Gas flow guide assembly for turbine blade of aero-engine

Abstract

The invention discloses an aero-engine turbine blade fuel gas flow guide assembly. The assembly comprises an outer shell; an inner shell of the combustion chamber is arranged in the middle position and located in the outer shell, and an outer duct is formed in the area between the outer shell and the inner shell; a carbon composite material plate is arranged in the outer duct and is fixed on the outer wall of the inner shell; the carbon composite material plate is a phenolic aldehyde ablation-resistant composite material, and the carbon composite material is located outside the combustion chamber. When high-temperature heat flow generated in the combustion chamber is conducted to the inner shell, ablation gasification occurs on the carbon composite material plate, then heat is taken away through gasified gas, meanwhile, gas protection is formed in the outer duct, the damage risk of high temperature to the outer duct is reduced, and therefore the ablation cooling effect is achieved. The temperature of high-temperature heat flow flowing to turbine blades from a combustion chamber is reduced, and the heat exchange efficiency is improved.

Description

Technical Field

[0001] The present invention relates to a gas guiding assembly for an aeroengine turbine blade, belonging to the technical field of aeroengines. Background Art

[0002] To improve the performance of the turbine and prevent the turbine blade from being destructively ablated due to high temperature and affecting the normal operation, the blade is designed as a hollow structure (see Chinese Patent Publication No. CN115111002B), and cooling air is introduced into the internal cavity of the blade for heat exchange (see Chinese Patent Publication No. CN107908816B) to ensure the safe and stable operation of the blade.

[0003] The inner cavity of the blade is usually designed as a serpentine channel to enable the cooling air to exchange heat with the inner wall of the blade. However, when designing the turning area of the serpentine channel, except for the partition that isolates the middle cavity from the two side cavities, there is no other guiding structure, resulting in the formation of vortices at the corner points on both sides of the channel elbow, making the flow velocity of the cooling air in this area relatively small and there being a problem of low heat exchange efficiency of the blade. Summary of the Invention

[0004] To solve the above technical problems, the present invention provides a gas guiding assembly for an aeroengine turbine blade.

[0005] The present invention is achieved through the following technical solutions.

[0006] A gas guiding assembly for an aeroengine turbine blade provided by the present invention includes:

[0007] A gas guiding assembly that can improve the heat exchange efficiency.

[0008] The gas guiding assembly includes: an outer housing;

[0009] An inner housing with a combustion chamber in the middle position. The inner housing is located inside the outer housing, and the area between the outer housing and the inner housing forms an outer duct;

[0010] There is a carbon composite material plate inside the outer duct. The carbon composite material plate is fixed on the outer wall of the inner housing; the carbon composite material plate is a phenolic ablative-resistant composite material, and the carbon composite material is located outside the combustion chamber.

[0011] A number of arc-shaped plates are inserted at the upper end of the carbon composite material plate. The arc-shaped plates are made of the same material as the carbon composite material plate; the end of the arc-shaped plate far from the carbon composite material plate abuts against the inner wall of the outer housing; the arc-shaped plates are arranged at equal angles along the circumferential direction of the carbon composite material plate. A number of air holes are provided inside the arc-shaped plates, and the air holes are evenly distributed on the arc-shaped plates; the arc-shaped plates bulge towards the direction of the refraction baffle plate.

[0012] A fixing frame is fixed between the outer shell and the inner shell, and the fixing frame is annular; a plurality of metal plates arranged at equal angles are fixed inside the fixing frame, and the cross section of the metal plates is wavy.

[0013] A rotating shaft is rotatably installed inside the inner shell, an air intake turbofan is fixed to the end of the rotating shaft, and a guide member is detachably fixed to the end of the inner shell away from the outer shell; the guide member includes a fixing ring fixed inside the inner shell, and the fixing ring is inclined in the same direction as the inner wall of the inner shell toward the inner side of the inner shell.

