An anti-icing structure for an aircraft engine inlet casing

Abstract

This utility model discloses an anti-icing structure for an aero-engine inlet casing, belonging to the field of aero-engine technology. It includes an inlet casing with an internal anti-icing mechanism on its inner wall. Two sets of support frames are fixedly connected to the inner wall of the inlet casing, and inner pillars are fixedly connected to the ends of the two sets of support frames. In this utility model, a first set of wires energizes a first heating wire ring and a heating screw. The heat generated by the operation of the first heating wire ring heats the inner pillar, and the heat generated by the operation of the heating screw heats the arc-shaped support. A second set of wires energizes a second heating wire ring, and the heat generated by the operation of the second heating wire ring heats the outer heating ring. The heat from the arc-shaped support and the inner pillar prevents icing on the inner side of the inlet casing, and the outer heating ring prevents icing on the inner wall of the inlet casing, resulting in good anti-icing performance.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine technology, and more specifically, to an anti-icing structure for an aero-engine air intake casing. Background Technology

[0002] An aero-engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers flight but also serves as a crucial driving force for the development of the aviation industry. The aero-engine intake casing is a vital load-bearing component. When operating at high altitudes, the cold, moist air entering the aero-engine easily accumulates and condenses into ice at the casing support plates. As the ice layer thickens, it affects the air intake operation of the intake casing.

[0003] A search revealed that utility model patent CN219197475U discloses an anti-icing structure for an aero-engine intake casing, including an intake casing with casing support plates fixedly installed inside. Support plate inner rings are fixedly installed between the casing support plates, and a vibration motor is fixedly installed on the inner wall of the inner ring. A heating component is installed inside the inner ring. High heat generated by an electric heating wire is conducted to the inside of the casing support plates through a heat-conducting tube. The heated surface of the casing support plates alleviates icing during high-altitude air intake. When the electric heating wire is inefficient, the timed vibration motor generates vibration that is transmitted to the circumferentially distributed casing support plates, dispersing residual ice. The vibration motor and heating component work together to effectively reduce the possibility of icing at the inner ring of the support plates during air intake. The electric heating wire is encapsulated in a shell and a heat-conducting tube, improving its exposed state and reducing the possibility of damage.

[0004] However, the above-mentioned patent still has the following shortcomings: the electric heating wire can only heat the inner ring of the support plate and the casing support plate, and it is not convenient to heat the inner wall of the intake casing. There is also the possibility of icing on the inner wall of the intake casing. In addition, when the wind is flowing too fast, it is not convenient to heat the cold and humid air by relying on only a set of inner rings of the support plate and the casing support plate, which will lead to icing on the blades at the rear of the engine. Therefore, we have proposed an anti-icing structure for the intake casing of an aero-engine. Utility Model Content

[0005] In view of the problems existing in the prior art, the purpose of this utility model is to provide an anti-icing structure for the air intake casing of an aero-engine.

[0006] To solve the above problems, the present invention adopts the following technical solution: an anti-icing structure for an aero-engine intake casing, comprising an intake casing, an inner anti-icing mechanism provided on the inner wall of the intake casing, two sets of support frame groups fixedly connected to the inner wall of the intake casing, inner pillars fixedly connected to the ends of the two sets of support frame groups, each of the two sets of support frame groups including multiple arc-shaped brackets fixedly connected between the intake casing and the inner pillars, an inner mounting groove provided inside the inner pillars, and insertion holes provided inside the arc-shaped brackets, the ends of the insertion holes being connected to the inner cavity of the inner mounting grooves, multiple first heating wire rings fixedly sleeved on the inner wall of the inner mounting grooves, wherein multiple heating wire rods are fixedly connected to the sides of two of the first heating wire rings, and the ends of the multiple heating wire rods are movably sleeved into the inner cavity of the insertion holes.

[0007] As a preferred embodiment of this utility model, the internal anti-icing mechanism includes an outer heating ring fixedly sleeved on the inner wall of the intake casing. The outer heating ring has multiple annular grooves inside, and a second heating wire ring is sleeved in the inner cavity of the multiple annular grooves. A second wire groove is provided on the side of the outer heating ring, and a second wire group is sleeved in the inner cavity of the second wire groove. The second wire group is connected to the multiple second heating wire rings respectively.

[0008] As a preferred embodiment of the present invention, a third wire groove is provided on the side of the outer heating ring, a first wire groove is provided inside the arc-shaped bracket, a first wire group is sleeved in the inner cavity of the first wire groove, one end of the first wire group extends into the inner cavity of the inner mounting groove and is electrically connected to a plurality of first heating wire rings, and the other end of the first wire group extends through the third wire groove to the outside of the outer heating ring.

[0009] As a preferred embodiment of this utility model, the multiple arc-shaped supports on the two sets of support frame groups are staggered in front and behind each other.

