Combustion chamber flame tube and power system

Abstract

The invention relates to a combustion chamber flame tube and a power system. The combustion chamber flame tube comprises a flame tube outer ring, a flame tube inner ring, a flame tube head ring, a plurality of nozzles, a plurality of hole sets and a flow guide part. A gap between the flame tube outer ring and the flame tube inner ring forms an annular cavity; the flame tube head ring is connected to the flame tube outer ring and the flame tube inner ring; the multiple nozzles are arranged on the flame tube head ring at intervals. The multiple hole sets are at least arranged on the outer ring of the flame tube and comprise main combustion holes, and the main combustion holes communicate with the annular cavity and the exterior of the flame tube. The flow guide part is arranged on the flame tube outer ring and contained in the annular cavity, at least part of the flow guide part inclines towards the nozzle relative to the axis of the main combustion hole, and the inclination direction of the flow guide part intersects with the center line of the nozzle. According to the combustion chamber flame tube, use of nozzles is reduced, and the manufacturing cost of the combustion chamber flame tube is reduced.

Description

Technical Field

[0001] This application relates to the field of turbine engine technology, and in particular to combustion chamber flame tubes and power systems. Background Technology

[0002] With the rapid development of aviation technology and the increasing demands of users, people have put forward higher requirements for turbine engines, and some new configurations of turbine engines have emerged one after another, such as the tip turbofan engine.

[0003] As one of the three major components of a turbine engine, the combustion chamber is typically located between the compressor and the turbine. It converts the chemical energy in the fuel into heat energy and heats the high-pressure air from the compressor to the allowable temperature before the turbine, allowing it to expand and perform work within the exhaust system. Combustion chambers are generally expensive to manufacture, and reducing their cost is a pressing technical challenge in turbine engine technology. Summary of the Invention

[0004] This application provides a combustion chamber flame tube and a power system, which aim to reduce the manufacturing cost of the combustion chamber flame tube to a certain extent.

[0005] The first aspect of this application provides a combustion chamber flame tube, which includes an outer ring, an inner ring, a head ring, multiple nozzles, multiple orifice groups, and a flow guide. The gap between the outer and inner rings forms an annular cavity. The head ring is connected to the outer and inner rings. Multiple nozzles are spaced apart on the head ring. At least one orifice group is provided on the outer ring, including a main combustion orifice that communicates with the annular cavity and the outside of the flame tube. The flow guide is provided on the outer ring and housed within the annular cavity. At least a portion of the flow guide is inclined relative to the axis of the main combustion orifice and toward the nozzle, and the inclination direction of the flow guide intersects the centerline of the nozzle.

[0006] In some embodiments, the orifice group includes a plurality of main combustion orifices, the plurality of main combustion orifices including a first main combustion orifice and a second main combustion orifice. Along the axial direction of the combustion chamber flame tube, the second main combustion orifice is disposed on the side of the first main combustion orifice away from the nozzle. The guide member includes a first guide section and a second guide section connected together. The first guide section is inclined relative to the axial direction of the first main combustion orifice and toward the nozzle, and the second guide section is inclined relative to the axial direction of the second main combustion orifice and away from the nozzle.

[0007] In some embodiments, the plurality of main combustion holes include a plurality of first main combustion holes and a plurality of second main combustion holes; on the coplanar plane of the centerline of the nozzle and the axis of the combustion chamber flame tube, the plurality of first main combustion holes are located on both sides of the coplanar plane, and the plurality of second main combustion holes are located on both sides of the coplanar plane.

[0008] In some embodiments, the plurality of main combustion holes further includes a third main combustion hole, which is disposed on the side of the second main combustion hole away from the first main combustion hole along the axial direction of the combustion chamber flame tube. The diameters of the first main combustion hole, the second main combustion hole, and the third main combustion hole are not equal.

[0009] In some embodiments, the plurality of main combustion holes include a plurality of third main combustion hole units, which are spaced apart along the axial direction of the combustion chamber flame tube. Each third main combustion hole unit includes a plurality of third main combustion holes, which are spaced apart circumferentially along the outer ring of the flame tube.

