the first guide groove 4 and the second guide groove 5 is further distributed evenly to the cavity 3 formed between the blade basin 1 and the blade back 2 through a number of second air inlets 7 evenly spaced on the inner wall of the blade basin 1, so as to achieve preliminary cooling of the cavity 3 and the inner wall of the blade basin 1.

[0035] The ribs 8 welded inside the cavity 3 serve a dual function of support and heat exchange. The baffles 9 welded evenly at intervals on the sidewalls of the ribs 9, as well as the protrusions 10 and grooves 11 evenly spaced on the sidewalls of the baffles 9, greatly increase the contact area between the cooling medium and the structure. At the same time, the irregular layout of the protrusions 10 and grooves 11 enhances the turbulence effect of the cooling medium in the cavity 3, promotes sufficient heat exchange between the cooling medium and the ribs 8, baffles 9 and the inner wall of the blade back 2, significantly improves the overall heat exchange rate, and ensures uniform cooling inside the cavity 3 and the blade back 2.

[0036] The cooling medium that has completed heat exchange forms a stable airflow in the cavity 3 and is discharged through a number of evenly spaced air outlets 14 at the rear end of the connecting frame 13 welded between the blade basin 1 and the blade back 2.

[0037] The present invention provides a multi-level cooling structure for aero-engine turbine blades, which forms a complete closed-loop cooling circuit consisting of "guide strip 12 for guiding - first air inlet 6 for air intake - first guide groove 4 and second guide groove 5 for layered cooling - second air inlet 7 for diverting to cavity 3 - rib plate 8, baffle 9, protrusion 10 and groove 11 inside cavity 3 for enhanced heat exchange - exhaust port 14 for exhaust". This effectively avoids heat accumulation caused by the retention of cooling medium inside the structure, and ultimately achieves multi-level, all-round, uniform and efficient cooling of the entire aero-engine turbine blade, ensuring stable blade operation.

[0038] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A multi-stage cooling structure for aero-engine turbine blades, characterized in that: It includes a leaf basin and a leaf back, the leaf basin is connected to the leaf back, a cavity is provided between the leaf basin and the leaf back, the leaf basin is provided with a first guide groove and a second guide groove inside, the first guide groove and the second guide groove are connected, the outer wall of the leaf basin is provided with a first air inlet hole, the first air inlet hole is connected to the first guide groove, and the inner wall of the leaf basin is provided with a second air inlet hole, the second air inlet hole is connected to the second guide groove.

2. The multi-stage cooling structure for aero-engine turbine blades according to claim 1, characterized in that: The cavity is provided with a rib plate, the top of which is connected to the leaf basin and the bottom of which is connected to the back of the leaf.

3. The multi-stage cooling structure for aero-engine turbine blades according to claim 2, characterized in that: The sidewalls of the ribs are provided with baffles to increase the heat exchange area.

4. The multi-stage cooling structure for aero-engine turbine blades according to claim 3, characterized in that: The baffle is provided with protrusions to increase the heat exchange area.

5. The multi-stage cooling structure for aero-engine turbine blades according to claim 3, characterized in that: The baffle is provided with grooves to increase the heat exchange area.

6. The multi-stage cooling structure for aero-engine turbine blades according to claim 1, characterized in that: The outer wall of the leaf basin is provided with flow guide strips.

7. The multi-stage cooling structure for aero-engine turbine blades according to claim 1, characterized in that: A connecting frame is provided around the leaf basin, and the bottom of the inner side wall of the connecting frame is connected to the back of the leaf.

8. The multi-stage cooling structure for aero-engine turbine blades according to claim 7, characterized in that: An air vent is provided at the rear end of the connecting frame.

9. The multi-stage cooling structure for aero-engine turbine blades according to claim 1, characterized in that: Both the first and second guide channels have a serpentine structure.

10. The multi-stage cooling structure for aero-engine turbine blades according to claim 1, characterized in that: Both the leaf base and the back of the leaf are arc-shaped structures.

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