Heating device of piston aero-engine

Abstract

The utility model discloses a heating device of a piston aero-engine, the piston aero-engine comprises an engine crankcase and an engine cylinder body, the heating device is composed of a resistance heating belt, a power supply assembly, a temperature control switch and a heat preservation cover, the resistance heating belt is wound on the engine crankcase and the engine cylinder body, and the temperature control switch is arranged on the power supply assembly. The temperature control switch is fixed to the engine and connected with the resistance heating belt in series. The heat preservation cover wraps an engine crankcase, an engine cylinder body and the resistance heating belt. By means of the mode of integrally heating the engine, the heating device effectively improves the temperature of an engine shell, a combustion chamber in the engine shell and air, improves the starting success rate of the engine, greatly shortens the starting time, is widely suitable for small piston aero-engines, and provides a more reliable power system for users.

Description

Technical Field

[0001] The utility model relates to a heating device, in particular to a heating device for a piston aircraft engine. Background Art

[0002] Traditional small piston aircraft engines have a long starting time and a low success rate at low temperatures below 0°C. The success rate will further decrease at temperatures below -10°C. The main reasons are as follows: (1) Poor fuel atomization: In low temperature environments, the atomization effect of the fuel will deteriorate. Fuel atomization is a key step in engine combustion. If the atomization is poor, the mixture will be unevenly formed, which will affect the combustion quality and cause starting difficulties; (2) Poor oil fluidity: At low temperatures, the oil fluidity decreases and the lubrication effect inside the engine deteriorates. This will increase the friction resistance of the engine, making the starter take longer and use more power to drive the engine to rotate, thereby extending the starting time; (3) Degraded battery performance: In a low temperature environment, the chemical reaction rate inside the battery slows down and the battery's discharge capacity weakens. If the battery performance is poor, it may not provide enough current to drive the starter, resulting in starting failure; (4) Low intake temperature: At low temperatures, the air temperature entering the cylinder is low, the air density increases, but the oxygen content decreases, which affects the combustion efficiency, causing the engine to require more fuel for combustion, thereby increasing the difficulty of starting; (5) Insufficient engine preheating: In the cold state, the engine needs to be preheated to increase the oil temperature and fuel temperature. If the preheating is insufficient, the oil and fuel temperatures will remain at a low level, affecting the engine's starting performance.

[0003] Therefore, the problem of long starting time and low success rate of small piston engines under low temperature conditions needs to be solved urgently. Summary of the Invention

[0004] Purpose of the invention: The purpose of the utility model is to provide a heating device for a piston aircraft engine that effectively improves the starting success rate and significantly shortens the starting time.

[0005] Technical solution: The utility model provides a heating device for a piston aircraft engine, which includes an engine crankcase and an engine cylinder. The heating device consists of a resistance heating belt, a power supply component, a temperature control switch and a thermal insulation cover. The resistance heating belt is wrapped around the engine crankcase and the engine cylinder, the temperature control switch is fixed on the engine and connected in series with the resistance heating belt, and the thermal insulation cover wraps the engine crankcase, the engine cylinder and the resistance heating belt.

[0006] The resistance heating tape is glued to the engine crankcase and cylinder block. Tightly wrapping the resistance heating tape and bonding it to the engine case and cylinder block with thermally conductive adhesive ensures uniform and efficient heating.

[0007] The heat preservation cover is composed of a cover plate and a shell; the shell is sleeved on the outside of the engine crankcase and the engine cylinder block and is connected to the engine crankcase by bolts, and the cover plate is connected to the shell by bolts.

[0008] Wherein, the cover plate is provided with a through hole for sleeve-mounting the engine crankcase.

[0009] Among them, the insulation cover is provided with a hollow portion, covering 65-75% of the surface area of ​​the piston aircraft engine; a special insulation shell is installed on the periphery of the resistance heating belt, covering 65-75% of the surface of the engine, which helps to reduce heat loss and ensure that the engine can reach the ideal starting temperature in a shorter time, further enhancing the insulation effect.

[0010] Wherein, the power supply component consists of a power plug and a battery.

[0011] The battery is a 24V lithium battery. The heating system uses a 24V lithium battery as a power source, which is small in size, has a high discharge rate, and a large capacity, providing stable and reliable power support.

[0012] The temperature control switch disconnects when the detected temperature exceeds 50°C, and the resistance heating belt stops heating. To prevent overheating due to continuous heating after the engine is successfully started, an intelligent temperature control switch is equipped. When the temperature exceeds 50°C, the switch automatically disconnects the power supply to the resistance heating belt, ensuring that the engine always operates within a safe temperature range.