[0010] In some embodiments, the axis of the main combustion orifice is parallel to the radial direction of the combustion chamber flame tube.

[0011] In some embodiments, multiple nozzles are arranged at intervals along the circumference of the head ring, and each nozzle corresponds to a group of holes.

[0012] In some embodiments, the number of nozzles is 3 to 6.

[0013] In some embodiments, the diameter of the main combustion orifice is 2mm to 4mm.

[0014] In some embodiments, the orifice group further includes cooling orifices and mixing orifices, at least a portion of the cooling orifices and at least a portion of the mixing orifices being located on the side of the main combustion orifice away from the nozzle along the axial direction of the combustion chamber flame tube, the axial direction of the cooling orifices intersecting the axial direction of the main combustion orifice, the cooling orifices penetrating the outer ring of the flame tube, and the mixing orifices penetrating the outer ring of the flame tube.

[0015] In some embodiments, the orifice group includes a plurality of main combustion orifices and a plurality of cooling orifices, the plurality of main combustion orifices being spaced apart along the axial direction of the combustion chamber flame tube; a portion of the plurality of cooling orifices being located between two main combustion orifices, and another portion of the plurality of cooling orifices being located on the side of the main combustion orifice furthest from the nozzle that is furthest from the nozzle.

[0016] This application provides a power system, which includes a combustion chamber flame tube, which is the combustion chamber flame tube as described above.

[0017] The combustion chamber flame tube and power system provided in this application, wherein the combustion chamber flame tube is equipped with a flow guide, which is inclined relative to the axis of the main combustion orifice and toward the nozzle, and the inclined direction of the flow guide intersects the centerline of the nozzle. Through the synergistic effect of the main combustion orifice and the flow guide inclined toward the nozzle, the airflow forms a spiral flow region in the annular cavity and extends circumferentially toward both sides of the nozzle. The fuel atomized by the nozzle passes through this region, which prolongs its combustion residence time, enabling continuous and complete combustion, and eliminating the need for the swirler used to form backflow in traditional combustion chambers. Moreover, adjacent airflows extending circumferentially toward both sides of the nozzle can connect with each other, thereby achieving a highly efficient and stable flame connection effect, and also increasing the circumferential spacing ratio of the nozzles, thereby reducing the number of nozzles used and lowering the manufacturing cost of the combustion chamber flame tube. Attached Figure Description

[0018] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings, wherein the same or similar reference numerals denote the same or similar features.

[0019] Figure 1 This is a partial structural schematic diagram of a combustion chamber flame tube provided in an embodiment of this application; Figure 2 This is a schematic diagram of the part of the combustion chamber flame tube head ring that is shown in perspective, according to an embodiment of this application. Figure 3 This is a top view of a combustion chamber flame tube provided in an embodiment of this application; Figure 4 This is a partial right view of a combustion chamber flame tube provided in an embodiment of this application; Figure 5 yes Figure 4 A magnified view of a portion of the image; Figure 6 This is a schematic diagram of the combustion chamber flame tube provided in the embodiment of this application.

[0020] Explanation of reference numerals in the attached figures: 10. Combustion chamber flame tube; 10a. Annular cavity; 1. Outer ring of the flame tube; 2. Inner ring of the flame tube; 3. Flame tube head ring; 4. Nozzle; 5. Hole group; 51. Main combustion hole; 51a. First main combustion hole; 51b. Second main combustion hole; 51c. Third main combustion hole; 52. Cooling hole; 53. Mixing hole; 6. Flow guide; 61. First flow guide section; 62. Second flow guide section; X, the axial direction of the combustion chamber flame tube. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0022] Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

[0023] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. It should be noted that, unless otherwise specified, different features in the embodiments of this application can be combined with each other.

