Inlet guide vane of gas compressor

Abstract

The invention belongs to the technical field of guide vanes, and provides a compressor inlet guide vane which comprises a guide vane handle, a guide vane body and a connecting structure which are integrally formed, and the guide vane handle and the connecting structure are arranged at the two opposite ends of the guide vane body respectively. A vent hole is formed in the end part of the guide vane; a first heat exchange cavity and a second heat exchange cavity which are communicated with each other are formed in the guide vane; the vent hole is communicated with the guide vane handle and the first heat exchange cavity; an exhaust window is formed in the outer surface of the guide vane and communicates with the second heat exchange cavity. The guide vane handle, the guide vane and the connecting structure are integrally formed, so that procedures and machining are reduced, and the cost is reduced; through integral forming, no special processes such as brazing are realized, no welding defect is introduced, and the reliability can be improved; and meanwhile, the part machining period is shortened, the percent of pass can be greatly increased, and the cost can be effectively controlled.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, and specifically relates to a compressor inlet guide vane. Background Technology

[0002] To ensure the stability and safety of aero-engines operating at high altitudes, anti-icing guide vanes are required at the compressor inlet. High-temperature, high-pressure air enters the guide vanes and heats them, thus achieving the anti-icing effect. To ensure the manufacturability of the internal heat exchange cavity structure, existing compressor inlet guide vanes employ a split design, mainly composed of the blade body, cover plate, and blade shank. Figure 1 As shown, the blade body and cover plate are made of copper alloy, and the blade shank is made of stainless steel. Existing compressor inlet anti-icing guide vanes are mainly constructed by brazing the blade body, cover plate, and blade shank. Specific welding locations are shown in [reference needed]. Figure 2 The blade is brazed to the cover plate and the blade stalk, which places high demands on brazing technology, process and equipment. At the same time, because the chamber is a semi-enclosed cavity and the space is small, the solder accumulated in the cavity and exhaust window cannot be removed, blocking the airflow channel. This results in low part qualification rate, long processing cycle, high cost, and the anti-icing effect does not meet the design requirements. It will also affect engine performance and operational safety.

[0003] Therefore, an integrated, molded guide vane structure is needed. Summary of the Invention

[0004] To address the aforementioned problems, this invention proposes a compressor inlet guide vane, comprising an integrally formed guide vane shank, a guide vane, and a connecting structure, wherein the guide vane shank and the connecting structure are respectively disposed at opposite ends of the guide vane. The guide vane has a vent hole at its end and a first heat exchange chamber and a second heat exchange chamber that are interconnected. The vent hole connects the guide vane stalk and the first heat exchange chamber. An exhaust window is provided on the outer surface of the guide vane and is connected to the second heat exchange chamber.

[0005] Furthermore, the outer surface of the guide vane is provided with a first surface and a second surface that are connected by a transition. The first surface is curved and the second surface is flat. An exhaust window is provided on the second surface.

[0006] Furthermore, the guide vane petiole, guide vane, and connecting structure are manufactured using additive manufacturing technology.

[0007] Furthermore, the guide vane shank includes a threaded section, a rocker arm mounting section, a first support section, and a first connecting section connected in sequence; a circular vent hole is provided on the side of the first support section, and a square vent hole communicating with the circular vent hole is provided inside the first connecting section and the first support section, with the other end of the square vent hole communicating with the vent hole.

[0008] Furthermore, the threaded section, rocker arm mounting section, and first support section are all made of stainless steel, while the first connecting section is made of copper alloy. A mixed zone of stainless steel and high thermal conductivity copper alloy is formed at the connection between the first support section and the first connecting section.

[0009] Furthermore, the connecting structure includes a second connecting section and a second support section that are interconnected, with the second connecting section connected to the guide vane.

[0010] Furthermore, a heat exchange rib is provided in the first heat exchange cavity, and the heat exchange rib is fixedly connected to the first surface.

