Combustion chamber and engine

Abstract

The invention provides a combustion chamber and an engine, and belongs to the technical field of engine combustion chambers. The flame tube is arranged inside the cartridge receiver, an annular cavity is formed between the flame tube and the cartridge receiver, an air inlet hole and a vortex sheet are arranged on the head of the flame tube, and a plurality of main combustion holes and mixing holes are formed in an outer ring and an inner ring of the flame tube; the pre-evaporation device is arranged on an outer ring of the flame tube, and the outlet end of the pre-evaporation device is inserted into the flame tube; one end of the fuel manifold is connected with the fuel supply channel, and the other end is connected with the pre-evaporation device. Through the matching design of a pre-evaporation device and an annular vortex field, by means of the excellent flame propagation characteristic of a flame tube at the head of an annular vortex, the problem that the stable working boundary of a traditional pre-evaporation combustion chamber is narrow is solved, and stable operation of the combustion chamber is guaranteed while expensive multi-stage centrifugal nozzles and swirlers are replaced; according to the combustion chamber, the problem that in the prior art, the stable working boundary of a pre-evaporation combustion chamber is narrow is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of engine combustion chambers, and in particular to a combustion chamber and an engine. Background Art

[0002] Combustion chambers, where fuel or propellant burns to produce high-temperature combustion gases, are manufactured from high-temperature resistant alloys and are crucial components of gas turbine engines, ramjets, and rocket engines. Multi-stage swirlers and dual-oil centrifugal nozzles are widely used in traditional combustion chambers due to their superior performance. However, these devices are complex, require precise dimensions, and are expensive, making them difficult to meet the growing demand for cost reduction.

[0003] As one of the three major components of an aircraft gas turbine, reducing the manufacturing cost of the combustor can significantly improve the economic efficiency of the gas turbine. Currently, an effective means of reducing combustor costs is to eliminate the highly complex multi-channel fuel nozzle and multi-stage swirler design and adopt a fuel evaporation design to achieve fuel atomization. The fuel pre-evaporation design has the advantages of simple structure and low cost.

[0004] However, the flame stabilization working boundary of the above scheme is relatively narrow. Although aerodynamic assistance is used to promote fuel atomization, the atomization performance deteriorates sharply in a low-temperature and low-pressure environment or when the air flow is small, resulting in poor ignition performance in the combustion chamber. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problem of narrow stable working boundary of the pre-evaporation combustion chamber in the prior art, thereby providing a combustion chamber and an engine.

[0006] In order to solve the above technical problems, the present invention provides a combustion chamber, comprising: a casing, a flame tube, a pre-evaporation device and a fuel main pipe; the flame tube is arranged inside the casing, and an annular cavity is formed between the flame tube and the casing, the flame tube comprises a head, an outer ring and an inner ring, the outer ring and the inner ring are respectively arranged on both sides of the head, the head of the flame tube is provided with an air intake hole and a swirl sheet, the swirl sheet has a plurality of parallel arrangements, the air intake holes are arranged in a plurality of rows along an extension direction parallel to the swirl sheet, the outer ring and the inner ring are provided with a plurality of main combustion holes and mixing holes, the main combustion holes and the mixing holes are each arranged in a row along an extension direction perpendicular to the swirl sheet; the pre-evaporation device is arranged on the outer ring of the flame tube, and the outlet end of the pre-evaporation device is inserted into the interior of the flame tube; the fuel main pipe is arranged in the annular cavity, one end of the fuel main pipe is connected to the oil supply channel, and the other end of the fuel main pipe is connected to the pre-evaporation device.