[0024] When using terms such as "above," "above," "below," "below," or "relative" to define the positional relationship between two elements, this includes not only the state where the two elements are directly connected, but also the state where the two elements are separated by gaps or other elements. Furthermore, the terms "first," "second," and "third," etc., are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0025] The combustion chamber is one of the three core components of an aero-engine. For aero-engine combustion chambers, achieving good stable combustion and reliable flame connection is a key design indicator. Combustion chambers typically use vortex generators to achieve stable combustion. To ensure reliable flame connection throughout the combustion chamber, the circumferential spacing ratio of the fuel nozzles (i.e., the ratio of the arc length between two adjacent nozzles to the height of the flame tube) is usually designed to be relatively small.

[0026] In related technologies, the combustion chamber comprises a combustion chamber casing, a flame tube, several fuel nozzles, a fuel main pipe connecting each fuel nozzle and supplying fuel to the fuel nozzles, and several swirlers. The swirlers are uniformly assembled on the flame tube in the circumferential direction. The fuel nozzles are matched with the swirlers one by one and extend into the swirlers. During combustion chamber operation, the airflow, pressurized by the compressor components, enters the two-channel annular cavity of the combustion chamber components. It then enters the flame tube through various orifices on the vortex generator, the inner ring, and the outer ring. Part of the air mixes with the atomized fuel injected from the fuel nozzle for efficient combustion; another part cools the flame tube walls; the remaining air mixes with the high-temperature combustion gas to achieve a suitable outlet temperature field quality, thus forming high-temperature, high-pressure combustion gas that drives the turbine components to perform work. The working principle is as follows: after the airflow passes through the swirling blades on the vortex generator and enters the flame tube, it mixes with the atomized fuel injected from the fuel nozzle, forming a single, independent annular vortex-shaped low-speed recirculation zone, generating a stable flame. The flame then ignites the annular vortex fuel-gas mixture at adjacent vortex generator locations, rapidly propagating circumferentially to complete flame coupling and combustion, producing high-temperature, high-pressure combustion gas. Therefore, in the vortex generator stable combustion design method, the vortex generator is a key component for stable combustion. To generate a stable combustion vortex, the internal airflow channels of the vortex generator must be designed with curved blades or orifices. Therefore, precision casting 3D printing technology is required for implementation, which is relatively expensive. In addition, due to the height of the flame tube cavity, the size of the oil-gas annular vortex is relatively small, which requires the nozzle circumferential spacing ratio to be designed to be smaller. The number of circumferentially arranged vortex generators is also larger, which increases the number of fuel nozzles and increases the manufacturing cost of the combustion chamber.

[0027] The combustion chamber flame tube provided in this application, by setting a flow guide and tilting the flow guide relative to the axis of the main combustion orifice toward the nozzle, with the tilting direction of the flow guide intersecting the centerline of the nozzle, allows the airflow to form a spiral flow region within the annular cavity through the synergistic effect of the main combustion orifice and the flow guide tilted toward the nozzle. This spiral flow extends circumferentially toward both sides of the nozzle. The fuel atomized by the nozzle passes through this region, which prolongs its combustion residence time, enabling continuous and complete combustion and eliminating the need for swirlers used to create backflow in traditional combustion chambers. Furthermore, adjacent airflows extending circumferentially toward both sides of the nozzle can connect with each other, thereby achieving a highly efficient and stable flame connection effect. This also increases the circumferential spacing ratio of the nozzles, reducing the number of nozzles used and lowering the manufacturing cost of the combustion chamber flame tube.

[0028] For ease of explanation, the following embodiments use a combustion chamber flame tube according to an embodiment of this application as an example.

[0029] Please refer to Figures 1 to 4This application discloses a combustion chamber flame tube 10, which includes an outer ring 1, an inner ring 2, a head ring 3, multiple nozzles 4, multiple orifice groups 5, and a guide member 6. The gap between the outer ring 1 and the inner ring 2 forms an annular cavity 10a. The head ring 3 is connected to the outer ring 1 and the inner ring 2. The multiple nozzles 4 are spaced apart on the head ring 3. The multiple orifice groups 5 are at least disposed on the outer ring 1, and the orifice groups 5 include a main combustion orifice 51, which communicates with the annular cavity 10a and the outside of the flame tube. The guide member 6 is disposed on the outer ring 1 and housed within the annular cavity 10a. At least a portion of the guide member 6 is inclined relative to the axis of the main combustion orifice 51 and toward the nozzle 4, and the inclination direction of the guide member 6 intersects the centerline of the nozzle 4.

