Anti-icing flexible air inlet cone structure
By combining a flexible rubber inlet cone at the front and a rigid material at the rear, centrifugal force is used to throw out ice blocks. Combined with a double-step structure, the weight and efficiency problems in traditional anti-icing designs are solved, enabling automatic de-icing and anti-icing of aircraft engines.
Patent Information
- Application Number
- CN202511274061.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-08
- Publication Date
- 2025-11-18
AI Technical Summary
In traditional aircraft engine anti-icing designs, electric heating and high-temperature gas anti-icing methods increase engine weight and reduce efficiency, and require complex bleed air devices.
The system combines a flexible rubber front section and a rigid material rear section of the air intake cone, using centrifugal force to automatically eject ice blocks. The double-step structure reduces the stiffness of the cone tip, achieving automatic de-icing and anti-icing.
It achieves rapid de-icing of the intake cone without the need for electric heating devices or high-temperature gases, reducing engine weight and ensuring safe operation.
Smart Images
Figure CN120968883A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of anti-icing design of gas turbine engine, and discloses an anti-icing flexible inlet cone structure. BACKGROUND
[0002] During the flight process of the aircraft, such as take-off, climbing and descending, there are icing weather conditions such as supercooled water droplets and freezing rain in the low-temperature atmospheric cloud layer, and the inlet components of the aero-engine are prone to icing problems, especially the engine inlet cone structure. The icing not only affects the aerodynamic performance of the aero-engine, reduces the inlet flow of the engine, and the accumulation or shedding of ice has an important influence on the safe operation of the engine, and the anti-icing design is an important factor that must be considered for high-performance aero-engines.
[0003] In the traditional anti-icing design of the aero-engine, the electric heating method or the method of introducing high-temperature gas of the compressor is used for anti-icing treatment of the inlet structure, both methods have good anti-icing effect, but the complex air introduction device or electric heating structure needs to be designed, which increases the weight of the engine, and the introduction of high-temperature gas reduces the working efficiency of the engine. SUMMARY
[0004] The purpose of the present application is to provide an anti-icing flexible inlet cone structure, which can realize automatic deicing and anti-icing of the aero-engine inlet cone without introducing complex electric heating devices or high-temperature gas for heat exchange, and ensure the safe operation of the aero-engine.
[0005] In order to achieve the above technical effects, the technical scheme adopted by the present application is as follows: An anti-icing flexible inlet cone structure, comprising an inlet cone front section having a cone tip portion, and an inlet cone rear section fixedly connected to the inlet cone front section; the inlet cone front section is made of flexible rubber material, and the inlet cone rear section is made of hard material; the inlet cone front section is a hollow structure, and the inner wall of the rotary cross section of the inlet cone front section is a double-step structure.
[0006] Further, the axial length of the inlet cone front section is 15-30% of the total length of the inlet cone structure.
[0007] Further, the double-step structure of the inner wall of the rotary cross section of the inlet cone front section comprises a first step close to the cone tip portion and a second step close to the tail portion of the inlet cone front section; the included angle between the connecting surface of the second step and the first step and the axial direction of the inlet cone structure is 20-30°; and the included angle between the connecting surface of the first step and the cone tip portion and the axial direction of the inlet cone structure is 25-40°.
[0008] Further, the radial height of the tail end of the front section of the inlet cone is less than the radial height of the front end of the rear section of the inlet cone, so that the radial height difference is formed at the connecting position of the front section and the rear section of the inlet cone.
[0009] Further, the radial height difference is 0.08-0.1 times the radial height of the tail end of the front section of the inlet cone.
[0010] Further, the tail end of the front section of the inlet cone is provided with a clamping groove, and the rear section of the inlet cone is provided with a ring-shaped boss extending to the inside of the inlet cone structure at the connecting position with the front section of the inlet cone, and the ring-shaped boss is used for interference fit with the clamping groove.