[0007] During use, the fuel main pipe transports the fuel to the pre-evaporation device, where the fuel is preheated, premixed and pre-evaporated, and finally sprayed into the flame tube for combustion. Under the joint action of the air inlet, vortex sheet, mixing hole and main combustion hole jet, a spiral stepping annular vortex flow with a "spring" structure and axial backflow and tangential motion components is formed in the annular cavity inside the flame tube, providing a flow field environment for stable combustion. By matching the pre-evaporation device with the annular vortex flow field, expensive multi-stage centrifugal nozzles and swirlers are replaced while ensuring the stable operation of the combustion chamber. With the help of the superior flame propagation characteristics of the annular vortex head flame tube, the problem of the narrow stable working boundary of the traditional pre-evaporation combustion chamber can be overcome. The combustion chamber provided by the present invention solves the problem of the narrow stable working boundary of the pre-evaporation combustion chamber in the prior art.

[0008] Optionally, the pre-evaporation device includes: a pre-mixing pre-evaporation section and a pre-heating section; the pre-mixing pre-evaporation section is arranged on the outer ring, and the outlet end of the pre-mixing pre-evaporation section is inserted into the interior of the flame tube; the pre-heating section is arranged on the outer ring, the inlet end of the pre-heating section is connected to the fuel main pipe, and the outlet end of the pre-heating section is connected to the pre-mixing pre-evaporation section, and the pre-heating section is provided with at least two groups on both sides of the pre-mixing pre-evaporation section. Through the above arrangement, the fuel main pipe transports the fuel to the pre-heating section, and the pre-heating section can absorb the heat from the flame tube wall to stably increase the fuel, promote the evaporation and atomization of the fuel in the pre-mixing pre-evaporation section, and at the same time, reduce the temperature of the flame tube by absorbing heat from the fuel, thereby achieving the purpose of thermal protection; the pre-heating section is provided on both sides of the pre-mixing pre-evaporation section, which can cause the fuel to collide with each other and break, and then under the action of the pre-mixing pre-evaporation section, the fuel is atomized, evaporated and pre-mixed by means of pneumatic atomization.

[0009] Optionally, the preheating section includes: a diverter pipe, a heat absorbing pipe, and a manifold. The diverter pipe is connected to the fuel main pipe. A plurality of heat absorbing pipes are provided on the diverter pipe. The end of the heat absorbing pipe away from the diverter pipe is connected to the manifold. The manifold is connected to the premixing and pre-evaporating section. The manifolds of the two preheating sections are symmetrically arranged on both sides of the premixing and pre-evaporating section. Through the above arrangement, after the fuel enters the preheating section, it is diverted by the diverter pipe and enters each heat absorbing pipe respectively. Then, it converges in the manifold and enters the premixing and pre-evaporating section in a head-on collision posture. In the premixing and pre-evaporating section, a dispersed group of fuel droplets is formed by the dual action of aerodynamic force and impact force, and finally enters the flame tube to realize premixed combustion. The provision of a preheating section to absorb heat can eliminate the cooling design of the outer ring of the flame tube, thereby reducing the demand for cooling air and the processing cost of the cooling holes, further realizing a low-cost design of the combustion chamber.

[0010] Optionally, the fuel main pipe is provided with a plurality of branch pipes connected to the diverter pipes, and the number of the branch pipes is equal to the number of the diverter pipes. With this arrangement, the branch pipes of the fuel main pipe realize a primary parallel connection of the fuel, and the diverter pipes of the preheating unit realize a secondary parallel connection of the fuel. This two-stage parallel connection achieves uniform preheating of the fuel on the flame tube.

[0011] Optionally, the fuel manifold is disposed at the end of the flame tube, and the heat absorption tube extends from the end of the flame tube toward the head of the flame tube. With the above arrangement, the heat absorption tube extends from the end of the flame tube toward the head of the flame tube to form an "I-shaped" structure. The fuel manifold is disposed at the end of the flame tube primarily because the cooling source is strongest when the fuel just enters the flame tube, while the temperature at the head of the combustion chamber is generally lower, while the temperature in the middle section of the flame tube between the main combustion hole and the mixing hole is higher. Therefore, in combination with the "I-shaped" heat absorption tube, the low-temperature fuel first flows through the middle section of the flame tube where the heat load is higher, and finally converges near the head. The two-stage parallel preheating section and the "I-shaped" heat absorption tube structure disposed on the outer annular wall of the flame tube allow the fuel to be fully preheated, increasing the fuel temperature, reducing the fuel viscosity, and improving the fuel atomization and evaporation performance. Simultaneously, the outer annular wall of the flame tube is cooled, thereby saving approximately 10% of the combustion chamber gas consumption and reducing the processing of the outer annular cooling holes of the flame tube.