[0010] As a preferred embodiment of the present invention, the inner cavity of the second wire groove is fitted with a second heat insulation tube, and the second wire group passes through the inner cavity of the second heat insulation tube.

[0011] As a preferred embodiment of this utility model, the inner cavities of the third wire groove and the first wire groove are both fitted with a first heat insulation tube, and the first wire group passes through the inner cavity of the first heat insulation tube.

[0012] Compared with the prior art, the advantages of this utility model are: (1) In this utility model, the first heating wire ring and the heating screw are energized by the first wire group, and the heat generated by the operation of the first heating wire ring causes the inner support to carry heat, and the heat generated by the operation of the heating screw causes the arc support to carry heat. In addition, the second heating wire ring is energized by the second wire group, and the heat generated by the operation of the second heating wire ring causes the outer heating ring to carry heat. The heat on the arc support and the inner support prevents the inner side of the intake casing from freezing, and the outer heating ring prevents the inner wall of the intake casing from freezing, thus achieving a good anti-icing effect.

[0013] (2) In this utility model, by setting two sets of arc-shaped supports on the inner side of the intake casing, the cold and humid air entering the inner cavity of the intake casing is heated twice by the two sets of arc-shaped supports with intersecting positions, so as to avoid the cold and humid air entering the engine and affecting its operation. Attached Figure Description

[0014] Figure 1 is a schematic diagram of the overall structure of this utility model.

[0015] Figure 2 is an exploded view of the overall structure of this utility model.

[0016] Figure 3 is a schematic diagram of the arc-shaped bracket of this utility model.

[0017] Figure 4 is a cross-sectional schematic diagram of the inner support column of this utility model.

[0018] Figure 5 is a schematic diagram of the structure of the external heating ring of this utility model.

[0019] Figure 6 is a cross-sectional schematic diagram of the external heating ring of this utility model.

[0020] The following are the labels in the diagram: 1. Intake casing; 2. Internal anti-icing mechanism; 3. Arc-shaped bracket; 4. Internal support column; 5. Internal mounting groove; 6. Insertion hole; 7. First heating wire ring; 8. Heating lead screw; 9. Outer heating ring; 10. Ring groove; 11. Second heating wire ring; 12. Second wire groove; 13. Second wire assembly; 14. Second heat insulation tube; 15. Third wire groove; 16. First wire groove; 17. First wire assembly; 18. First heat insulation tube; 19. Support frame assembly. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present utility model without creative effort are within the scope of protection of the present utility model.

[0022] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "top / bottom," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0023] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances. Example 1

[0024] As shown in Figures 1 to 6, an anti-icing structure for an aero-engine inlet casing includes an inlet casing 1. An internal anti-icing mechanism 2 is provided on the inner wall of the inlet casing 1. Two sets of support frame assemblies 19 are fixedly connected to the inner wall of the inlet casing 1. Inner support columns 4 are fixedly connected to the ends of the two sets of support frame assemblies 19. Each set of support frame assemblies 19 includes multiple arc-shaped brackets 3 fixedly connected between the inlet casing 1 and the inner support columns 4. Both the arc-shaped brackets 3 and the inner support columns 4 are made of heat-conducting materials. An inner mounting groove 5 is provided inside the inner support column 4. Each arc-shaped bracket 3 has an insertion hole 6 inside. The end of the insertion hole 6 connects to the inner cavity of the inner mounting groove 5. Multiple first heating wire rings 7 are fixedly sleeved on the inner wall of the outer heating ring 9. Multiple heating wire rods 8 are fixedly connected to the sides of two of the first heating wire rings 7. The ends of the multiple heating wire rods 8 are movably sleeved into the inner cavity of the insertion hole 6. A third wire groove 15 is provided on the side of the outer heating ring 9. A first wire groove 16 is provided inside an arc-shaped bracket 3. A first wire group 17 is sleeved in the inner cavity of the first wire groove 16. One end of the first wire group 17 extends into the inner cavity of the inner mounting groove 5 and is electrically connected to the multiple first heating wire rings 7. The other end of the first wire group 17 passes through the third wire groove 15 and extends to the outside of the outer heating ring 9. A first heat insulation tube 18 is sleeved in the inner cavity of both the third wire groove 15 and the first wire groove 16. The first wire group 17 passes through the inner cavity of the first heat insulation tube 18. The first heat insulation tube 18 is used to prevent the heat on the arc-shaped bracket 3 and the outer heating ring 9 from affecting the first wire group 17. Example 2

