Cooling structure of aero-engine combustion chamber head

Abstract

The invention relates to the technical field of aero-engines, in particular to a cooling structure of an aero-engine combustion chamber head, a plurality of mounting holes are annularly and uniformly distributed in an annular ring, and a plurality of first cooling holes are distributed around the mounting holes; the annular piece is mounted in the mounting hole of the hole ring; the flow guide ring comprises a flow guide ring straight barrel section and a flow guide ring conical barrel section integrally formed at the right end of the flow guide ring straight barrel section, and the flow guide ring straight barrel section is inserted into the inner hole of the annular piece; the splash plate is arranged on the outer peripheral surface of the right end of the annular piece in a sleeving manner, and a first cooling gap is formed between the outer surface of the splash plate and the groove surface of the hole ring in a spaced manner; the first cooling hole is communicated with the first cooling gap; a second cooling gap is formed among the outer surface of the conical cylinder section of the flow guide ring, the right end surface of the annular piece and the inner wall surface of the splash plate; a plurality of cooling inclined holes are annularly and evenly distributed in the annular piece and communicated with the second cooling gap, and the included angle alpha formed by the axis of each cooling inclined hole and the axis of the annular piece is an acute angle.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to a cooling structure for the head of an aero-engine combustion chamber. Background Technology

[0002] The basic functions of the combustion chamber head and flame tube body are to organize and control the fuel-air mixing and combustion process. The flame tube is a major component of the combustion chamber and also the component in the engine subjected to the highest temperature load. The temperature in the combustion zone of the flame tube head can reach over 2100℃, far exceeding the melting point of the flame tube material. The high temperature of the combustion gas at the combustion chamber head, coupled with strong high-temperature radiation and convective heat transfer, and the complex changes in the flow and temperature fields of the main combustion zone, result in poor cooling of the flame tube head wall. This high wall temperature makes it one of the most susceptible areas to ablation. Under the influence of high-temperature combustion gas, the flame tube generates significant thermal stress, creep stress, and fatigue stress, leading to deformation, cracks, wrinkling, and localized overheating and spalling. To ensure the reliability of the flame tube and extend its service life, effective heat insulation and cooling measures must be implemented. The overall goal of flame tube head cooling technology is to minimize the maximum temperature of the flame tube wall while maintaining a low temperature gradient, which is closely related to the flow and temperature fields near the wall.

[0003] In the prior art, patent application CN114110657A discloses a cooling structure for the head of the combustor of a medium-thrust aero-engine. Airflow enters the first cooling gap through a second cooling hole and impacts the guide shield, enhancing convective heat transfer with the guide shield. Subsequently, most of the airflow exiting the first cooling gap forms an air film along the guide shield's conical section, increasing the coverage area of ​​the cooling airflow to protect the downstream of the guide plate. Airflow can also enter the second cooling gap through a through-hole formed by the first and fourth cooling holes, serving two purposes: cooling the sleeve and removing vortices between the sleeve and the guide shield. Airflow can further cool the sleeve by entering the second cooling gap from the first cooling gap through a fifth cooling hole.

[0004] However, the aforementioned prior art CN114110657A has the following problems: Part of the airflow in the second cooling gap comes from the through-hole formed by the first and fourth cooling holes, and the other part comes from the fifth cooling hole. Since the through-hole formed by the first and fourth cooling holes is perpendicular to the axial direction, and this through-hole is perpendicular to the direction of the incoming cooling airflow, it greatly weakens the velocity of the cooling airflow in the second cooling gap. Furthermore, the velocity of the cooling airflow is already weakened when it enters the first cooling gap from the second cooling hole and impacts the guide shield; when it re-enters the second cooling gap through the fifth cooling hole, the velocity is weakened again. These factors result in a weakened cooling airflow velocity in the second cooling gap, leading to a short air film length and a small coverage area after the cooling airflow is ejected from the second cooling gap. Summary of the Invention

[0005] The main objective of this invention is to propose a cooling structure for the combustion chamber head of an aero-engine, aiming to solve the aforementioned technical problems.