[0012] Optionally, the premixing and pre-evaporating section includes an air intake section, a mixing section, and an expansion section. The mixing section connects the air intake section and the expansion section. The air intake section is connected to the manifold via a connecting pipe. The cross-section of the connecting pipe gradually decreases from the manifold toward the air intake section. The cross-sectional diameter of the connecting pipe at the interface with the premixing and pre-evaporating section is 0.4 to 1.0 mm. The expansion section is inserted into the interior of the flame tube. Through the above arrangement, after the preheating section's manifold collects the fuel, the pressure drop and velocity distribution within the preheating section can be adjusted by controlling the area of the interface between the connecting pipe and the air intake section. The high-temperature fuel is injected into the air intake section of the premixing and pre-evaporating section through the connecting pipe with a reduced cross-section. The large-diameter air intake in the air intake section and the combustion structure of the flame tube achieve effective thermal protection of the cavity, solving the problem of easy ablation of the evaporating tube and replacing the expensive multi-stage cyclone design.

[0013] Optionally, the connection between the air intake section and the mixing section is configured as a vertical bend. Through the above configuration, the vertical bend can prevent fuel from flowing back into the annular cavity space between the outer ring of the flame tube and the casing.

[0014] Optionally, the mixing section is circumferentially deflected by -30° to -10° around the air inlet section, and the expansion section is circumferentially deflected by 30° to 50°.

[0015] Optionally, the expansion section is configured to contract first and then expand, with an expansion angle of 35° to 50°. With this configuration, the oil-gas mixture, after being mixed in the mixing section, flows into the flame tube along the expansion angle of the expansion section. This angle helps to distribute the oil-gas mixture more evenly within the flame tube, thereby increasing the flame propagation range.

[0016] The present invention provides an engine comprising a compressor, a turbine, and a combustion chamber according to any one of the above-mentioned solutions, wherein the combustion chamber is arranged between the compressor and the turbine. Due to the use of the above-mentioned combustion chamber, any of the above-mentioned advantages is achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 A schematic diagram of an embodiment of a combustion chamber provided in an embodiment of the present invention;

[0019] Figure 2 for Figure 1 Schematic diagram of the mid-flame tube;

[0020] Figure 3 for Figure 2 Schematic diagram of the pre-evaporation device;

[0021] Figure 4 for Figure 3 Schematic diagram of the premixing and preevaporation section from the first perspective;

[0022] Figure 5 for Figure 3 Schematic diagram of the premixing and preevaporation section from a second perspective;

[0023] Figure 6 This is a schematic diagram of an embodiment of an engine provided in an embodiment of the present invention.

[0024] Description of reference numerals:

[0025] 1. Casing; 2. Combustion chamber; 21. Head; 22. Outer ring; 23. Inner ring; 24. Air inlet; 25. Swirl plate; 26. Main combustion hole; 27. Mixing hole; 3. Pre-evaporation device; 31. Pre-mixing and pre-evaporation section; 311. Air inlet section; 312. Mixing section; 313. Expansion section; 32. Preheating section; 321. Diverter pipe; 322. Heat absorption pipe; 323. Converging pipe; 4. Fuel main pipe; 5. Branch pipe; 6. Connecting pipe; 7. Compressor; 8. Turbine. DETAILED DESCRIPTION

[0026] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of the present invention.

[0027] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0028] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0029] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0030] This embodiment provides a structure of a combustion chamber 2 that can reduce costs and solve the problem of a narrow stable working margin of the pre-evaporation combustion chamber 2 , and is used to provide high-temperature combustion gas to the engine.