[0011] Furthermore, there are gaps between the heat exchange ribs and the inner surface and the second surface of the first heat exchange cavity.

[0012] Furthermore, the second heat exchange cavity is provided with a number of linearly arrayed heat exchange columns, all of which are fixedly connected to the first surface.

[0013] Furthermore, there are gaps between the heat exchange column and the inner surface and the second surface of the second heat exchange chamber.

[0014] Furthermore, the first heat exchange chamber and the second heat exchange chamber are connected at the end away from the vent.

[0015] Beneficial effects 1. A compressor inlet guide vane of the present invention includes an integrally formed guide vane shank, a guide vane, and a connecting structure, wherein the guide vane shank and the connecting structure are respectively disposed at opposite ends of the guide vane; by integrally forming the guide vane shank, the guide vane, and the connecting structure, the number of processes and machining is reduced, thereby reducing costs; through integral forming, special processes such as brazing are eliminated, thus eliminating the introduction of welding defects and improving reliability; at the same time, the parts processing cycle is shortened, the pass rate is significantly improved, and costs can be effectively controlled.

[0016] 2. The compressor inlet guide vane of the present invention improves the heat conduction efficiency of the guide vane by setting heat exchange ribs and heat exchange columns in the guide vane, thereby achieving high-efficiency heat conduction and de-icing; thus, the heat exchange effect can be greatly improved while the external profile remains completely unchanged, and the external hot air demand will also be reduced, further improving engine performance and life.

[0017] 3. The guide vane shank, guide vane and connecting structure of the compressor inlet guide vane of the present invention are made by additive manufacturing technology; which can not only improve the anti-icing heat exchange effect, but also shorten the production cycle, reduce processing costs and ensure the safe operation of the engine.

[0018] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description and the drawings. Attached Figure Description

[0019] 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.

[0020] Figure 1 A schematic diagram of the hot air flow path inside the anti-icing guide vanes of a typical compressor is shown.

[0021] Figure 2 A schematic diagram showing the location of brazing filler metal residue inside a typical compressor anti-icing guide vane is shown.

[0022] Figure 3 A schematic diagram of the overall device of the compressor inlet guide vane in an embodiment of the present invention is shown.

[0023] Figure 4 A schematic diagram of the hot air flow path inside the compressor inlet guide vane in an embodiment of the present invention is shown.

[0024] Figure 5 A schematic diagram of the guide vane shank structure of the compressor inlet guide vane in an embodiment of the present invention is shown.

[0025] Figure 6 A cross-sectional structural diagram of the guide vane shank of the compressor inlet guide vane in an embodiment of the present invention is shown.

[0026] Figure 7 A partial cross-sectional view of the guide vane shank of the compressor inlet guide vane in an embodiment of the present invention is shown.

[0027] Figure 8 A schematic cross-sectional view of the guide vane of the compressor inlet guide vane in an embodiment of the present invention is shown.

[0028] Figure 9 A schematic diagram of the transverse cross-sectional structure of the compressor inlet guide vane in an embodiment of the present invention is shown.

[0029] Figure 10 A schematic diagram of the connection structure of the compressor inlet guide vane in an embodiment of the present invention is shown.

[0030] Figure 11 A schematic diagram of the installation of the anti-icing guide vane at the compressor inlet of the present invention is shown.

[0031] Figure 12 A schematic diagram of the temperature distribution of a typical compressor inlet anti-icing guide vane is shown.

[0032] Figure 13 A schematic diagram of the temperature distribution of the compressor inlet guide vanes in an embodiment of the present invention is shown.

[0033] In the diagram, 10 is the guide vane stalk; 11 is the threaded section; 12 is the rocker arm mounting section; 13 is the circular vent hole; 14 is the first support section; 15 is the square vent hole; and 16 is the first connecting section. 20. Guide vane; 21. Vent hole; 22. First heat exchange chamber; 23. Heat exchange fin; 24. Chamber partition; 26. Exhaust window; 27. Heat exchange column; 28. Second heat exchange chamber; 30. Connecting structure; 31. Second connecting section; 32. Second supporting section; 40. Compressor casing; 50. Nut; 60. Rocker arm; 70. Compressor rotor blade. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, 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, 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.