[0006] To achieve the above objectives, this invention proposes a cooling structure for the head of an aero-engine combustor, comprising an annular component, a perforated ring, a guide ring, and a splash deflector. The perforated ring has an annular groove and multiple mounting holes evenly distributed around it, with multiple first cooling holes distributed around each mounting hole. The annular component is installed in the mounting holes of the perforated ring. The guide ring includes a straight cylindrical section and a conical section integrally formed at the right end of the straight cylindrical section, with the straight cylindrical section inserted into the inner hole of the annular component. The splash deflector is fitted onto the right end of the annular component. On the outer circumferential surface of the ring, a first cooling gap is formed between the outer surface of the splash deflector and the groove surface of the ring; the first cooling hole is connected to the first cooling gap; the outer surface of the guide ring cone section, the right end face of the ring member, and the inner wall surface of the splash deflector together form a second cooling gap; multiple cooling oblique holes are evenly distributed in a ring on the ring member, and the cooling oblique holes are connected to the second cooling gap; the air inlet and air outlet of the cooling oblique holes are located on the left and right end faces of the ring member, respectively, and the angle α formed by the axis of the cooling oblique holes and the axis of the ring member is an acute angle.

[0007] Preferably, the angle α formed by the axis of the cooling oblique hole and the axis of the annular component is 45 degrees.

[0008] Preferably, an installation ring is fitted on the outer circumferential surface of the left end of the straight section of the guide ring, and two pairs of ear plates are provided on the outer circumferential surface of the installation ring, with the two pairs of ear plates extending to the left; a cyclone separator is installed on the ear plate, and the cyclone separator rotates in the same direction as the inclination direction of the cooling inclined hole.

[0009] Preferably, the mounting ring is fitted onto the outer circumferential surface of the left end of the straight section of the guide ring and then welded and fixed.

[0010] Preferably, the hydrocyclone includes a hydrocyclone housing, and the right half of the hydrocyclone housing is disposed in the inner hole of the guide ring; a third cooling gap is formed between the hydrocyclone housing and the guide ring; a plurality of second cooling holes are evenly distributed in an annular shape on the straight section of the guide ring, and the second cooling holes are located in the area between the mounting ring and the annular component; the second cooling holes are connected to the third cooling gap.

[0011] Preferably, the hydrocyclone shell includes, from left to right, a straight cylindrical section, a middle conical section, and a right-end conical section; the third cooling gap includes an expansion section and a converging ejection section; from left to right, the diameter of the middle conical section gradually decreases, while the diameter of the right-end conical section gradually increases; the outer conical surface of the middle conical section and the inner bore surface of the guide ring straight cylindrical section are spaced apart to form the expansion section of the third cooling gap; the outer conical surface of the right-end conical section and the inner conical surface of the guide ring conical section are spaced apart to form the converging ejection section of the third cooling gap; the outlet of the second cooling hole is directly opposite the outer conical surface of the middle conical section.

[0012] Preferably, screw holes are provided on the ear plates, and the two pairs of ear plates are tightly clamped to the outer circumferential surface of the straight section of the housing and fastened together by screws.

[0013] Preferably, the annular component is inserted into the mounting hole and fixed by welding; the straight section of the guide ring is inserted into the inner hole of the annular component and fixed by welding; the splash shield is sleeved on the outer circumferential surface of the right end of the annular component and fixed by welding.

[0014] Preferably, the expansion angle θ of the splash deflector relative to the combustion chamber axis is 59 degrees.

[0015] Preferably, the first cooling gap spacing is h, the diameter of the first cooling hole is d, the spacing between two adjacent first cooling holes is x, satisfying: 4d≤x≤5d, and h / d=1.6~1.7.

[0016] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows: (1) In this invention, multiple cooling oblique holes are evenly distributed on the annular part, and the cooling oblique holes are connected to the second cooling gap. The air inlet and outlet of the cooling oblique holes are located on the left and right end faces of the annular part, respectively. The angle α formed by the axis of the cooling oblique holes and the axis of the annular part is an acute angle. By adopting the above structure, when the cooling airflow at the head of the combustion chamber impacts the left end face of the annular part, the airflow can directly enter the second cooling gap through the cooling oblique holes. Compared with the prior art, placing the air inlet and outlet of the cooling oblique holes on the left and right end faces of the annular part respectively reduces the speed reduction of the cooling airflow entering the second cooling gap, thereby increasing the length of the gas film formed after the cooling airflow is ejected in the second cooling gap and increasing the coverage area of ​​the gas film. In addition, since the cooling oblique holes are inclined, a rotating airflow with a certain oblique angle is generated. When it is ejected through the slit of the second cooling gap, a rotating gas film is formed, which is beneficial for blowing away abnormally high temperature vortices.