[0014] The fixed ring is rotatably connected to a guide plate, which is a plurality of guide plates rotatably mounted on the side of the fixed ring to control the size of the passing area of ​​the area surrounded by all the guide plates;

[0015] A connecting block is fixed on the inner side of each guide plate, the end of the connecting block away from the guide plate is hingedly connected to a resistance rod, and the end of the resistance rod away from the connecting block is fixedly connected to a moving block, which is ring-shaped and slides on the inner side of the fixed ring.

[0016] The end of the fixing ring away from the interference rod is rotatably connected with an adjusting rod, a fixing block is arranged outside the adjusting rod, the adjusting rod and the fixing block are connected through a threaded pair, the fixing block is fixed on the inner wall of the fixing ring, and a knob is fixed on the extending side of the fixing block of the adjusting rod.

[0017] A refraction baffle is fixed on the inner wall of the outer shell, and the end of the refraction baffle away from the outer shell abuts against the outer wall of the inner shell. The refraction baffle is inclined and is provided with a plurality of through holes, which are evenly distributed on the refraction baffle.

[0018] An inclined air inlet is provided on the inner wall of the outer shell, the inclined air inlet is located between the arc plate and the refraction baffle, the inclined air inlet is connected to an air guide channel, the end of the air guide channel away from the inclined air inlet is connected to a vertical air outlet, and a plurality of inclined air inlets are provided on the outer shell.

[0019] The air guide channel is internally connected with a rotatable rotating rod, and a spiral blade is fixed to the end of the rotating rod near the inclined air inlet, and a plurality of spiral blades are arranged along the circumference of the rotating rod. The rotating rod is conical in shape, so that the diameter of the rotating rod near the vertical air outlet is smaller than the diameter near the inclined air inlet.

[0020] The beneficial effects of the present invention are as follows: When the high-temperature heat generated inside the combustion chamber is conducted to the inner shell, ablation and gasification occur on the carbon composite material plate. Then, the heat is carried away by the gasified gas, and at the same time, a gas protection is formed inside the bypass duct to reduce the risk of damage to the bypass duct caused by high temperature, thereby achieving the ablation cooling effect; the temperature of the high-temperature heat flow flowing from the combustion chamber to the turbine blade is reduced, and combined with the serpentine channels designed inside the blade, the heat transfer and cooling efficiency of the blade is improved, solving the problem of low heat transfer efficiency of the blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic structural diagram of the present invention from the left front perspective;

[0022] Figure 2 is a schematic structural diagram of the present invention from the right rear perspective;

[0023] Figure 3 is a schematic diagram of the main view semi-section of the present invention;

[0024] Figure 4 is Figure 3 the sectional view taken along line A-A in

[0025] Figure 5 is Figure 2 the partial enlarged schematic diagram at A in

[0026] Figure 6 is Figure 4 the partial enlarged schematic diagram at B in

[0027] In the figure: 1 - outer shell; 2 - inner shell; 3 - bypass duct; 4 - combustion chamber; 5 - rotating shaft; 6 - inlet air turbine fan; 7 - fixing ring; 8 - deflector; 9 - carbon composite material plate; 10 - connecting block; 11 - abutting rod; 12 - moving block; 13 - adjusting rod; 14 - fixing block; 15 - knob; 16 - arc plate; 17 - air hole; 18 - refracting baffle; 19 - through hole; 20 - inclined air inlet; 21 - air guiding channel; 22 - vertical air outlet; 23 - rotating rod; 24 - spiral blade; 25 - fixing frame; 26 - metal plate. DETAILED DESCRIPTION OF THE INVENTION

[0028] The technical solution of the present invention will be further described below, but the scope of protection claimed is not limited thereto.

[0029] As Figures 1 to 6 shown.

[0030] A gas guiding assembly for a turbine blade of an aeroengine according to the present application includes:

[0031] outer shell 1;

[0032] The middle position is the inner shell 2 of the combustion chamber 4. The inner shell 2 is located inside the outer shell 1, and the area between the outer shell 1 and the inner shell 2 forms the outer duct 3; a turbine is installed at the rear position of the combustion chamber 4.