[0035] The installation location of the compressor inlet anti-icing guide vanes on the aero engine is as follows: Figure 11 As shown, the compressor casing 40 is fixed and rotated as needed via an external actuation mechanism to adjust engine flow. When the aircraft flies through low-temperature clouds (air), the low-temperature air enters the engine flow path, causing the mainstream gas temperature to drop. Upon encountering the inlet anti-icing guide vanes, it ices up, forming ice flakes or ice blocks. Under external excitation, these ice flakes or ice blocks on the guide vane surface detach and impact the compressor rotor blades 70 behind, causing damage or failure and affecting engine operating safety. Therefore, to prevent this, high-temperature, high-pressure gas is introduced from the outside into the guide vanes to heat them and prevent icing. A schematic diagram of gas flow inside the guide vanes is shown below. Figure 4 .

[0036] Example 1, refer to Figure 5The guide vane shank 10 includes a threaded section 11, a rocker arm mounting section 12, a circular vent 13, a first support section 14, a square vent 15, and a first connecting section 16. The threaded section 11 engages with the nut 50 to fix the rocker arm 60, ensuring it operates in the correct position. The rocker arm mounting section 12 connects to the rocker arm 60, transmitting external torque to drive the guide vane to rotate. The rocker arm mounting section 12 can be designed as circular, racetrack-shaped, rectangular, etc., depending on the cross-sectional shape of the inner hole of the rocker arm 60, taking manufacturability into consideration. The circular vent 13 and the square vent 15 are used in pairs (see reference). Figure 6 The circular vent 13 and the square vent 15 are connected (see reference). Figure 7 The hot gas entering the annular chamber of the compressor casing 40 is directed into the guide vane stalk 10 and the guide vane 20. The shapes of the circular vent 13 and the square vent 15 can be designed according to the required airflow, such as circular and square, or other shapes. The first support section 14 is used to support the guide vane 20 and fix it to the compressor casing 40. The first support section 14 is a cylinder with a certain diameter. The first connecting section 16 is cylindrical with a larger diameter than the first support section 14. It is used to connect the first support section 14 and the guide vane 20, giving it sufficient strength and rigidity. Considering strength, hardness, and heat exchange effect, the threaded section 11, the rocker arm mounting section 12, and the first support section 14 are made of stainless steel, while the first connecting section 16 is made of copper alloy. A mixed zone of stainless steel and high thermal conductivity copper alloy will be formed between the two structures.

[0037] refer to Figure 8 The guide vane 20 is provided with a vent 21, a first heat exchange chamber 22, a heat exchange fin 23, a chamber partition 24, an exhaust window 26, a heat exchange column 27, and a second heat exchange chamber 28. The vent 21 is an extension of the square vent 15, with the same size, except that the vent 21 is designed at the upper end of the guide vane 20 to introduce hot air into the cavity of the guide vane 20. The first heat exchange chamber 22 is located on the right side of the guide vane 20 and is part of the entire heat exchange chamber. Hot air flows inside it. In order to ensure a certain strength, rigidity, and manufacturability, a certain thickness should be ensured around it. The heat exchange fin 23 is located inside the first heat exchange chamber 22 and only contacts the second surface (the thickness of the second surface is greater than that of the first surface). The heat exchange fin 23 does not contact the other side (the first surface) (see reference). Figure 9To change the contact time between hot air and heat exchange fins 23, the thickness, inclination angle, and number of heat exchange fins 23 can be adjusted according to requirements. The chamber baffle 24 is located in the middle of the guide vane 20 chamber and is designed in different shapes according to the blade thickness distribution and heat exchange effect, but it must be completely integrated with the first and second surfaces. The chamber baffle 24 is completely integrated with the end where the vent hole 21 is provided. A channel of a certain width is left at the end of the chamber baffle 24 and the guide vane 20 installation connection structure 30 to ensure that hot air can smoothly enter from the first heat exchange chamber 22. In the second heat exchange chamber 28, the exhaust window 26 is shaped like a sieve and located on the second surface side of the guide vane 20. Hot air flows out from the exhaust window 26 and enters the main flow channel. The size and number of windows are designed according to the hot air flow rate, while also considering manufacturability. The heat exchange column 27 is located in the second heat exchange chamber 28. The heat exchange column 27 has a similar function to the heat exchange fin 23. The heat exchange column 27 only contacts the first surface and does not contact the second surface. To increase the contact time between the hot air and the fin, the diameter, arrangement, and number of the heat exchange column 27 can be adjusted according to requirements. The guide vane 20 is made of a high thermal conductivity copper alloy.