[0017] (2) In this invention, an installation ring is fitted on the outer circumferential surface of the left end of the straight section of the guide ring, and a swirler is installed on the ear plate of the installation ring. The swirling direction of the swirler is the same as the tilting direction of the cooling oblique hole, so that the swirling direction of the rotating gas film formed when the slit of the second cooling gap is ejected is the same as the swirling direction of the airflow ejected by the swirler. This is beneficial to further increase the coverage area of ​​the rotating gas film, improve the cooling efficiency, and thus help to efficiently reduce the wall temperature of the flame tube head and improve the reliability of the flame tube head structure.

[0018] (3) In this invention, by utilizing the structure that connects the second cooling hole and the third cooling gap, the cooling airflow can enter the third cooling gap through the second cooling hole and impact the cyclone shell, thereby cooling the cyclone shell. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the cooling structure provided by the present invention, in which the cyclone separator is not installed; Figure 2 This is a schematic diagram of the cooling structure provided by the present invention, in which a cyclone separator has been installed; Figure 3 This is a three-dimensional model of the mounting ring in this invention; Figure 4 This is a schematic diagram of the perforated ring in this invention; Figure 5for Figure 4 A view with orientation A in the middle; Figure 6 for Figure 5 Sectional view of AA; Figure 7 This is a three-dimensional model diagram of the hole ring in this invention; Figure 8 This is a three-dimensional model diagram of the flow guide ring in this invention; Figure 9 This is a three-dimensional model diagram of the splash guard in this invention; Figure 10 This is a three-dimensional structural diagram of the ring-shaped component in this invention; Figure 11 This is a schematic diagram showing the inclination angle of the cooling oblique holes on the annular component in this invention; Figure 12 This is a front view of the annular component in this invention; Figure 13 This is a three-dimensional model diagram of the cooling structure provided by the present invention, in which the cyclone separator is not installed.

[0021] Figure 14 This is a simplified diagram of the first cooling gap formed by the perforated ring and the splash guard in this invention; Figure 15 This is the head flow field when the expansion angle of the splash guard is 57° in this invention; Figure 16 This is the head flow field when the expansion angle of the splash guard is 59° in this invention; Figure 17 This refers to the gas film formed when the included angle α of the cooling oblique holes in this invention is 0°; Figure 18 This refers to the rotating gas film formed when the included angle α of the cooling oblique holes in this invention is 18°. Figure 19 This refers to the rotating gas film formed when the included angle α of the cooling oblique holes in this invention is 30°. Figure 20 This refers to the rotating gas film formed when the included angle α of the cooling oblique holes in this invention is 45°; Reference numerals: 1. Mounting ring; 101. Ear plate; 102. Screw hole; 2. Annular part; 201. Cooling oblique hole; 3. Hole ring; 301. Annular groove; 302. Mounting hole; 303. First cooling hole; 4. Guide ring; 401. Straight section of guide ring; 402. Conical section of guide ring; 403. Second cooling hole; 5. Splash deflector; 6. First cooling gap; 7. Second cooling gap; 8. Swirl generator; 801. Straight section of shell; 802. Middle conical section; 803. Right end conical section; 9. Third cooling gap. Detailed Implementation

[0022] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0023] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0024] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0025] As shown in the attached figures, a cooling structure for the head of an aero-engine combustion chamber includes an annular component 2, a perforated ring 3, a guide ring 4, and a splash deflector 5. The perforated ring 3 is provided with an annular groove 301, and a plurality of mounting holes 302 are evenly distributed in a ring on the perforated ring 3. A plurality of first cooling holes 303 are distributed around each mounting hole 302.

[0026] The annular component 2 is inserted into the mounting hole 302 and fixed by welding.

[0027] The guide ring 4 includes a straight cylindrical section 401 and a conical section 402 integrally formed on the right end of the straight cylindrical section 401. The straight cylindrical section 401 is inserted into the inner hole of the annular part 2 and fixed by welding.

[0028] The splash guard 5 is fitted onto the outer circumferential surface of the right end of the annular part 2 and welded in place.

[0029] Combination Figure 1 and Figure 2 As shown, a first cooling gap 6 is formed between the outer surface of the splash deflector 5 and the inner groove surface of the annular groove 301 of the hole ring 3; the first cooling hole 303 is connected to the first cooling gap 6.

[0030] The outer surface of the guide ring cone section 402, together with the right end face of the annular component 2 and the inner wall of the splash plate 5, forms a second cooling gap 7; a plurality of cooling oblique holes 201 are evenly distributed in a ring on the annular component 2, and the cooling oblique holes 201 are connected to the second cooling gap 7; the air inlet and air outlet of the cooling oblique holes 201 are located on the left and right end faces of the annular component 2, respectively, and the angle α formed by the axis of the cooling oblique holes 201 and the axis of the annular component 2 is an acute angle.