[0025] Based on Embodiment 1, as shown in Figures 1, 2, 5, and 6, the internal anti-icing mechanism 2 includes an outer heating ring 9 fixedly fitted onto the inner wall of the intake casing 1. The outer heating ring 9 is made of a heat-conducting material so that the heat from the second heating wire ring 11 can be conducted to the outer heating ring 9, preventing ice formation on the inner surface of the outer heating ring 9. The outer heating ring 9 has multiple annular grooves 10 inside, and the inner cavities of the multiple annular grooves 10 are fitted with the second heating wire rings 11. The outer heating ring 9 has a second wire groove 12 on its side, and the inner cavity of the second wire groove 12 is fitted with a second wire assembly 13. The second wire assembly 13 is connected to the multiple second heating wire rings 11. The inner cavity of the second wire groove 12 is fitted with a second heat insulation tube 14, and the second wire assembly 13 penetrates the inner cavity of the second heat insulation tube 14. The second heat insulation tube 14 prevents the heat from the outer heating ring 9 from affecting the second wire assembly 13. The second wire assembly 13 and the first wire assembly 17... The ends of the structure are connected to the power supply on the aircraft, and the structure is controlled by the control system on the aircraft. Example 3

[0026] Based on Embodiment 1 and Embodiment 2, as shown in Figures 1 and 2, the multiple arc-shaped supports 3 on the two sets of support frame groups 19 are staggered in front and behind to ensure the quality of the heat from the arc-shaped supports 3 arranged in front and behind to heat the cold and humid air.

[0027] It should be noted that this utility model is an anti-icing structure for an aero-engine intake casing. In use, the first heating wire ring 7 and the heating screw 8 are energized by the first wire group 17. The heat generated by the operation of the first heating wire ring 7 heats the inner support 4, and the heat generated by the operation of the heating screw 8 heats the arc-shaped support 3. In addition, the second heating wire ring 11 is energized by the second wire group 13. The heat generated by the operation of the second heating wire ring 11 heats the outer heating ring 9. The heat on the outer heating ring 9, the arc-shaped support 3, and the inner support 4 prevents ice from forming on the inside of the intake casing 1. In addition, the two sets of arc-shaped supports 3 can heat the cold and humid air entering the intake casing 1 twice, preventing the cold and humid air from affecting the operation of the engine.

[0028] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model based on the technical solution and its improved concept should be covered within the protection scope of the present utility model.

Claims

1. An anti-icing structure for an aircraft engine inlet casing, comprising an inlet casing cylinder (1), characterized in that: The inner wall of the intake casing (1) is provided with an internal anti-icing mechanism (2). The inner wall of the intake casing (1) is fixedly connected with two sets of support frame groups (19). The ends of the two sets of support frame groups (19) are fixedly connected with inner pillars (4). The two sets of support frame groups (19) respectively include multiple arc-shaped brackets (3) fixedly connected between the intake casing (1) and the inner pillars (4). The inner pillars (4) are provided with an inner mounting groove (5). The arc-shaped brackets (3) are all provided with insertion holes (6). The ends of the insertion holes (6) are connected to the inner cavity of the inner mounting groove (5). Multiple first heating wire rings (7) are fixedly sleeved on the inner wall of the inner mounting groove (5). Multiple heating wire rods (8) are fixedly connected to the sides of two of the first heating wire rings (7). The ends of the multiple heating wire rods (8) are movably sleeved into the inner cavity of the insertion holes (6).

2. The anti-icing structure for an aero-engine inlet casing according to claim 1, characterized in that: The internal anti-icing mechanism (2) includes an outer heating ring (9) fixedly sleeved on the inner wall of the intake casing (1). The outer heating ring (9) has multiple annular grooves (10) inside. The inner cavity of the multiple annular grooves (10) is fitted with a second heating wire ring (11). The side of the outer heating ring (9) is provided with a second wire groove (12). The inner cavity of the second wire groove (12) is fitted with a second wire group (13). The second wire group (13) is connected to the multiple second heating wire rings (11) respectively.

3. The anti-icing structure for an aero-engine inlet casing according to claim 2, characterized in that: The outer heating ring (9) has a third wire groove (15) on its side, and the arc-shaped bracket (3) has a first wire groove (16) inside. The inner cavity of the first wire groove (16) is fitted with a first wire group (17). One end of the first wire group (17) extends into the inner cavity of the inner mounting groove (5) and is electrically connected to multiple first heating wire rings (7). The other end of the first wire group (17) passes through the third wire groove (15) and extends to the outside of the outer heating ring (9).

4. The anti-icing structure for an aero-engine inlet casing according to claim 1, characterized in that: The multiple arc-shaped supports (3) on the two sets of support frame groups (19) are staggered in front and behind each other.

5. The anti-icing structure for an aero-engine inlet casing according to claim 2, characterized in that: The inner cavity of the second wire groove (12) is fitted with a second heat insulation tube (14), and the second wire group (13) passes through the inner cavity of the second heat insulation tube (14).

6. The anti-icing structure for an aero-engine inlet casing according to claim 3, characterized in that: The inner cavities of the third wire groove (15) and the first wire groove (16) are both fitted with a first heat insulation tube (18), and the first wire group (17) passes through the inner cavity of the first heat insulation tube (18).

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