[0030] The combustion chamber flame tube 10 is generally ring-shaped or quasi-ring-shaped.

[0031] The annular cavity 10a is located between the outer ring 1 and the inner ring 2 of the flame tube, and the outer ring 1, the inner ring 2, and the head ring 3 of the flame tube enclose at least a portion of the annular cavity 10a. In some embodiments, the annular cavity 10a includes a main combustion zone, a mixing zone, and a transition zone. The nozzle 4 communicates with the main combustion zone, and the main combustion orifice 51 communicates with the main combustion zone.

[0032] The outer ring 1, inner ring 2, and head ring 3 of the flame tube can be integrally formed; or, they can be separate components. For example, the outer ring 1, inner ring 2, and head ring 3 can be detachably connected for easy replacement and maintenance.

[0033] Multiple hole groups 5 are also provided in the inner ring 2 of the flame tube. For example, the multiple hole groups 5 include a first hole group and a second hole group, with the first hole group provided in the outer ring 1 of the flame tube and the second hole group provided in the inner ring 2 of the flame tube. The outer ring 1 of the flame tube has opposing outer and inner wall surfaces along the thickness direction, and the main combustion hole 51 penetrates the outer ring 1 of the flame tube along the thickness direction to connect the outer and inner wall surfaces of the outer ring 1 of the flame tube.

[0034] In some embodiments, the axial direction of the main combustion port 51 intersects the axial direction x of the combustion chamber flame tube 10. For example, the axial direction of the main combustion port 51 is perpendicular to the axial direction x of the combustion chamber flame tube 10.

[0035] In some embodiments, the orifice group 5 includes a main combustion orifice 51. The main combustion orifice 51 may be an oblong orifice extending circumferentially along the outer ring 1 of the flame tube. Alternatively, the orifice group 5 may include a plurality of main combustion orifices 51, which are spaced apart circumferentially along the outer ring 1 of the flame tube.

[0036] The aforementioned guide member 6 can guide the airflow flowing in from the main combustion port 51 to change the direction of the airflow. The guide member 6 can be connected to the inner wall surface of the outer ring 1 of the flame tube. Alternatively, the guide member 6 can be arranged around the outer ring 1 of the flame tube. In some embodiments, the combustion chamber flame tube 10 includes a plurality of guide members 6, and the plurality of guide members 6 are arranged in a one-to-one correspondence with a plurality of main combustion ports 51.

[0037] Based on the aforementioned structure, compared to the number of nozzles in the flame tubes of the prior art, the number of nozzles 4 in the combustion chamber flame tube 10 provided in this application is reduced by 30% to 50%.

[0038] The combustion chamber flame tube 10 provided in this embodiment of the application, by setting a guide member 6, and tilting the guide member 6 relative to the axis of the main combustion hole 51 towards the nozzle 4, and the tilting direction of the guide member 6 intersecting the center line of the nozzle 4, through the synergistic effect of the main combustion hole 51 and the guide member 6 tilted towards the nozzle 4, causes the airflow to form a spiral flow region in the annular cavity 10a, and extend circumferentially towards both sides of the nozzle 4. The fuel atomized by the nozzle 4 will have its combustion residence time extended when passing through this region, which can achieve continuous and complete combustion, and can also eliminate the need for the swirler used to form backflow in the traditional combustion chamber. Moreover, the adjacent airflows extending circumferentially towards both sides of the nozzle 4 can be connected to each other, thereby achieving a highly efficient and stable flame connection effect, and also increasing the circumferential spacing ratio of the nozzle 4, thereby reducing the number of nozzles 4 used and reducing the manufacturing cost of the combustion chamber flame tube 10.