[0031] By adopting the above structure, on the one hand, the airflow enters the first cooling gap 6 through the first cooling hole 303 and impacts the splash plate 5, which can enhance the convective heat transfer with the splash plate 5. Then, the airflow generates a slit air film from the first cooling gap 6 to cool and protect the inner groove surface of the perforated ring 3. Most of the airflow exiting the first cooling gap 6 forms an air film along the guiding direction of the splash plate 5, increasing the coverage area of ​​the cooling airflow to protect the downstream of the perforated ring 3 and improve the cooling efficiency of the flame tube head.

[0032] Secondly, when the cooling airflow impacts the left end face of the annular component 2, the airflow can directly enter the second cooling gap through the cooling oblique hole 201. Compared with the prior art, placing the air inlet and outlet of the cooling oblique hole 201 on the left and right end faces of the annular component 2 respectively reduces the reduction in the speed of the cooling airflow entering the second cooling gap 7, thereby increasing the length of the air film formed after the cooling airflow is ejected in the second cooling gap 7 and increasing the coverage area of ​​the air film. In addition, since the cooling oblique hole 201 is inclined, it generates a rotating airflow with a certain oblique angle. When it is ejected through the slit of the second cooling gap 7, it forms a rotating air film, which is beneficial for blowing away abnormally high temperature vortices.

[0033] Combination Figures 10 to 12 As shown, the angle α formed by the axis of the cooling oblique hole 201 and the axis of the annular component 2 is 45 degrees. Specifically, there are 20 cooling oblique holes 201, with a diameter of φ2.1~φ2.5mm.

[0034] To determine the angle α formed by the axis of the cooling oblique hole 201 and the axis of the annular component 2, flow field simulations were performed on the cooling structures formed by the cooling oblique hole 201 with angles of 0°, 15°, 30°, and 45°. The near-wall flow field of the splash plate 5 at different angles is shown in the figure. Figures 17 to 20 As shown.

[0035] When the included angle α of the cooling inclined hole 201 is 0°, the cooling airflow velocity is relatively small, the convective heat transfer is weak, and the gas film coverage is incomplete. Especially at the edge of the splash plate 5, the effect of isolating the combustion gas is poor.

[0036] As the inclination angle of the cooling oblique hole 201 increases, the cooling airflow coverage area increases, the air film becomes more uniform, and the cooling airflow velocity increases, thus enhancing convective heat transfer. Considering that the cooling airflow exiting the cooling oblique hole 201 of the annular part 2 also needs to impact the cooling guide ring 4, if the angle of the oblique hole is too large, its impact cooling performance will be reduced. Therefore, taking into account the coverage area of ​​the rotating air film, the airflow velocity, and the impact cooling on the guide ring 4, the angle of the cooling oblique hole 201 on the annular part 2 is determined to be 45°.

[0037] Combination Figures 1 to 3 As shown, an installation ring 1 is fitted onto the outer circumferential surface of the left end of the straight cylindrical section 401 of the guide ring, and the straight cylindrical section 401 of the guide ring is welded and fixed to the installation ring 1. Two pairs of ear plates 101 are provided on the outer circumferential surface of the installation ring 1, and the two pairs of ear plates 101 extend to the left; a cyclone separator 8 is installed on the ear plate 101, and the cyclone separator 8 rotates in the same direction as the inclination direction of the cooling inclined hole 201.

[0038] Since the swirling direction of the cyclone separator 8 is the same as the tilting direction of the cooling oblique hole 201, the swirling direction of the rotating gas film formed when the second cooling gap 7 is ejected is the same as the swirling direction of the airflow ejected from the cyclone separator 8. This is beneficial to further increase the coverage area of ​​the rotating gas film, improve the cooling efficiency, and thus help to efficiently reduce the wall temperature of the flame tube head and improve the reliability of the flame tube head structure.

[0039] Combination Figure 2 As shown, the hydrocyclone 8 includes a hydrocyclone shell, and the right half of the hydrocyclone shell is disposed in the inner hole of the guide ring 4; a third cooling gap 9 is formed between the hydrocyclone shell and the guide ring 4; a plurality of second cooling holes 403 are evenly distributed in a ring on the straight cylindrical section 401 of the guide ring, and the second cooling holes 403 are located in the area between the mounting ring 1 and the annular member 2; the second cooling holes 403 are connected to the third cooling gap 9. Cooling fluid can enter the third cooling gap 9 through the second cooling holes 403 and impact the hydrocyclone shell, thereby cooling the hydrocyclone shell.