[0011] Further, the interference amount between the ring-shaped boss and the clamping groove is greater than 0.1 mm.
[0012] Further, the position where the clamping groove contacts the ring-shaped boss is provided with sealing glue.
[0013] Compared with the prior art, the present application has the beneficial effects that: the flexible deformation of the front section of the inlet cone can automatically throw the ice block of the front section of the inlet cone to the fan flow channel under the action of centrifugal force, realize the rapid ice removal and ice prevention of the inlet cone, and the automatic ice removal and ice prevention of the inlet cone of the aero-engine can be realized without introducing complex electric heating devices or high-temperature gas for heat exchange, so as to ensure the safe operation of the aero-engine; in addition, the inner wall of the rotating cross section of the front section of the inlet cone is a double-step structure, the double-step structure can reduce the rigidity of the cone tip, rely on the flexible deformation of the cone tip to strengthen the ice removal effect, and reduce the weight of the engine. BRIEF DESCRIPTION OF DRAWINGS
[0014] Fig. 1 Structure diagram of the ice-prevention flexible inlet cone in the embodiment; Fig. 2 Connecting diagram of the front section of the inlet cone and the rear section of the inlet cone in the embodiment; Fig. 3 Double-step structure diagram of the front section of the inlet cone in the embodiment; 1, front section of inlet cone; 2, rear section of inlet cone; 3, first step; 4, second step; 5, clamping groove; 6, ring-shaped boss. DETAILED DESCRIPTION
[0015] The present application will be further described in conjunction with the embodiments and the drawings. However, it should not be understood that the scope of the above-mentioned subject matter of the present application is limited to the following embodiments, and any technology realized based on the content of the present application belongs to the scope of the present application.
[0016] EMBODIMENT Reference Figs. 1 to 3The application discloses an anti-icing flexible inlet cone structure, which comprises an inlet cone front section 1 with a cone tip and an inlet cone rear section 2 fixedly connected to the inlet cone front section 1; the inlet cone front section 1 is made of flexible rubber material, and the inlet cone rear section 2 is made of hard material; the inlet cone front section 1 is a hollow structure, and the inner wall of the inlet cone front section 1 is a double-step structure.
[0017] In the embodiment, the inlet cone is divided into two parts, i.e., the inlet cone front section 1 made of flexible rubber material and the inlet cone rear section 2 made of traditional hard material such as metal. When the aero-engine is working, the flexible deformation of the inlet cone front section 1 automatically throws the ice block of the inlet cone front section 1 to the fan flow channel under the centrifugal force, so that the rapid ice removal and anti-icing of the inlet cone are realized. The automatic ice removal and anti-icing of the aero-engine inlet cone can be realized without introducing complex electric heating devices or high-temperature gas for heat exchange, so that the safe operation of the aero-engine is ensured. In addition, the inner wall of the inlet cone front section 1 is a double-step structure, which can reduce the rigidity of the cone tip, rely on the flexible deformation of the cone tip to strengthen the ice removal effect, and reduce the weight of the engine.
[0018] In the embodiment, the axial length of the inlet cone front section 1 is 15-30% of the total length of the inlet cone structure.
[0019] The double-step structure of the inner wall of the inlet cone front section 1 comprises a first step 3 close to the cone tip and a second step 4 close to the tail of the inlet cone front section 1; the connecting surface between the second step 4 and the first step 3 is 20-30 degrees to the axial direction of the inlet cone structure; and the connecting surface between the first step 3 and the cone tip is 25-40 degrees to the axial direction of the inlet cone structure. In the embodiment, the connecting surface between the second step 4 and the first step 3 is 26 degrees to the axial direction of the inlet cone structure, and the connecting surface between the first step 3 and the cone tip is 32 degrees to the axial direction of the inlet cone structure, so that the rigidity gradient and the connection reliability of the inlet cone front section 1 along the axial direction are ensured, and the weight of the inlet cone is reduced.