[0038] refer to Figure 10 The connecting structure 30 includes a second connecting section 31 and a second supporting section 32. The second connecting section 31 is cylindrical, and its diameter is larger than that of the second supporting section 32. It is used to connect the second supporting section 32 and the guide vane 20, giving it sufficient strength and rigidity. The second supporting section 32 supports the guide vane 20. The second supporting section 32 is fixed to the compressor casing 40 and is a cylindrical section with a certain diameter. Considering the heat exchange effect, the second connecting section 31 and the second supporting section 32 are made of copper alloy.

[0039] Example 2, refer to Figure 3 A compressor inlet guide vane includes an integrally formed guide vane shank 10, a guide vane 20, and a connecting structure 30. The guide vane shank 10 and the connecting structure 30 are respectively disposed at opposite ends of the guide vane 20. A vent hole 21 is provided at the end of the guide vane 20. A first heat exchange chamber 22 and a second heat exchange chamber 28 are provided in the guide vane 20 and are interconnected. The vent hole 21 connects the guide vane shank 10 and the first heat exchange chamber 22. An exhaust window 26 is provided on the outer surface of the guide vane 20 and is connected to the second heat exchange chamber 28. The exhaust window 26 is scoop-shaped, and this scoop-shaped design facilitates heat conduction.

[0040] Furthermore, by integrating the guide vane shank 10, guide vane 20, and connecting structure 30 into a single unit, fewer processes and a significant reduction in machining are achieved, thereby lowering costs. The integrated molding eliminates the need for special processes such as brazing for the compressor inlet guide vane, shortening the parts processing cycle, significantly improving the pass rate, and effectively controlling costs. The number of parts is reduced from three to one, and the absence of welding defects improves reliability.

[0041] The guide vane stalk 10 and the connecting structure 30 are used to fix the guide vane 20.

[0042] refer to Figure 9 The outer surface of the guide vane 20 is provided with a first surface and a second surface that are connected by a transition. The first surface is curved and the second surface is flat. The second surface is provided with an exhaust window 26.

[0043] Specifically, the thickness of the first surface is greater than the thickness of the second surface, and the first heat exchange chamber 22 and the second heat exchange chamber 28 are separated by a chamber partition 24; by providing heat exchange fins 23 and heat exchange columns 27 in the guide vane 20, the thermal conductivity of the guide vane 20 is improved (see reference). Figure 12 and Figure 13 , Figure 12 This is a schematic diagram of the temperature distribution of the anti-icing guide vanes at the inlet of a typical compressor. Figure 13 This is a schematic diagram of the temperature distribution of the compressor inlet guide vanes in an embodiment of the present invention, combined with... Figure 12 and Figure 13 It can be clearly seen that the guide vane temperature of this invention is higher than that of the prior art, thus achieving high-efficiency heat conduction and de-icing. This invention can significantly improve the heat exchange effect while maintaining the same external contour, and also reduces the external heat demand, further improving engine performance and lifespan. Furthermore, the guide vane stalk 10, guide vane 20, and connecting structure 30 are manufactured using additive manufacturing technology. This not only improves the anti-icing heat exchange effect but also shortens the production cycle, reduces processing costs, and ensures engine operating safety.