[0040] Further, the cyclone separator housing includes, from left to right, a straight cylindrical section 801, a middle conical section 802, and a right-end conical section 803; the third cooling gap 9 includes an expansion section 901 and a converging ejection section 902; from left to right, the diameter of the middle conical section 802 gradually decreases, while the diameter of the right-end conical section 803 gradually increases. The outer conical surface of the middle conical section 802 is spaced apart from the inner bore surface of the straight cylindrical section 401 of the guide ring to form the expansion section 901 of the third cooling gap 9; the outer conical surface of the right-end conical section 803 is spaced apart from the inner conical surface of the conical section 402 of the guide ring to form the converging ejection section 902 of the third cooling gap 9; the outlet of the second cooling hole 403 is directly opposite the outer conical surface of the middle conical section 802.

[0041] By adopting the above structure, the cooling airflow enters the third cooling gap 9 through the second cooling hole 403 and impacts the outer cone surface of the middle cone section 802 for cooling. The cooling airflow expands in the expansion section 901 and enters the convergent ejection section 902. The airflow in the third cooling gap 9 can cool both the cyclone shell and the guide ring 4.

[0042] Combination Figure 3 As shown, screw holes 102 are provided on the ear plate 101, and the two pairs of ear plates 101 are tightly attached to the outer circumferential surface of the straight cylindrical section 801 of the housing and fastened together by screws.

[0043] In this embodiment, the surfaces of the splash shield 5 and the flow guide ring 4 are coated with high-temperature magnetic paint, which can enhance the thermal protection of the splash shield 5 and the flow guide ring 4 and increase their service life.

[0044] Combination Figure 1 As shown, the expansion angle θ of the splash deflector 5 relative to the combustion chamber axis is 59 degrees.

[0045] If the expansion angle of the splash plate 5 is small, the high-temperature gas coming out of the outlet of the cyclone separator 8 will stick to the wall of the splash plate 5, which will easily cause high-temperature erosion of the wall of the splash plate 5, and even cause fire to appear at the edge of the splash plate 5.

[0046] If the expansion angle of the splash plate 5 is too small, the high-temperature gas coming out of the outlet of the cyclone separator 8 will be far away from the wall, which will easily cause high-temperature angular vortices, resulting in local ablation of the splash plate wall.

[0047] Combination Figure 15 and Figure 16 The figures show the head flow fields of the splash guard 5 when the expansion angle θ is 57° and 59°, respectively. It can be seen that; When the expansion angle θ of the splash plate 5 is 57°, the gas coming out of the outlet of the cyclone separator 5 adheres closely to the wall of the splash plate 5, which can easily lead to high-temperature ablation. When the expansion angle θ of the splash plate 5 is 59°, the outlet airflow of the cyclone separator 5 is appropriately far away from the wall surface of the splash plate 5, and there is no angular vortex near the wall surface.

[0048] Therefore, in this embodiment, the expansion angle θ of the splash deflector 5 is determined to be 59°. Thus, in order to ensure the uniformity of the first cooling gap 6, the angle of the inner wall of the annular groove 301 is adaptively designed to be 59°.

[0049] Combination Figure 14The diagram shows a heat transfer model of the first cooling gap formed by the perforated ring and the splash guard. The spacing of the first cooling gap 6 is h, and the diameter of the first cooling hole 303 is d; the spacing between two adjacent first cooling holes 303 is x; satisfying: 4d≤x≤5d, and h / d=1.6~1.7.

[0050] In this embodiment, 102 first cooling holes 303 are distributed around each mounting hole 302. The diameter d of the first cooling hole 303 is designed to be 1.2 mm.