[0033] Inside the outer duct 3, there is a carbon composite material plate 9, and the carbon composite material plate 9 is fixed on the outer wall of the inner shell 2; the carbon composite material plate 9 is made of phenolic ablative-resistant composite material. The carbon composite material is located outside the combustion chamber 4. When the high-temperature heat generated inside the combustion chamber 4 conducts to the inner shell 2, ablation and gasification occur on the carbon composite material plate 9, and then the heat is carried away by the gasified gas. At the same time, a gas protection is formed inside the outer duct 3, reducing the risk of damage to the outer duct 3 by high temperature, thereby achieving the ablation cooling effect; the high-temperature heat flow flowing from the combustion chamber to the turbine blade is cooled, combined with the serpentine channels designed inside the blade, to improve the blade cooling heat transfer efficiency and solve the problem of low heat transfer efficiency of the blade.

[0034] A fixing frame 25 is fixed between the outer shell 1 and the inner shell 2, and the fixing frame 25 is annular; several metal plates 26 arranged at equal angles are fixed inside the fixing frame 25, and the cross-section of the metal plate 26 is wavy.

[0035] A rotating shaft 5 is rotatably installed inside the inner shell 2, and an air inlet turbine fan 6 is fixed at the end of the rotating shaft 5. A guide member is detachably fixed at the end of the inner shell 2 far from the outer shell 1; the guide member includes a fixing ring 7 fixed inside the inner shell 2 by screws, and the side of the fixing ring 7 facing the inside of the inner shell 2 is in the same inclined direction as the inner wall of the inner shell 2.

[0036] A guide vane 8 is rotatably connected to the side of the fixing ring 7. There are several guide vanes 8 that can rotate on the side of the fixing ring 7 to control the passing area of the area surrounded by all the guide vanes 8; the cross-section of the guide vane 8 is triangular.

[0037] A connecting block 10 is fixed inside each guide vane 8. A resisting rod 11 is hinged to the end of the connecting block 10 far from the guide vane 8, and a moving block 12 is fixedly connected to the end of the resisting rod 11 far from the connecting block 10. The moving block 12 is annular and slides inside the fixing ring 7.

[0038] An adjusting rod 13 is rotatably connected to the end of the fixing ring 7 far from the resisting rod 11. A fixing block 14 is provided outside the adjusting rod 13, and the adjusting rod 13 and the fixing block 14 are connected through a threaded pair. The fixing block 14 is fixed on the inner wall of the fixing ring 7, and a knob 15 is fixed on the side where the adjusting rod 13 extends out of the fixing block 14.

[0039] When the knob 15 rotates, the knob 15 can drive the adjusting rod 13 to rotate. After the adjusting rod 13 rotates, since the adjusting rod 13 and the fixed block 14 are connected through a threaded pair, at this time, the adjusting rod 13 can move along the fixed block 14. Through the spherical joint between the adjusting rod 13 and the moving block 12, the adjusting rod 13 drives the moving block 12 to slide within the fixed ring 7, and then drives the abutting rod 11 to move towards the end of the deflector 8. When the abutting rod 11 abuts against the deflector 8, it can drive the deflector 8 to rotate, thereby changing the passing area of the area surrounded by all the deflectors 8. When the above passing area is smaller, the amount of heat flow exported is more compressed, and thus the jet speed is faster, which can quickly divert the flow while increasing the jet power.

[0040] A plurality of arc-shaped plates 16 are inserted into the upper end of the carbon composite material plate 9, and the arc-shaped plates 16 are made of the same material as the carbon composite material plate 9; the end of the arc-shaped plate 16 away from the carbon composite material plate 9 abuts against the inner wall of the outer casing 1; the arc-shaped plates 16 are provided in several at equal angles along the circumferential direction of the carbon composite material plate 9, and a plurality of air holes 17 are provided inside the arc-shaped plates 16, and the air holes 17 are evenly distributed on the arc-shaped plates 16.