[0031] like Figure 1 、 Figure 2As shown, a specific embodiment of a combustion chamber 2 provided in this embodiment includes: a casing 1, a flame tube, a pre-evaporation device 3 and a fuel main pipe 4; the flame tube is arranged inside the casing 1, and an annular cavity is formed between the flame tube and the casing 1. The flame tube includes a head 21, an outer ring 22 and an inner ring 23, and the outer ring 22 and the inner ring 23 are respectively arranged on both sides of the head 21. The head 21 of the flame tube is provided with an air inlet 24 and a swirl sheet 25. The swirl sheet 25 has a plurality of parallel arrangements, and the air inlet 24 is arranged along a direction parallel to the The vortex sheet 25 is provided with several rows in the extension direction, and the outer ring 22 and the inner ring 23 are provided with several main combustion holes 26 and mixing holes 27, and the main combustion holes 26 and the mixing holes 27 are each provided in a row along the extension direction perpendicular to the vortex sheet 25; the pre-evaporation device 3 is provided on the outer ring 22 of the flame tube, and the outlet end of the pre-evaporation device 3 is inserted into the interior of the flame tube; the fuel main pipe 4 is provided in the annular cavity, one end of the fuel main pipe 4 is connected to the oil supply channel, and the other end of the fuel main pipe 4 is connected to the pre-evaporation device 3.

[0032] When in use, the fuel main pipe 4 transports the fuel to the pre-evaporation device 3, where the fuel is preheated, premixed and pre-evaporated, and finally sprayed into the flame tube for combustion. Under the joint action of the air inlet 24, the vortex sheet 25, the mixing hole 27 and the main combustion hole 26 jet, a spiral vortex flow with a "spring" structure and tangential motion components is formed in the annular cavity inside the flame tube, providing a flow field environment for stable combustion. By matching the pre-evaporation device 3 with the annular vortex flow field, the expensive multi-stage centrifugal nozzle and swirler are replaced while ensuring the stable operation of the combustion chamber 2. With the help of the excellent flame propagation characteristics of the flame tube of the annular vortex head 21, the problem of the narrow stable working boundary of the traditional pre-evaporation combustion chamber 2 can be overcome; the combustion chamber 2 provided in this embodiment solves the problem of the narrow stable working boundary of the pre-evaporation combustion chamber 2 in the prior art.

[0033] It should be noted that the pre-evaporation device 3, the fuel manifold 4 and the flame tube can be integrated, replacing the multi-oil centrifugal nozzle while reducing the number of components. The fuel manifold 4 is partially embedded in the flame tube.

[0034] like Figure 2 、 Figure 3As shown, in the combustion chamber 2 provided in this embodiment, the pre-evaporation device 3 includes: a premixing pre-evaporation section 31 and a preheating section 32; the premixing pre-evaporation section 31 is arranged on the outer ring 22, and the outlet end of the premixing pre-evaporation section 31 is inserted into the interior of the flame tube; the preheating section 32 is arranged on the outer ring 22, the inlet end of the preheating section 32 is connected to the fuel main pipe 4, and the outlet end of the preheating section 32 is connected to the premixing pre-evaporation section 31, and at least two groups of preheating sections 32 are arranged on both sides of the premixing pre-evaporation section 31. The fuel manifold 4 transports fuel to the preheating section 32. The preheating section 32 absorbs heat from the flame tube wall, steadily increasing the fuel temperature and promoting evaporation and atomization of the fuel within the premixing and preevaporating section 31. The preheating section 32 also reduces the flame tube temperature by absorbing heat, achieving thermal protection. The preheating sections 32 are positioned on either side of the premixing and preevaporating section 31, causing the fuel to collide and break apart. Then, under the action of the premixing and preevaporating sections 31, the fuel is atomized, evaporated, and premixed through pneumatic atomization. Alternatively, the preheating section 32 can be omitted, and cooling can be achieved through other cooling methods, such as cooling holes provided in the flame tube. The fuel is then preheated by absorbing heat during transportation as it is laid along the flame tube in the fuel manifold 4.