[0051] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A cooling structure for the head of an aero-engine combustion chamber, characterized in that, It includes an annular component (2), a perforated ring (3), a flow guide ring (4), and a splash guard (5); The hole ring (3) is provided with an annular groove (301), and a plurality of mounting holes (302) are evenly distributed in an annular pattern on the hole ring (3). A plurality of first cooling holes (303) are distributed around each mounting hole (302). The annular component (2) is installed in the mounting hole (302) of the perforated ring (3); The guide ring (4) includes a straight section (401) of the guide ring and a conical section (402) of the guide ring integrally formed on the right end of the straight section (401), and the straight section (401) of the guide ring is inserted into the inner hole of the annular part (2); The splash deflector (5) is sleeved on the outer circumferential surface of the right end of the annular part (2), and a first cooling gap (6) is formed between the outer surface of the splash deflector (5) and the groove surface of the hole ring (3); the first cooling hole (303) is connected to the first cooling gap (6); The outer surface of the guide ring cone section (402) and the right end face of the annular part (2) and the inner wall surface of the splash plate (5) together form a second cooling gap (7). Multiple cooling oblique holes (201) are evenly distributed in a ring on the annular part (2), and the cooling oblique holes (201) are connected to the second cooling gap (7); The air inlet and outlet of the cooling oblique hole (201) are located on the left and right end faces of the annular part (2), respectively, and the angle α formed by the axis of the cooling oblique hole (201) and the axis of the annular part (2) is an acute angle.

2. The cooling structure for the combustion chamber head of an aero-engine as described in claim 1, characterized in that, The angle α formed by the axis of the cooling oblique hole (201) and the axis of the annular part (2) is 45 degrees.

3. The cooling structure for the combustion chamber head of an aero-engine as described in claim 1, characterized in that, An installation ring (1) is fitted on the outer circumferential surface of the left end of the straight section (401) of the guide ring. Two pairs of ear plates (101) are provided on the outer circumferential surface of the installation ring (1), and the two pairs of ear plates (101) extend to the left. A cyclone separator (8) is installed on the ear plate (101), and the cyclone separator (8) rotates in the same direction as the inclination direction of the cooling inclined hole (201).

4. The cooling structure for the combustion chamber head of an aero-engine as described in claim 3, characterized in that, After the mounting ring (1) is fitted onto the outer circumferential surface of the left end of the straight section (401) of the guide ring, it is welded and fixed.

5. The cooling structure for the combustion chamber head of an aero-engine as described in claim 3, characterized in that, The hydrocyclone (8) includes a hydrocyclone housing, and the right half of the hydrocyclone housing is disposed in the inner hole of the guide ring (4); a third cooling gap (9) is formed between the hydrocyclone housing and the guide ring (4). Multiple second cooling holes (403) are evenly distributed in a ring on the straight cylindrical section (401) of the flow guide ring, and the second cooling holes (403) are located in the area between the mounting ring (1) and the annular part (2); The second cooling hole (403) is connected to the third cooling gap (9).

6. The cooling structure for the combustion chamber head of an aero-engine as described in claim 5, characterized in that, The hydrocyclone shell, from left to right, includes a straight section (801), a middle conical section (802), and a right-end conical section (803). The third cooling gap (9) includes an expansion section (901) and a convergent ejection section (902). From left to right, the diameter of the middle conical section (802) gradually decreases, and the outer conical surface of the middle conical section (802) and the inner hole surface of the straight section (401) of the guide ring are spaced apart to form the expansion section (901) of the third cooling gap (9). From left to right, the diameter of the right end conical section (803) gradually increases, and the outer conical surface of the right end conical section (803) and the inner conical surface of the guide ring conical section (402) are spaced apart to form the converging ejection section (902) of the third cooling gap (9). The outlet of the second cooling hole (403) is directly opposite the outer conical surface of the middle conical section (802).

7. The cooling structure for the combustion chamber head of an aero-engine as described in claim 6, characterized in that, Screw holes (102) are provided on the ear plates (101), and the two pairs of ear plates (101) are tightly attached to the outer circumferential surface of the straight cylindrical section (801) of the housing and fastened together by screws.

8. The cooling structure for the combustion chamber head of an aero-engine as described in claim 1, characterized in that, The annular component (2) is inserted into the mounting hole (302) and fixed by welding; the straight section (401) of the guide ring is inserted into the inner hole of the annular component (2) and fixed by welding; the splash plate (5) is sleeved on the outer circumferential surface of the right end of the annular component (2) and fixed by welding.

9. The cooling structure for the combustion chamber head of an aero-engine as described in claim 1, characterized in that, The expansion angle θ of the splash deflector (5) relative to the combustion chamber axis is 59 degrees.

10. The cooling structure for the combustion chamber head of an aero-engine as described in claim 1, characterized in that, The spacing of the first cooling gap (6) is h, the diameter of the first cooling hole (303) is d, the spacing between two adjacent first cooling holes (303) is x, and the following conditions are met: 4d≤x≤5d, and h / d=1.6~1.7.

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