[0039] See also Figure 5 and Figure 6 Please refer to the following as well. Figures 1 to 4 As shown, the orifice group 5 includes multiple main combustion orifices 51, including a first main combustion orifice 51a and a second main combustion orifice 51b. The structures of the first main combustion orifice 51a and the second main combustion orifice 51b can be different. Along the axial direction x of the combustion chamber flame tube 10, the second main combustion orifice 51b is located on the side of the first main combustion orifice 51a away from the nozzle 4. The flow guide 6 includes a first flow guide section 61 and a second flow guide section 62 connected together. The first flow guide section 61 is inclined relative to the axial direction of the first main combustion orifice 51a and toward the nozzle 4, and the second flow guide section 62 is inclined relative to the axial direction of the second main combustion orifice 51b and away from the nozzle 4.

[0040] Optionally, the diameters of the first main combustion orifice 51a and the second main combustion orifice 51b are different. For example, the diameter of the first main combustion orifice 51a is larger than the diameter of the second main combustion orifice 51b. With this configuration, the main airflow entering the annular cavity 10a flows to the nozzle 4, ensuring that the fuel is fully combusted in the main combustion zone.

[0041] In some embodiments, the plurality of main combustion holes 51 include a plurality of first main combustion holes 51a, each of which is correspondingly disposed to the flow guide 6. And / or, the plurality of main combustion holes 51 include a plurality of second main combustion holes 51b, each of which is correspondingly disposed to the flow guide 6.

[0042] The flow guide 6 includes a first flow guide section 61, a second flow guide section 62, and a transition section. The transition section is located between and connects the first and second flow guide sections 61 and 62. The transition section is connected to the outer ring 1 of the flame tube. The outer ring 1 of the flame tube and the flow guide 6 are integrally formed, or they are separate structures. This arrangement of the flow guide 6 guides a portion of the airflow along the axial direction x of the combustion chamber flame tube 10, moving away from the nozzle 4. The airflow formed by the two flow guide sections 6 can more fully cover the upstream and downstream of the main combustion zone, promoting further reaction of unburned fuel to improve combustion efficiency.

[0043] In some embodiments, such as Figure 3 and Figure 4 As shown, the multiple main combustion holes 51 include multiple first main combustion holes 51a and multiple second main combustion holes 51b. On the coplanar plane of the centerline of the nozzle 4 and the axial direction x of the combustion chamber flame tube 10, the multiple first main combustion holes 51a are located on opposite sides of the coplanar plane, and the multiple second main combustion holes 51b are located on opposite sides of the coplanar plane. The airflow, through the interaction of the main combustion holes 51 and the guide member 6, allows the oil droplets ejected from the nozzle 4 to overlap with those ejected from adjacent fuel nozzles 4. When the igniter operates, igniting a certain oil droplet, the ignition is rapidly transmitted through the overlapping area to the oil droplets formed by other nozzles 4 within the annular cavity 10a, resulting in a highly efficient and stable flame connection effect in the combustion chamber flame tube 10.

[0044] In some embodiments, the plurality of main combustion holes 51 include a plurality of first main combustion holes 51a, which are spaced apart circumferentially along the outer ring 1 of the flame tube and symmetrically located on both sides of a coplanar surface. The plurality of main combustion holes 51 also include a plurality of second main combustion holes 51b, which are spaced apart circumferentially along the outer ring 1 of the flame tube and symmetrically located on both sides of a coplanar surface. The plurality of first main combustion holes 51a and the plurality of second main combustion holes 51b are located on both sides of the nozzle 4, allowing the formed spiral airflow to flow uniformly along both sides of the nozzle 4 and achieve a longer flow distance along the circumference of the annular cavity 10a, thereby reducing the required number of nozzles 4.

[0045] In some embodiments, such as Figure 3 and Figure 5As shown, the plurality of main combustion holes 51 also includes a third main combustion hole 51c. Along the axial direction x of the combustion chamber flame tube 10, the third main combustion hole 51c is located on the side of the second main combustion hole 51b away from the first main combustion hole 51a. The diameters of the first main combustion hole 51a, the second main combustion hole 51b, and the third main combustion hole 51c are not equal. The third main combustion hole 51c is not correspondingly provided with the guide member 6.

