Forced air cooling air cover for aero-engine
The combined structure of tungsten alloy inner hood and copper alloy cooling fins, combined with a forced air cooling hood with alumina and zirconium oxide coatings, solves the problem of poor heat dissipation of existing air cooling hoods, and improves the engine's heat dissipation efficiency and the durability of the hood.
Patent Information
- Application Number
- CN202423118807.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-17
- Publication Date
- 2025-09-23
- Estimated Expiration
- 2034-12-17
AI Technical Summary
Existing forced air cooling hoods for aircraft engines cannot effectively and quickly dissipate the heat generated by engine operation, resulting in heat accumulation and affecting engine performance and safety.
The combined structure of tungsten alloy inner hood, copper alloy heat sink fins and outer hood is adopted. The high thermal conductivity of tungsten alloy is used to evenly transfer heat to the copper alloy heat sink fins, and the heat is removed by airflow. At the same time, the outer hood is coated with aluminum oxide and zirconium oxide to improve high temperature resistance and corrosion resistance.
It achieves rapid heat dissipation of the aircraft engine, improves the engine's operating performance and stability, reduces the risk of overheating failure, and extends the service life of the wind cover.
Smart Images
Figure CN223374514U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of forced air cooling hoods for aircraft engines, in particular to a forced air cooling hood for aircraft engines. Background Art
[0002] An aircraft engine is a highly complex and sophisticated thermodynamic machine that provides the power necessary for flight in aircraft (such as airplanes and helicopters). Its basic principle is to convert the chemical energy of the fuel into mechanical energy, driving the aircraft to generate thrust or pull, thereby enabling the aircraft to fly. A forced air cooling hood for an aircraft engine is a device installed externally to the engine. Its primary function is to cool the engine through forced ventilation, ensuring that the engine operates within the appropriate temperature range. Current forced air cooling hoods for aircraft engines often use a single cooling channel for heat dissipation and temperature reduction, resulting in inefficient cooling. Therefore, a new forced air cooling hood for aircraft engines is needed.
[0003] The existing forced air cooling hood for aircraft engines is not convenient for quickly dissipating the heat generated by the operation of the aircraft engine during use, resulting in continuous accumulation of heat in the hood. The overall temperature of the engine is difficult to quickly reduce, which greatly affects the working performance and operating stability of the aircraft engine, increases the risk of failure due to overheating, and poses a potential threat to aviation safety. Therefore, there is an urgent need for a forced air cooling hood for aircraft engines. Utility Model Content
[0004] Based on this, the purpose of the present invention is to provide a forced air cooling hood for an aircraft engine, so as to solve the problem that the existing forced air cooling hood for an aircraft engine is inconvenient to quickly dissipate the heat generated by the operation of the aircraft engine.
[0005] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a forced air cooling hood for an aircraft engine, comprising a tungsten alloy inner hood, the outer wall of which is fixedly connected to a support block, the outer wall of which is mounted with an outer hood, the outer wall of which is fixedly connected to a copper alloy heat sink fin, and the interior of the copper alloy heat sink fin is provided with heat dissipation holes.
[0006] The inner wall of the outer wind cover is fixedly connected with an aluminum oxide coating, and the outer wall of the outer wind cover is fixedly connected with a zirconium oxide coating.
[0007] Preferably, the support blocks are welded to the outer wind shield, and the support blocks are arranged in a ring shape with the central axis of the tungsten alloy inner wind shield as the center.
[0008] Preferably, the copper alloy heat dissipation fins are arranged at equal intervals on the outer wall of the tungsten alloy inner air hood, and the copper alloy heat dissipation fins are welded to the tungsten alloy inner air hood.
[0009] Preferably, the outer wind shield is sleeved on the outer wall of the tungsten alloy inner wind shield, and the inner diameter of the outer wind shield is larger than the outer diameter of the tungsten alloy inner wind shield.
[0010] Preferably, the outer wind hood and the aluminum oxide coating are tightly fitted, and the outer wind hood and the aluminum oxide coating are arranged in parallel.
[0011] Preferably, the outer wind cover is tightly fitted to the zirconium oxide coating, and the zirconium oxide coating is arranged in parallel to the aluminum oxide coating.
[0012] Compared with the prior art, the beneficial effects of the present invention are:
[0013] 1. The utility model provides a tungsten alloy inner wind cover, an outer wind cover and copper alloy heat sink fins. Since the material of the tungsten alloy inner wind cover is tungsten alloy, heat can be transferred to the copper alloy heat sink fins. The copper alloy heat sink fins are evenly spaced on the outer wall of the tungsten alloy inner wind cover, so that the tungsten alloy inner wind cover can evenly transfer the heat dissipated by the aircraft engine to each copper alloy heat sink fin. When the aircraft is flying, the airflow will pass through the ventilation groove between the tungsten alloy inner wind cover and the outer wind cover, and blow away the heat on the copper alloy heat sink fins, so that the hot air is discharged through the ventilation groove on the other side, which facilitates the rapid dissipation of the heat generated by the operation of the aircraft engine.
[0014] 2. The utility model provides an outer air hood, an aluminum oxide coating and a zirconium oxide coating. The inner wall of the outer air hood is fixedly connected with the aluminum oxide coating, which can improve the high-temperature resistance of the outer air hood. The outer wall of the outer air hood is fixedly connected with the zirconium oxide coating, which can improve the waterproof and corrosion resistance of the outer air hood, thereby increasing the service life of the forced air cooling hood. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 This is a schematic diagram of the three-dimensional structure of the utility model;
[0016] Figure 2 This is a three-dimensional diagram of the tungsten alloy inner wind shield of the utility model;
[0017] Figure 3 This is a three-dimensional diagram of the outer wind shield of the utility model;
[0018] Figure 4 It is a three-dimensional cross-sectional view of the outer air hood of the utility model.
