Two-stroke aero-engine cylinder head
By introducing a water-cooling heat dissipation structure into the cylinder head of a two-stroke aircraft engine, the problems of high noise and uneven air-cooling heat dissipation are solved, and a low-noise and uniform water-cooling heat dissipation effect is achieved.
Patent Information
- Application Number
- CN202423146348.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-19
- Publication Date
- 2025-09-26
- Estimated Expiration
- 2034-12-19
AI Technical Summary
Existing two-stroke aircraft engines use air cooling, which is noisy, has uneven heat dissipation, is greatly affected by the environment, and has poor heat dissipation effect.
Water cooling is adopted, and an annular cooling water groove and water inlet and outlet are set in the cylinder head body, and cooling fins are provided on the outer periphery to achieve precise heat dissipation of the combustion chamber.
It achieves low noise and uniform heat dissipation effect, is not affected by the environment, and improves heat dissipation efficiency.
Smart Images
Figure CN223387430U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aviation engines, in particular to a cylinder head of a two-stroke aviation engine. Background Art
[0002] A two-stroke aircraft engine is a piston-type aircraft engine. Its operating principle is similar to that of a conventional two-stroke engine, but it is primarily used in the aviation industry. The operating cycle of a two-stroke engine consists of four stages: intake, compression, power generation, and exhaust. The piston reciprocates twice during each cycle. The operating principle of a two-stroke aircraft engine is as follows: 1. Intake: As the piston moves downward, a mixture of fresh air and fuel enters the cylinder through the intake port. 2. Compression: As the piston moves upward, it compresses the mixture, increasing its temperature and pressure. 3. Power generation: When the mixture is compressed to a certain level, a spark plug ignites the mixture, creating an explosion that pushes the piston downward, thereby propelling the aircraft forward. 4. Exhaust: As the piston moves upward, exhaust gases exit the cylinder through the exhaust port.
[0003] Existing two-stroke aircraft engines mainly use air cooling to dissipate heat. The heat generated by the piston when working is transferred to the heat sink through the cylinder body, and then carried away by the flowing air. This method is noisy, dissipates heat unevenly, is greatly affected by the environment, and has poor heat dissipation effect. Utility Model Content
[0004] The technical problem to be solved by the utility model is to overcome the existing defects and provide a two-stroke aircraft engine cylinder head, which adopts water cooling to accurately dissipate heat at the combustion chamber position in the cylinder head body, is not affected by the environment, has low heat dissipation noise, uniform heat dissipation, and good heat dissipation effect, and can effectively solve the problems in the background technology.
[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solution: a two-stroke aircraft engine cylinder head, comprising a cylinder head body, an annular cooling water groove is provided on the side wall of the cylinder head body corresponding to its combustion chamber, a water outlet is provided at the upper end of one side of the cylinder head body corresponding to the annular cooling water groove, and a water inlet is provided at the lower end of the other side of the cylinder head body corresponding to the annular cooling water groove.
[0006] As a preferred technical solution of the present invention, heat dissipation fins are provided on the outer peripheral side of the cylinder head body.
[0007] As a preferred technical solution of the present invention, an air inlet is provided at the lower end of one side of the cylinder head body, and an exhaust port is provided at the middle portion of the other side of the cylinder head body.
[0008] Compared with the prior art, the beneficial effects of the present invention are:
[0009] The two-stroke aircraft engine cylinder head of the utility model adopts water cooling to accurately dissipate heat at the combustion chamber position in the cylinder head body, is not affected by the environment, has low heat dissipation noise, uniform heat dissipation, and good heat dissipation effect. BRIEF DESCRIPTION OF THE DRAWINGS
[0010] Figure 1 This is a schematic diagram of the structure of the utility model;
[0011] Figure 2 for Figure 1 Schematic diagram of the right view structure;
[0012] Figure 3 for Figure 2 Schematic diagram of the cross-sectional structure at AA in the middle;
[0013] Figure 4 for Figure 2 Schematic diagram of the cross-sectional structure at the middle BB;
[0014] Figure 5 for Figure 1 Schematic diagram of the top view structure;
[0015] Figure 6 for Figure 5 Schematic diagram of the cross-sectional structure at CC in the middle;
[0016] Figure 7 It is a three-dimensional diagram of the present utility model.
[0017] In the figure: 1 cylinder head body, 2 air inlet, 3 exhaust port, 4 heat dissipation fins, 5 annular cooling water tank, 51 water outlet, 52 water inlet. DETAILED DESCRIPTION
[0018] 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. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.
[0019] See also Figure 1-7The utility model provides a technical solution: a two-stroke aircraft engine cylinder head, including a cylinder head body 1, an annular cooling water groove 5 is opened on the side wall of the cylinder head body 1 corresponding to its combustion chamber, a water outlet 51 is provided at the upper end of one side of the cylinder head body 1 corresponding to the annular cooling water groove 5, and a water inlet 52 is provided at the lower end of the other side of the cylinder head body 1 corresponding to the annular cooling water groove 5. Cold water enters the annular cooling water groove 5 through the water inlet 52 to perform heat exchange on the combustion chamber part of the cylinder head body 1, thereby cooling it, and the heat exchange water is discharged through the water outlet 51.
[0020] Furthermore, heat dissipation fins 4 are provided on the outer peripheral side of the cylinder head body 1 to assist in cooling the annular cooling water tank 5 .
[0021] Furthermore, an air inlet 2 is provided at the lower end of one side of the cylinder head body 1 , an exhaust port 3 is provided at the middle of the other side of the cylinder head body 1 , and a spark plug mounting hole is provided at the top of the cylinder head body 1 .
[0022] The utility model adopts a water-cooling heat dissipation method to accurately dissipate heat at the combustion chamber position in the cylinder head body 1, is not affected by the environment, has low heat dissipation noise, uniform heat dissipation, and good heat dissipation effect.
[0023] The undisclosed parts of the present invention are all prior art, and their specific structures, materials and working principles will not be described in detail. Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A two-stroke aircraft engine cylinder head, comprising a cylinder head body (1), characterized in that: An annular cooling water groove (5) is provided on the side wall of the cylinder head body (1) corresponding to its combustion chamber, a water outlet (51) is provided at the upper end of one side of the cylinder head body (1) corresponding to the annular cooling water groove (5), and a water inlet (52) is provided at the lower end of the other side of the cylinder head body (1) corresponding to the annular cooling water groove (5).
2. The two-stroke aircraft engine cylinder head according to claim 1, characterized in that: The outer peripheral side of the cylinder head body (1) is provided with heat dissipation fins (4).
3. The two-stroke aircraft engine cylinder head according to claim 1, characterized in that: An air inlet (2) is provided at the lower end of one side of the cylinder head body (1), and an air outlet (3) is provided at the middle of the other side of the cylinder head body (1).