[0046] The plurality of main combustion holes 51 also includes a fourth main combustion hole, which is located on the side of the third main combustion hole 51c away from the second main combustion hole 51b along the axial direction x of the combustion chamber flame tube 10. The diameters of the first main combustion hole 51a, the second main combustion hole 51b, the third main combustion hole 51c, and the fourth main combustion hole are not equal. For example, the diameters of the first main combustion hole 51a, the second main combustion hole 51b, the third main combustion hole 51c, and the fourth main combustion hole decrease along the axial direction x of the combustion chamber flame tube 10. Or, for another example, the diameters of the first main combustion hole 51a, the second main combustion hole 51b, the third main combustion hole 51c, and the fourth main combustion hole gradually decrease along the axial direction x of the combustion chamber flame tube 10.

[0047] The multiple main combustion holes 51 include multiple third main combustion hole units, which are spaced apart along the axial direction x of the combustion chamber flame tube 10. Each third main combustion hole unit includes multiple third main combustion holes 51c, which are spaced apart along the circumferential direction of the outer ring 1 of the flame tube.

[0048] In some examples, a first main combustion hole 51a, a second main combustion hole 51b, a third main combustion hole 51c, and a fourth main combustion hole 51c are respectively provided along the axial direction x of the combustion chamber flame tube 10. It can be understood that the multiple main combustion holes 51 form 4 rows along the axial direction x of the combustion chamber flame tube 10.

[0049] In some other embodiments of this application, the orifice group 5 includes a plurality of main combustion orifice units, which are spaced apart along the axial direction x of the combustion chamber flame tube 10. Each main combustion orifice unit includes a plurality of main combustion holes 51, which are spaced apart circumferentially along the outer ring 1 of the flame tube. The number of main combustion orifice units is 4 to 6.

[0050] Please refer to Figure 1 and Figure 5 The axis of the main combustion orifice 51 is parallel to the radial direction of the combustion chamber flame tube 10. The airflow from the compressor can enter the annular cavity 10a directly and vertically in the radial direction to reduce the airflow resistance of the oblique opening.

[0051] The main combustion orifice 51 can be a first main combustion orifice 51a. The airflow enters the annular cavity 10a perpendicular to the direction of the annular cavity 10a through the first main combustion orifice 51a, and is guided to the nozzle 4 by the guide member 6. The guide member 6 can directly turn the radial airflow to the direction of the nozzle 4, and the local backflow near the nozzle 4 is fast, which is beneficial to the deceleration of the atomized fuel and the full mixing.

[0052] The main combustion port 51 can be a second main combustion port 51b. The airflow enters the annular cavity 10a through the second main combustion port 51b in a direction perpendicular to the annular cavity 10a, and is guided by the flow guide 6 to flow away from the nozzle 4.

[0053] The main combustion port 51 can be the third main combustion port 51c, and the airflow enters the annular cavity 10a through the third main combustion port 51c in a direction perpendicular to the annular cavity 10a.

[0054] In some embodiments, a plurality of nozzles 4 are arranged circumferentially along the flame tube head ring 3, and the plurality of nozzles 4 are arranged in a one-to-one correspondence with a plurality of orifice groups 5. The plurality of nozzles 4 are arranged at equal intervals along the circumferential direction of the flame tube head ring 3. Alternatively, the plurality of nozzles 4 are arranged on a portion of the flame tube head ring 3 along its circumferential direction. The number of nozzles 4 is 3 to 6, for example, the number of nozzles 4 is equal to the number of orifice groups 5, which is 4.

[0055] It should be noted that the diameter of the main combustion hole 51 is 2mm to 4mm. Specifically, the diameter of the first main combustion hole 51a can be 3mm to 4mm, the diameter of the second main combustion hole 51b is 2.5mm to 3.5mm, and the diameter of the third main combustion hole 51c is 2mm to 3mm.

[0056] The main combustion hole 51 provided on the outer ring 1 of the flame tube has a suitable aperture, which improves the situation where an excessively large aperture weakens the structural strength of the outer ring 1 wall and improves the situation where insufficient air intake and incomplete combustion are caused by an excessively small aperture.