[0019] In the figure: 1. Tungsten alloy inner air hood; 2. Support block; 3. Outer air hood; 4. Copper alloy heat sink fins; 5. Heat dissipation holes; 6. Alumina coating; 7. Zirconia coating. DETAILED DESCRIPTION
[0020] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.
[0021] The following describes an embodiment of the present invention based on its overall structure.
[0022] See also Figure 1-4 The outer wall of the tungsten alloy inner wind cover 1 is fixedly connected to the support block 2, and the outer wall of the support block 2 is provided with an outer wind cover 3. The outer wall of the tungsten alloy inner wind cover 1 is fixedly connected to the copper alloy heat dissipation fins 4, and the copper alloy heat dissipation fins 4 are provided with heat dissipation holes 5. The support block 2 is welded to the outer wind cover 3, and the support block 2 is arranged in a ring shape with the central axis of the tungsten alloy inner wind cover 1 as the center. The copper alloy heat dissipation fins 4 are arranged at equal intervals on the outer wall of the tungsten alloy inner wind cover 1, and the copper alloy heat dissipation fins 4 are welded to the tungsten alloy inner wind cover 1. The outer wind cover 3 is sleeved on the outer wall of the tungsten alloy inner wind cover 1, and the inner diameter of the outer wind cover 3 is larger than the outer diameter of the tungsten alloy inner wind cover 1, which can facilitate the rapid dissipation of heat generated by the operation of the aircraft engine.
[0023] See also Figure 1-4 A forced air cooling hood for an aircraft engine, the inner wall of the outer hood 3 is fixedly connected with an alumina coating 6, the outer wall of the outer hood 3 is fixedly connected with a zirconia coating 7, the outer hood 3 and the alumina coating 6 are tightly fitted, and the outer hood 3 and the alumina coating 6 are arranged parallel to each other, the outer hood 3 and the zirconia coating 7 are tightly fitted, and the zirconia coating 7 and the alumina coating 6 are arranged parallel to each other, which can improve the high temperature resistance of the outer hood 3.
[0024] Working principle: When in use, the material of the tungsten alloy inner wind cover 1 is tungsten alloy. When the aircraft engine is running, due to the high temperature resistance and high thermal conductivity of tungsten alloy, the heat can be conducted to the copper alloy heat sink 4. The copper alloy heat sink fins 4 are arranged at equal intervals on the outer wall of the tungsten alloy inner wind cover 1, so that the tungsten alloy inner wind cover 1 can evenly conduct the heat dissipated by the aircraft engine to each copper alloy heat sink fin 4. Since the support block 2 is welded to the outer wind cover 3, when the aircraft is flying, the airflow will pass through the ventilation groove between the tungsten alloy inner wind cover 1 and the outer wind cover 3, and blow away the heat on the copper alloy heat sink fin 4, so that the hot air is discharged through the ventilation groove on the other side, so that the heat of the aircraft engine is stably dissipated. The inner wall of the outer wind cover 3 is fixedly connected with an aluminum oxide coating 6, which can improve the high temperature resistance of the outer wind cover 3. The outer wall of the outer wind cover 3 is fixedly connected with a zirconium oxide coating 7, which can improve the waterproof and corrosion resistance of the outer wind cover 3. This completes the use process of the device. The content not described in detail in this specification belongs to the existing technology known to professional and technical personnel in this field.
[0025] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.
Claims
1. A forced air cooling hood for an aircraft engine, comprising a tungsten alloy inner hood (1), characterized in that: The outer wall of the tungsten alloy inner wind cover (1) is fixedly connected to a support block (2), the outer wall of the support block (2) is installed with an outer wind cover (3), the outer wall of the tungsten alloy inner wind cover (1) is fixedly connected to a copper alloy heat dissipation fin (4), and the copper alloy heat dissipation fin (4) is provided with a heat dissipation hole (5) inside. An aluminum oxide coating (6) is fixedly connected to the inner wall of the outer wind hood (3), and a zirconium oxide coating (7) is fixedly connected to the outer wall of the outer wind hood (3).
2. The forced air cooling hood for an aircraft engine according to claim 1, characterized in that: The support block (2) is welded to the outer wind shield (3), and the support block (2) is arranged in a ring shape with the central axis of the tungsten alloy inner wind shield (1) as the center.
3. The forced air cooling hood for an aircraft engine according to claim 1, characterized in that: The copper alloy heat dissipation fins (4) are arranged at equal intervals on the outer wall of the tungsten alloy inner wind cover (1), and the copper alloy heat dissipation fins (4) are welded to the tungsten alloy inner wind cover (1).
4. The forced air cooling hood for an aircraft engine according to claim 1, characterized in that: The outer wind cover (3) is sleeved on the outer wall of the tungsten alloy inner wind cover (1), and the inner diameter of the outer wind cover (3) is larger than the outer diameter of the tungsten alloy inner wind cover (1).
5. The forced air cooling hood for an aircraft engine according to claim 1, characterized in that: The outer wind cover (3) and the aluminum oxide coating (6) are tightly fitted together, and the outer wind cover (3) and the aluminum oxide coating (6) are arranged in parallel.
6. The forced air cooling hood for an aircraft engine according to claim 1, characterized in that: The outer wind cover (3) and the zirconium oxide coating (7) are tightly fitted, and the zirconium oxide coating (7) and the aluminum oxide coating (6) are arranged in parallel.