[0035] It should be noted that, in order to ensure the evaporation and atomization performance of the fuel and the thermal protection of the flame tube, the preheating part 32 needs to provide a certain oil supply pressure and also cover the wall surface of the flame tube as much as possible.

[0036] like Figure 2 、 Figure 3As shown, in the combustion chamber 2 provided in this embodiment, the preheating part 32 includes: a diverter pipe 321, a heat absorption pipe 322 and a manifold 323. The diverter pipe 321 is connected to the fuel main pipe 4. A plurality of heat absorption pipes 322 are provided on the diverter pipe 321. One end of the heat absorption pipe 322 away from the diverter pipe 321 is connected to the manifold 323. The manifold 323 is connected to the premixing and pre-evaporation part 31. The manifolds 323 of the two preheating parts 32 are symmetrically arranged on both sides of the premixing and pre-evaporation part 31. After entering the preheating section 32, the fuel is divided by the diverter pipe 321 and flows into each of the heat absorption pipes 322. The fuel then converges in the converging pipe 323 and enters the premixing and preevaporating section 31 in pairs, facing each other head-on. Within the premixing and preevaporating section 31, aerodynamic forces and impact forces form dispersed fuel droplets, which ultimately enter the flame tube for premixed combustion. The provision of the preheating section 32 for heat absorption eliminates the need for cooling the flame tube outer ring 22, thereby reducing the need for cooling air and the cost of processing cooling holes, further enabling a low-cost design for the combustion chamber 2. Alternatively, as an alternative embodiment, four or more sets of preheating sections 32 can be provided on either side of the premixing and preevaporating section 31, depending on design requirements.

[0037] Specifically, the number of the heat absorption tubes 322 is 2 to 8 times the number of the diverter tubes 321 and the converging tubes 323 , and the number of the diverter tubes 321 and the converging tubes 323 is twice the number of the premixing and pre-evaporating parts 31 .

[0038] Specifically, the cross-sections of the diverter pipe 321 , the heat absorbing pipe 322 and the converging pipe 323 may be circular, rectangular, triangular or elliptical.

[0039] Specifically, the cross-sectional area of each heat absorption tube 322 can be different, and the cross-sectional area can be used to balance the difference in heat load. The cross-sectional area of the heat absorption tube 322 that is farther away from the outlet of the diverter tube 321 or closer to the local high-temperature area of the flame tube can be appropriately increased.

[0040] like Figure 3 As shown, in the combustion chamber 2 provided in this embodiment, the fuel main pipe 4 is provided with a plurality of branch pipes 5, each of which is connected to the diverter pipe 321. The number of branch pipes 5 is the same as the number of diverter pipes 321. The branch pipes 5 of the fuel main pipe 4 implement a primary parallel connection of the fuel, and the diverter pipe 321 of the preheating unit 32 implements a secondary parallel connection of the fuel. The two-stage parallel connection achieves uniform preheating of the fuel on the flame tube. Specifically, the branch pipe 5 is provided in the middle of the diverter pipe 321. In addition, as an alternative embodiment, the branch pipe 5 can be omitted, and the end of the diverter pipe 321 can be directly connected to the fuel main pipe 4.

[0041] like Figure 2 、 Figure 3 As shown, in the combustion chamber 2 provided in this embodiment, the fuel main pipe 4 is arranged at the end of the flame tube, and the heat absorption pipe 322 is extended from the end of the flame tube toward the head 21 of the flame tube. The heat absorption pipe 322 extends from the end of the flame tube toward the head 21 of the flame tube to form an "I-shaped" structure. The fuel main pipe 4 is arranged at the end of the flame tube mainly because the cold source is the strongest when the fuel just enters the flame tube, and the temperature of the head 21 of the combustion chamber 2 is usually lower, and the temperature of the middle section of the flame tube between the main combustion hole 26 and the mixing hole 27 is higher. Therefore, combined with the "I-shaped" structure of the heat absorption pipe 322, the low-temperature fuel first flows through the middle section of the flame tube with a higher heat load, and finally converges near the head 21. Through the two-stage parallel preheating part 32 and the "I-shaped" structure design of the heat absorption pipe 322 arranged on the wall of the outer ring 22 of the flame tube, the fuel is fully preheated, the fuel temperature is increased, the fuel viscosity is reduced, and the fuel atomization and evaporation performance is improved. At the same time, the wall of the outer ring 22 of the flame tube is cooled, thereby saving about 10% of the gas consumption of the combustion chamber 2 and reducing the processing of the cooling holes of the outer ring 22 of the flame tube. In addition, as an alternative embodiment, the heat absorption tube 322 can also be set to a "U-shaped", "T-shaped", "L-shaped" or other structural forms.