[0044] The technical solution of this invention utilizes additive manufacturing technology and adopts an integrated design approach. To ensure heat exchange efficiency, the guide vane 20 and guide vane shank 10 are made of different materials, but are integrated into a single design. The guide vane 20 is made of a material with high thermal conductivity, while the guide vane shank 10 is made of a material with high hardness. The inner cavity of the guide vane 20 (i.e., the second heat exchange cavity 28 and the first heat exchange cavity 22) is designed with heat exchange columns 27 and heat exchange ribs 23 to enhance heat exchange efficiency. The guide vane shank 10 and the connecting structure 30 provide mounting support, allowing the guide vane to be mounted and fixed on the compressor casing 40. The guide vane 20 provides the heat exchange structure and is a key structure of the guide vane.

[0045] refer to Figure 5The guide vane shank 10 includes a threaded section 11, a rocker arm mounting section 12, a first support section 14, and a first connecting section 16 connected in sequence. A circular vent hole 13 is provided on the side of the first support section 14. Both the first connecting section 16 and the first support section 14 have square vent holes 15 communicating with the circular vent hole 13. The square vent holes 15 communicate with the vent hole 21. Specifically, the threaded section 11 cooperates with the nut 50 to fix the rocker arm 60, ensuring it operates in the correct position. Furthermore, the threaded section 11, the rocker arm mounting section 12, and the first support section 14 are all made of stainless steel, while the first connecting section 16 is made of copper alloy. A mixed zone of stainless steel and high thermal conductivity copper alloy is formed at the connection between the first support section 14 and the first connecting section 16. The use of copper alloy in the first connecting section 16 achieves thermal conductivity, and the mixed zone at the connection between the first support section 14 and the first connecting section 16 achieves both high strength and good thermal conductivity.

[0046] Furthermore, the guide vane shank 10 is made of stainless steel and copper alloy using an integrated molding process, which significantly reduces the number of machining processes and ensures good consistency of the parts.

[0047] refer to Figure 10 The connecting structure 30 includes a second connecting section 31 and a second supporting section 32 that are interconnected. The second connecting section 31 is connected to the guide vane 20. Specifically, the diameter of the second connecting section 31 is larger than the diameter of the second supporting section 32. Both the second connecting section 31 and the second supporting section 32 are made of copper alloy material, thereby improving the heat dissipation effect.

[0048] refer to Figure 8 A heat exchange fin 23 is provided in the first heat exchange chamber 22, and the heat exchange fin 23 is fixedly connected to the first surface. By providing the heat exchange fin 23, the heat conduction efficiency is increased, thereby improving the de-icing efficiency. With the external contour remaining completely unchanged, the heat exchange effect can be greatly improved, and the external heat demand will be reduced, further improving engine performance and lifespan. Furthermore, there are gaps between the heat exchange rib 23 and the inner and second surfaces of the first heat exchange cavity 22.

[0049] In another optional embodiment of the present invention, the angle between the heat exchange fin 23 and the axis of the vent 21 is α, where α ranges from 30° to 60° in the connection structure. This is used to increase the contact time between hot air and the heat exchange fin 23. The thickness, inclination angle, and number of fins can be adjusted according to requirements.

[0050] Specifically, refer to Figure 8Four heat exchange fins 23 are arranged sequentially in the first heat exchange chamber 22. Each heat exchange fin 23 is fixedly connected to the inner wall of the first surface only, and there are gaps between it and the other surfaces inside the heat exchange fin 23, thereby realizing the circulation of hot air.

[0051] refer to Figure 8 The second heat exchange chamber 28 is provided with a plurality of linearly arrayed heat exchange columns 27, and the plurality of heat exchange columns 27 are all fixedly connected to the first surface.