[0057] like Figure 1 and Figure 3 As shown, the orifice group 5 also includes a cooling orifice 52 and a mixing orifice 53. At least a portion of the cooling orifice 52 and at least a portion of the mixing orifice 53 are located on the side of the main combustion orifice 51 away from the nozzle 4 along the axial direction x of the combustion chamber flame tube 10. The axial direction of the cooling orifice 52 intersects the axial direction of the main combustion orifice 51. The cooling orifice 52 penetrates the outer ring 1 of the flame tube, and the mixing orifice 53 penetrates the outer ring 1 of the flame tube. Along the axial direction x of the combustion chamber flame tube 10, the mixing orifice 53 is located between the cooling orifice 52 and the main combustion orifice 51.

[0058] In some embodiments, the orifice group 5 includes a plurality of main combustion orifice units, a plurality of cooling orifice units, and a plurality of mixing orifice units. The plurality of cooling orifice units are located on the side of the plurality of mixing orifice units located away from the plurality of main combustion orifice units along the axial direction x of the combustion chamber flame tube 10. The plurality of main combustion orifice units are spaced apart along the axial direction x of the combustion chamber flame tube 10, the plurality of mixing orifice units are spaced apart along the axial direction x of the combustion chamber flame tube 10, and the plurality of cooling orifice units are spaced apart along the axial direction x of the combustion chamber flame tube 10.

[0059] In other examples, the orifice group 5 includes multiple main combustion orifice units, multiple cooling orifice units, and multiple mixing orifice units located on the side of the multiple main combustion orifice units away from the nozzle 4 along the axial direction x of the combustion chamber flame tube 10. The multiple cooling orifice units and multiple mixing orifice units are arranged alternately along the axial direction x of the combustion chamber flame tube 10.

[0060] The main combustion hole 51, cooling hole 52 and mixing hole 53 are arranged in a unit to optimize airflow distribution. The main combustion hole 51 ensures the proportion of combustion air, the cooling hole 52 distributes and protects the airflow of the combustion chamber flame tube 10, and the mixing hole 53 regulates and controls the temperature airflow to achieve combustion stability and extend the life of the flame tube.

[0061] In some examples, the orifice group 5 includes a plurality of main combustion orifices 51 and a plurality of cooling orifices 52, wherein the plurality of main combustion orifices 51 are spaced apart along the axial direction x of the combustion chamber flame tube 10. A portion of the plurality of cooling orifices 52 is located between two main combustion orifices 51, and another portion of the plurality of cooling orifices 52 is located on the side of the main combustion orifice 51 furthest from the nozzle 4.

[0062] For example, orifice group 5 includes multiple main combustion orifice units and multiple cooling orifice units. The multiple main combustion orifice units are spaced apart along the axial direction x of the combustion chamber flame tube 10. At least one multiple cooling orifice unit is located between the two main combustion orifice units furthest from the nozzle 4 along the axial direction x of the combustion chamber flame tube 10. The other multiple cooling orifice units are located on the side of the multiple main combustion orifice units furthest from the nozzle 4. Multiple mixing orifices 53 are located between the multiple cooling orifice units. Each cooling orifice unit includes multiple cooling orifices 52, which are spaced apart circumferentially along the outer ring 1 of the flame tube. Each main combustion orifice unit includes multiple main combustion orifices 51, which are spaced apart circumferentially along the outer ring 1 of the flame tube.

[0063] The diameter of the main combustion hole 51 can be greater than or equal to the diameter of the mixing hole 53, and the diameter of the mixing hole 53 can be greater than the diameter of the cooling hole 52.

[0064] This application also provides a power system, which can be a turbine engine power system, such as an aircraft turbine engine power system. This power system includes all the features of the combustion chamber flame tube of the above embodiments, and therefore also has corresponding beneficial effects.

[0065] This application embodiment can also provide an aviation device, which may include the above-described power system or the above-described combustion chamber flame tube.

[0066] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0067] The above embodiments merely illustrate several implementation methods of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.