[0013] Beneficial effects: Compared with the prior art, the present invention has the following significant advantages: (1) By heating the engine as a whole, the heating device of the present invention effectively increases the temperature of the engine casing and its internal combustion chamber and air, improves the success rate of engine starting, and greatly shortens the starting time. In a severe cold environment of -10°C, the engine can be quickly heated to above 30°C within 30 minutes, ensuring that the engine is successfully started once within 3 seconds; (2) It is widely applicable to small piston aircraft engines, optimizes engine performance, improves its reliability under low temperature conditions, and provides users with a more reliable power system. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural diagram of the utility model;

[0015] Figure 2 This is a schematic structural diagram of the thermal insulation cover 6 of the present invention;

[0016] Figure 3 This is a schematic diagram of the structure of the power supply component 4 of this utility;

[0017] Figure 4This is a schematic diagram of the assembly of the thermal insulation cover 6 of the present invention;

[0018] Figure 5 This is a schematic diagram of the assembly of the thermal insulation cover 6 of the present invention;

[0019] Figure 6 Schematic diagram of the thermal insulation cover 6 of the present invention;

[0020] Figure 7 Schematic diagram of the thermal insulation cover 6 of the present invention;

[0021] Among them, there are engine crankcase 1, engine cylinder block 2, resistance heating belt 3, power supply component 4, temperature control switch 5, insulation cover 6, cover plate 7, shell 8, power plug 9 and battery 10. DETAILED DESCRIPTION

[0022] The technical solution of the present utility model will be further described below with reference to the accompanying drawings.

[0023] Example 1

[0024] like Figures 1 to 7 As shown, the heating device of the piston aircraft engine of the present invention comprises an engine crankcase 1 and an engine cylinder block 2, and the heating device comprises a resistance heating belt 3, a power supply component 4, a temperature control switch 5 and a thermal insulation cover 6. The resistance heating belt 3 is wound around the engine crankcase 1 and the engine cylinder block 2, the temperature control switch 5 is fixed on the engine and connected in series with the resistance heating belt 3, and the thermal insulation cover 6 wraps the engine crankcase 1, the engine cylinder block 2 and the resistance heating belt 3; the resistance heating belt 3 is fixed to the engine crankcase 1 and the engine cylinder block 2 by gluing.

[0025] The heat-insulating cover 6 consists of a cover plate 7 and a shell 8. The shell 8 is fitted over the engine crankcase 1 and engine block 2 and bolted to the engine crankcase 1. The cover plate 7 and shell 8 are also bolted together. The cover plate 7 has a through hole for fitting over the engine crankcase 1. The heat-insulating cover 6 has a hollowed-out portion that encloses 70% of the engine's surface area to achieve thermal insulation, while leaving a small amount of space for heat dissipation after the engine is successfully started.

[0026] like Figures 4 to 7 As shown, after the shell 8 of the heat preservation cover 6 is inserted into the engine, the cover plate 7 is fixed to the shell 8 through four heat preservation cover mounting bolts, and the shell 8 is fastened to the engine through the four heat preservation cover mounting bolts.

[0027] The power supply component 4 is composed of a power plug 9 and a battery 10, and the battery 10 is a 24V lithium battery; the resistance heating belt 3 is connected to the power supply through the power supply component 4 and starts heating, and the temperature control switch 5 is disconnected when the detected temperature exceeds 50°C, and the resistance heating belt 3 stops heating.

[0028] The heating device of the piston aircraft engine of the present invention effectively increases the intake temperature, fuel temperature and oil temperature by heating the engine as a whole. The increase in temperature improves the atomization performance of the fuel, enhances the lubricating effect of the oil, reduces the friction resistance of the engine, increases the temperature of the engine casing and its internal combustion chamber and air, increases the success rate of engine starting, and greatly shortens the starting time. Therefore, the present invention optimizes the engine performance and improves its reliability under low temperature conditions. It is widely applicable to small piston aircraft engines and provides users with a more reliable power system.

Claims

1. A heating device for a piston aircraft engine, the piston aircraft engine comprising an engine crankcase (1) and an engine cylinder block (2), characterized in that: The heating device is composed of a resistance heating belt (3), a power supply component (4), a temperature control switch (5) and a heat preservation cover (6); the resistance heating belt (3) is wound around an engine crankcase (1) and an engine cylinder block (2); the temperature control switch (5) is fixed on the engine and connected in series with the resistance heating belt (3); and the heat preservation cover (6) wraps the engine crankcase (1), the engine cylinder block (2) and the resistance heating belt (3).

2. The heating device according to claim 1, characterized in that: The heat-insulating cover (6) is composed of a cover plate (7) and a shell (8); the shell (8) is sleeved on the outside of the engine crankcase (1) and the engine cylinder block (2) and is connected to the engine crankcase (1) via bolts, and the cover plate (7) and the shell (8) are connected via bolts.

3. The heating device according to claim 2, characterized in that: The cover plate (7) is provided with a through hole for sleeve-mounting the engine crankcase (1).

4. The heating device according to claim 1, characterized in that: The heat-insulating cover (6) is provided with a hollow portion, covering 65-75% of the surface area of ​​the piston aircraft engine.

5. The heating device according to claim 1, characterized in that: The power supply assembly (4) is composed of a power plug (9) and a battery (10).

6. The heating device according to claim 5, characterized in that: The battery (10) is a 24V lithium battery.

7. The heating device according to claim 1, characterized in that: The resistance heating belt (3) is fixed to the engine crankcase (1) and the engine cylinder block (2) by gluing.

8. The heating device according to claim 1, characterized in that: The temperature control switch (5) is disconnected when the detected temperature exceeds 50° C., and the resistance heating belt (3) stops heating.

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