[0041] A refraction baffle 18 is fixed on the inner wall of the outer casing 1 by screws. The end of the refraction baffle 18 away from the outer casing 1 abuts against the outer wall of the inner casing 2. The refraction baffle 18 is inclined. A plurality of through holes 19 are provided on the refraction baffle 18, and the through holes 19 are evenly distributed on the refraction baffle 18. The distance between the through holes 19 is 25 cm.

[0042] The arc-shaped plate 16 protrudes towards the refraction baffle 18.

[0043] While inhaling air, a part of the external air enters the outer duct 3 along the metal plate 26, contacts the gas after ablation and gasification after passing through the arc-shaped plate 16, and then the gas filling the inside of the outer duct 3 is carried by the cold air at the air inlet to flow towards the refraction baffle 18.

[0044] Among them, the protruding direction of the arc-shaped plate 16 is set towards the refraction baffle 18, and air holes 17 are provided thereon to facilitate the entry of air. At the same time, the arc-shaped plate 16 can further increase the amount of gas generated by ablation and gasification. Since the arc-shaped plate 16 is convexly arranged, the contact area with the heat flow increases, and thus a large amount of heat can be quickly carried out, improving the heat dissipation performance of the outer duct 3.

[0045] An inclined air inlet 20 is provided on the inner wall of the outer casing 1. The inclined air inlet 20 is located between the arc-shaped plate 16 and the refraction baffle 18. The inclined air inlet 20 is communicated with a gas guiding channel 21. The end of the gas guiding channel 21 away from the inclined air inlet 20 is communicated with a vertical air outlet 22. A plurality of inclined air inlets 20 are provided on the outer casing 1.

[0046] A rotatable rotating rod 23 is connected inside the air guiding channel 21. A spiral blade 24 is fixed to the end of the rotating rod 23 close to the inclined air inlet 20. A plurality of spiral blades 24 are provided along the circumferential direction of the rotating rod 23. The rotating rod 23 is conical, so that the diameter of the rotating rod 23 at the end close to the vertical air outlet 22 is smaller than the diameter at the end close to the inclined air inlet 20.

[0047] The gas of the impact refraction baffle 18 flows back after being impacted. Since the air always enters along the outer duct 3, the flowing-back gas enters along the inclined air inlet 20 and impacts the spiral blade 24 inside the air guiding channel 21. The spiral blade 24 starts to rotate after being impacted, and then drives the rotating rod 23 to rotate. Since the rotating rod 23 is arranged in a conical shape, the gas outlet is accelerated. The gas is led out through the vertical air outlet 22 to the air inlet turbine fan 6, and then can carry the hot air with a certain amount of residual heat. The hot air enters the inner housing 2 again with the rotation of the air inlet turbine fan 6. Therefore, in the present invention, the heat radiated by the combustion chamber 4 inside the outer duct 3 can be quickly led out, and the led-out heat is conveyed back to the inside of the inner housing 2 again. While protecting the outer duct 3, the heat supply efficiency of the combustion chamber 4 can be improved.

Claims

1. A gas guide assembly for an aircraft engine turbine blade, characterized in that: include: A gas flow guide component capable of improving heat exchange efficiency.

2. The aircraft engine turbine blade gas guide assembly according to claim 1, characterized in that: The gas flow guide assembly comprises: an outer shell (1); The middle part is an inner shell (2) of a combustion chamber (4), the inner shell (2) is located inside the outer shell (1), and the area between the outer shell (1) and the inner shell (2) constitutes an outer duct (3); A carbon composite material plate (9) is provided inside the outer duct (3), and the carbon composite material plate (9) is fixed on the outer wall of the inner shell (2); the carbon composite material plate (9) is a phenolic ablation-resistant composite material, and the carbon composite material is located outside the combustion chamber (4).