[0052] Furthermore, gaps exist between the inner surface and the second surface of the heat exchange column 27 and the second heat exchange chamber 28. Specifically, refer to... Figure 8 Two rows of heat exchange columns 27 are arranged sequentially in the second heat exchange chamber 28. Each row of heat exchange columns 27 is fixedly connected to the inner wall of the first surface. There are gaps between the heat exchange columns 27 and the other surfaces inside the second heat exchange chamber 28, thereby realizing the circulation of hot air.

[0053] Furthermore, the first heat exchange chamber 22 and the second heat exchange chamber 28 are connected at the end furthest from the vent 21. This maximizes the area through which hot air flows in the guide vane 20, improving the heat transfer efficiency of the hot air. The first heat exchange chamber 22 and the second heat exchange chamber 28 form a "U" shape in the guide vane 20, thereby achieving a longer flow channel and improving the utilization rate of hot air.

[0054] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A compressor inlet guide vane, characterized in that, It includes an integrally formed guide vane stalk (10), guide vane (20) and connecting structure (30), wherein the guide vane stalk (10) and connecting structure (30) are respectively disposed at opposite ends of the guide vane (20); The guide vane (20) is provided with a vent hole (21) at its end. The guide vane (20) is provided with a first heat exchange chamber (22) and a second heat exchange chamber (28) that are interconnected. The vent hole (21) connects the guide vane stalk (10) and the first heat exchange chamber (22). The outer surface of the guide vane (20) is provided with an exhaust window (26), which is connected to the second heat exchange chamber (28).

2. The compressor inlet guide vane according to claim 1, characterized in that, The outer surface of the guide vane (20) is provided with a first surface and a second surface that are connected by a transition. The first surface is curved and the second surface is flat. An exhaust window (26) is provided on the second surface.

3. A compressor inlet guide vane according to claim 1, characterized in that, The guide leaf stalk (10), guide leaf (20) and connecting structure (30) are made using additive manufacturing technology.

4. A compressor inlet guide vane according to claim 1, characterized in that, The guide vane stalk (10) includes a threaded section (11), a rocker arm mounting section (12), a first support section (14), and a first connecting section (16) connected in sequence; a circular vent hole (13) is provided on the side of the first support section (14), and a square vent hole (15) communicating with the circular vent hole (13) is provided inside the first connecting section (16) and the first support section (14), and the other end of the square vent hole (15) is connected with the vent hole (21).

5. A compressor inlet guide vane according to claim 4, characterized in that, The threaded section (11), rocker arm mounting section (12) and first support section (14) are all made of stainless steel, and the first connecting section (16) is made of copper alloy. A mixed area of ​​stainless steel and high thermal conductivity copper alloy will be formed at the connection between the first support section (14) and the first connecting section (16).

6. A compressor inlet guide vane according to claim 1, characterized in that, The connection structure (30) includes a second connecting section (31) and a second support section (32) that are connected to each other, and the second connecting section (31) is connected to the guide vane (20).

7. A compressor inlet guide vane according to any one of claims 1-3, characterized in that, A heat exchange rib (23) is provided in the first heat exchange cavity (22), and the heat exchange rib (23) is fixedly connected to the first surface.

8. A compressor inlet guide vane according to claim 7, characterized in that, There are gaps between the heat exchange rib (23) and the inner and second surfaces of the first heat exchange cavity (22).

9. A compressor inlet guide vane according to any one of claims 1-3, characterized in that, The second heat exchange cavity (28) is provided with a plurality of linear array heat exchange columns (27), and the plurality of heat exchange columns (27) are fixedly connected to the first surface.

10. A compressor inlet guide vane according to claim 9, characterized in that, There are gaps between the heat exchange column (27) and the inner surface and the second surface of the second heat exchange chamber (28).

11. A compressor inlet guide vane according to claim 1, characterized in that, The first heat exchange chamber (22) and the second heat exchange chamber (28) are connected at the end away from the vent (21).

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