[0042] like Figure 4 、 Figure 5 As shown, in the combustion chamber 2 provided in this embodiment, the premixing and pre-evaporating section 31 includes: an air intake section 311, a mixing section 312 and an expansion section 313, the mixing section 312 connects the air intake section 311 and the expansion section 313, the air intake section 311 is connected to the manifold 323 through a connecting pipe 6, the cross-section of the connecting pipe 6 gradually shrinks from the manifold 323 toward the air intake section 311, the cross-sectional diameter of the connecting pipe 6 at the interface with the premixing and pre-evaporating section 31 is 0.4 to 1.0 mm, and the expansion section 313 is inserted into the interior of the flame tube. After the fuel is collected by the manifold 323 of the preheating section 32, the pressure drop and velocity distribution within the preheating section 32 can be adjusted by controlling the area of the interface between the connecting pipe 6 and the air intake section 311. The high-temperature fuel is sprayed into the air intake section 311 of the premixing and pre-evaporating section 31 through the connecting pipe 6 with a reduced cross-section. The large-diameter air intake of the air intake section 311 and the combustion structure of the flame tube achieve effective thermal protection of the cavity, solve the problem of easy ablation of the evaporating tube, and replace the expensive multi-stage cyclone design. Specifically, the connecting pipe 6 is configured as an "L-shaped" structure. In addition, as an alternative embodiment, the connecting pipe 6 can be omitted, and the manifold 323 is directly connected to the air intake section 311 of the premixing and pre-evaporating section 31.

[0043] like Figure 4 、 Figure 5 As shown, in the combustion chamber 2 provided in this embodiment, the connection between the air intake section 311 and the mixing section 312 is configured as a vertical angle. This vertical angle prevents fuel from flowing back into the annular space between the flame tube outer ring 22 and the casing 1. Alternatively, as an alternative embodiment, the connection between the air intake section 311 and the mixing section 312 can be configured as a non-vertical angle according to design requirements.

[0044] like Figure 3 As shown, in the combustion chamber 2 provided in this embodiment, the mixing section 312 is circumferentially deflected by -30° to -10° around the intake section 311, and the expansion section 313 is circumferentially deflected by 30° to 50°. The premixing and pre-evaporation section 31 forms a "Z-shaped" structure to achieve aerodynamic assistance.

[0045] like Figure 5 As shown, in the combustion chamber 2 provided in this embodiment, the expansion section 313 is configured to first contract and then expand, with an expansion angle of 35° to 50°. After mixing in the mixing section 312, the oil-gas mixture flows into the flame tube along the expansion angle of the expansion section 313. This angle helps to distribute the oil-gas mixture more evenly within the flame tube, increasing the flame propagation range. Alternatively, the expansion section 313 can be configured as a gradually expanding structure according to design requirements.

[0046] Directions:

[0047] like Figure 1 As shown, the combustion chamber 2 provided in this embodiment, when in use, the fuel main pipe 4 transports the fuel to the pre-evaporation device 3, where the fuel is preheated, premixed and pre-evaporated, and finally sprayed into the flame tube for combustion. Under the joint action of the jets of the air inlet 24, the vortex sheet 25, the mixing hole 27 and the main combustion hole 26, a spirally stepped annular vortex flow with a "spring" structure and axial backflow and tangential motion components is formed in the annular cavity inside the flame tube, providing a flow field environment for stable combustion.