[0020] In the embodiment, in order to strengthen the ice removal effect of the inlet cone, the radial height of the tail position of the cone surface of the inlet cone front section 1 is smaller than the radial height of the front end of the cone surface of the inlet cone rear section 2, so that the radial height difference is formed at the connecting position of the cone surfaces of the inlet cone front section 1 and the inlet cone rear section 2. Δh The water droplets can be prevented from forming a continuous wetting interface on the inlet cone surface, the contact angle of the water droplets on the surface of the inlet cone is improved, the hydrophobicity of the surface is improved, the contact area between the ice and the cone surface is increased, and the ice is accelerated to fall under the vibration of the cone tip. In the embodiment, the distance between the maximum outer diameter of the inlet cone front section 1 and the center line is 0.08-0.1. H , Δh / H
[0021] In the embodiment, the tail cone surface position of the front section of the air intake cone 1 is provided with a clamping groove 5, and the rear section of the air intake cone 2 is provided with a ring-shaped boss 6 extending to the inside of the air intake cone structure at the position connected with the front section of the air intake cone 1, the ring-shaped boss 6 is used to interfere with the clamping groove 5, and the interference amount is greater than 0.1 mm. When assembling, the clamping groove 5 of the front section of the air intake cone 1 and the ring-shaped boss 6 of the rear section of the air intake cone 2 are assembled by extruding the flexible deformation of the front section of the air intake cone 1, and the sealing glue is coated on the cooperation surface of the clamping groove 5 and the ring-shaped boss 6, so as to realize the stable connection of the front section of the air intake cone 1 and the rear section of the air intake cone 2.
[0022] The above is only a preferred embodiment of the present application, and is not used to limit the present application, any modification, equivalent replacement and improvement within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims
1. An ice-phobic flexible inlet cone structure, characterized by, The air intake cone front section (1) with a tapered tip, and the air intake cone rear section (2) fixedly connected to the air intake cone front section (1); the air intake cone front section (1) is made of flexible rubber material, and the air intake cone rear section (2) is made of hard material; the air intake cone front section (1) is a hollow structure, and the inner wall of the air intake cone front section (1) is a double-step structure.
2. The ice-phobic flexible inlet cone structure of claim 1, wherein, The axial length of the air intake cone front section (1) is 15-30% of the total length of the air intake cone structure.
3. The ice-phobic flexible inlet cone structure of claim 1, wherein, The double-step structure of the inner wall of the air intake cone front section (1) includes a first step (3) near the tapered tip and a second step (4) near the tail of the air intake cone front section (1); the connecting surface between the second step (4) and the first step (3) has an axial angle of 20-30° with the air intake cone structure; the connecting surface between the first step (3) and the tapered tip has an axial angle of 25-40° with the air intake cone structure.
4. The ice-phobic flexible inlet cone structure of claim 1, wherein, The radial height of the tail position of the air intake cone front section (1) is less than the radial height of the front end of the air intake cone rear section (2), so that the radial height difference is formed at the connecting position of the air intake cone front section (1) and the air intake cone rear section (2).
5. The ice-phobic flexible inlet cone structure of claim 4, wherein, The radial height difference is 0.08-0.1 times the radial height of the tail position of the air intake cone front section (1).
6. The ice-phobic flexible inlet cone structure of claim 1, wherein, The tail position of the air intake cone front section (1) is provided with a clamping groove (5), and the air intake cone rear section (2) is provided with a ring-shaped boss (6) extending to the inside of the air intake cone structure at the connecting position of the air intake cone front section (1), and the ring-shaped boss (6) is used for interference fit with the clamping groove (5).
7. The ice-phobic flexible inlet cone structure of claim 6, wherein, The interference amount between the ring-shaped boss (6) and the clamping groove (5) is greater than 0.1 mm.
8. The ice-phobic flexible inlet cone structure of claim 6, wherein, The position where the clamping groove (5) contacts the ring-shaped boss (6) is provided with sealing glue.