3. The aircraft engine turbine blade gas guide assembly according to claim 2, characterized in that: A plurality of arc-shaped plates (16) are inserted at the upper end of the carbon composite plate (9), and the arc-shaped plates (16) are made of the same material as the carbon composite plate (9); the end of the arc-shaped plate (16) away from the carbon composite plate (9) contacts the inner wall of the outer shell (1); the arc-shaped plates (16) are arranged at equal angles along the circumferential direction of the carbon composite plate (9), and a plurality of air holes (17) are arranged inside the arc-shaped plates (16), and the air holes (17) are evenly distributed on the arc-shaped plates (16); and the arc-shaped plates (16) protrude toward the direction of the refraction baffle (18).

4. The aircraft engine turbine blade gas guide assembly according to claim 2, characterized in that: A fixing frame (25) is fixed between the outer shell (1) and the inner shell (2), and the fixing frame (25) is annular; a plurality of metal plates (26) arranged at equal angles are fixed inside the fixing frame (25), and the cross section of the metal plates (26) is wavy.

5. The aircraft engine turbine blade gas guide assembly according to claim 2, characterized in that: A rotating shaft (5) is rotatably mounted inside the inner shell (2), an air intake turbofan (6) is fixed to the end of the rotating shaft (5), and a flow guide is detachably fixed to the end of the inner shell (2) away from the outer shell (1); the flow guide comprises a fixing ring (7) fixed inside the inner shell (2), and the fixing ring (7) is inclined in the same direction as the inner wall of the inner shell (2) toward the inner side of the inner shell (2).

6. The aircraft engine turbine blade gas guide assembly according to claim 5, characterized in that: The fixed ring (7) is rotatably connected to a guide plate (8), and the guide plates (8) are a plurality of guide plates rotatably mounted on the side of the fixed ring (7) to control the size of the passing area of ​​the area surrounded by all the guide plates (8); A connecting block (10) is fixed on the inner side of each guide plate (8); an end of the connecting block (10) away from the guide plate (8) is hingedly connected to a resistance rod (11); an end of the resistance rod (11) away from the connecting block (10) is fixedly connected to a moving block (12); the moving block (12) is ring-shaped and slides on the inner side of the fixing ring (7).

7. The aircraft engine turbine blade gas guide assembly according to claim 6, characterized in that: The end of the fixing ring (7) away from the interference rod (11) is rotatably connected with an adjusting rod (13), a fixing block (14) is arranged outside the adjusting rod (13), the adjusting rod (13) and the fixing block (14) are connected through a threaded pair, the fixing block (14) is fixed on the inner wall of the fixing ring (7), and a knob (15) is fixed on the side of the adjusting rod (13) extending from the fixing block (14).

8. The aircraft engine turbine blade gas guide assembly according to claim 2, characterized in that: A refraction baffle (18) is fixed on the inner wall of the outer shell (1), and the end of the refraction baffle (18) away from the outer shell (1) abuts against the outer wall of the inner shell (2). The refraction baffle (18) is arranged obliquely, and a plurality of through holes (19) are provided on the refraction baffle (18), and the through holes (19) are evenly distributed on the refraction baffle (18).

9. The aircraft engine turbine blade gas guide assembly according to claim 2, characterized in that: An inclined air inlet (20) is provided on the inner wall of the outer shell (1), the inclined air inlet (20) is located between the arc-shaped plate (16) and the refraction baffle plate (18), the inclined air inlet (20) is connected to an air guide channel (21), and the end of the air guide channel (21) away from the inclined air inlet (20) is connected to a vertical air outlet (22), and a plurality of inclined air inlets (20) are provided on the outer shell (1).

10. The aircraft engine turbine blade gas guide assembly according to claim 9, characterized in that: The air guide channel (21) is internally connected with a rotatable rotating rod (23), and a spiral blade (24) is fixed to the end of the rotating rod (23) close to the inclined air inlet (20), and a plurality of spiral blades (24) are arranged along the circumference of the rotating rod (23). The rotating rod (23) is conical in shape, so that the diameter of the rotating rod (23) close to the vertical air outlet (22) is smaller than the diameter of the end close to the inclined air inlet (20).

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