[0068] Although this application has been described with reference to preferred embodiments, various modifications can be made thereto and components can be replaced with equivalents without departing from the scope of this application. In particular, the technical features mentioned in the various embodiments can be combined in any manner, provided there is no structural conflict. This application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A combustion chamber flame tube, characterized in that, The combustion chamber flame tube includes: The outer ring and inner ring of the flame tube, the gap between the outer ring and the inner ring of the flame tube forming an annular cavity; A flame tube head ring is connected to the outer ring of the flame tube and the inner ring of the flame tube; Multiple nozzles are spaced apart at the head ring of the flame tube; Multiple sets of holes are provided at least on the outer ring of the flame tube, the sets of holes including main combustion holes, the main combustion holes communicating with the annular cavity and the outside of the flame tube; A flow guide is disposed on the outer ring of the flame tube and housed within the annular cavity. At least a portion of the flow guide is inclined relative to the axis of the main combustion orifice and toward the nozzle. The inclination direction of the flow guide intersects the centerline of the nozzle.

2. The combustion chamber flame tube according to claim 1, characterized in that, The orifice group includes a plurality of main combustion orifices, the plurality of main combustion orifices including a first main combustion orifice and a second main combustion orifice. Along the axial direction of the combustion chamber flame tube, the second main combustion orifice is disposed on the side of the first main combustion orifice away from the nozzle. The flow guide includes a first flow guide section and a second flow guide section connected together. The first flow guide section is inclined relative to the axial direction of the first main combustion orifice and toward the nozzle, while the second flow guide section is inclined relative to the axial direction of the second main combustion orifice and away from the nozzle.

3. The combustion chamber flame tube according to claim 2, characterized in that, The plurality of main combustion holes includes a plurality of first main combustion holes and a plurality of second main combustion holes; On the coplanar plane of the centerline of the nozzle and the axis of the combustion chamber flame tube, a plurality of first main combustion holes are located on both sides of the coplanar plane, and a plurality of second main combustion holes are located on both sides of the coplanar plane.

4. The combustion chamber flame tube according to claim 2, characterized in that, The plurality of main combustion holes also includes a third main combustion hole. Along the axial direction of the combustion chamber flame tube, the third main combustion hole is located on the side of the second main combustion hole away from the first main combustion hole. The diameters of the first main combustion hole, the second main combustion hole, and the third main combustion hole are not equal.

5. The combustion chamber flame tube according to claim 2, characterized in that, The plurality of main combustion holes include a plurality of third main combustion hole units, which are spaced apart along the axial direction of the combustion chamber flame tube. Each third main combustion hole unit includes a plurality of third main combustion holes, which are spaced apart circumferentially along the outer ring of the flame tube.

6. The combustion chamber flame tube according to claim 1, characterized in that, The axis of the main combustion hole is parallel to the radial direction of the combustion chamber flame tube.

7. The combustion chamber flame tube according to claim 1, characterized in that, Multiple nozzles are arranged at intervals along the circumference of the head ring of the flame tube, and each nozzle corresponds to one of the multiple orifice groups.

8. The combustion chamber flame tube according to claim 1, characterized in that, The orifice group further includes cooling holes and mixing holes. At least a portion of the cooling holes and at least a portion of the mixing holes are located on the side of the main combustion hole away from the nozzle along the axial direction of the combustion chamber flame tube. The axial direction of the cooling holes intersects the axial direction of the main combustion hole. The cooling holes penetrate the outer ring of the flame tube, and the mixing holes penetrate the outer ring of the flame tube.

9. The combustion chamber flame tube according to claim 8, characterized in that, The orifice group includes a plurality of main combustion orifices and a plurality of cooling orifices. The plurality of main combustion orifices are spaced apart along the axial direction of the combustion chamber flame tube. A portion of the plurality of cooling orifices is located between two of the main combustion orifices, and another portion of the plurality of cooling orifices is located on the side of the main combustion orifice furthest from the nozzle that is furthest from the nozzle.

10. A power system, characterized in that, The combustion chamber flame tube includes any one of claims 1 to 9.

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