[0048] In addition, if Figure 6 As shown, this embodiment also provides an engine, including a compressor 7, a turbine 8 and the combustion chamber 2 described in the above embodiment, and the combustion chamber 2 is arranged between the compressor 7 and the turbine 8 to achieve.

[0049] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will appreciate that other variations or modifications can be made based on the above description. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications derived therefrom remain within the scope of protection of the present invention.

Claims

1. A combustion chamber, characterized in that: include: Receiver (1); A flame tube is arranged inside the casing (1), and an annular cavity is formed between the flame tube and the casing (1). The flame tube comprises a head (21), an outer ring (22) and an inner ring (23), and the outer ring (22) and the inner ring (23) are respectively arranged on both sides of the head (21). An air inlet (24) and a vortex sheet (25) are arranged on the head (21) of the flame tube, and the vortex sheet (25) has a plurality of parallel arranged air inlet holes (24). The air inlet holes (24) are arranged in a plurality of rows along an extension direction parallel to the vortex sheet (25). The outer ring (22) and the inner ring (23) are provided with a plurality of main combustion holes (26) and mixing holes (27), and the main combustion holes (26) and the mixing holes (27) are each arranged in a row along an extension direction perpendicular to the vortex sheet (25); A pre-evaporation device (3) is arranged on the outer ring (22) of the flame tube, and the outlet end of the pre-evaporation device (3) is inserted into the interior of the flame tube; A fuel main pipe (4) is arranged in the annular cavity, one end of the fuel main pipe (4) is connected to the oil supply channel, and the other end of the fuel main pipe (4) is connected to the pre-evaporation device (3).

2. The combustion chamber according to claim 1, characterized in that The pre-evaporation device (3) comprises: A premixing and preevaporating portion (31) is provided on the outer ring (22), and an outlet end of the premixing and preevaporating portion (31) is inserted into the interior of the flame tube; A preheating section (32) is provided on the outer ring (22), an inlet end of the preheating section (32) is connected to the fuel main pipe (4), an outlet end of the preheating section (32) is connected to the premixing and preevaporating section (31), and at least two groups of preheating sections (32) are provided on both sides of the premixing and preevaporating section (31).

3. The combustion chamber according to claim 2, characterized in that The preheating section (32) comprises: a shunt pipe (321), a heat absorption pipe (322) and a confluence pipe (323); the shunt pipe (321) is connected to the fuel main pipe (4); a plurality of heat absorption pipes (322) are provided on the shunt pipe (321); one end of the heat absorption pipe (322) away from the shunt pipe (321) is connected to the confluence pipe (323); the confluence pipe (323) is connected to the premixing and pre-evaporation section (31); and the confluence pipes (323) of the two preheating sections (32) are symmetrically arranged on both sides of the premixing and pre-evaporation section (31).

4. The combustion chamber according to claim 3, characterized in that The fuel main pipe (4) is provided with a plurality of branch pipes (5), the branch pipes (5) are connected to the diverter pipe (321), and the number of the branch pipes (5) is the same as the number of the diverter pipes (321).

5. The combustion chamber according to claim 3, characterized in that The fuel main pipe (4) is arranged at the end of the flame tube, and the heat absorption pipe (322) is extended from the end of the flame tube toward the head (21) of the flame tube.

6. The combustion chamber according to any one of claims 3 to 5, characterized in that The premixing and pre-evaporating section (31) comprises an air intake section (311), a mixing section (312), and an expansion section (313); the mixing section (312) connects the air intake section (311) and the expansion section (313); the air intake section (311) is connected to the manifold (323) via a connecting pipe (6); the cross section of the connecting pipe (6) gradually shrinks from the manifold (323) toward the air intake section (311); the cross section diameter at the interface between the connecting pipe (6) and the air intake section (311) is 0.4 to 1.0 mm; and the expansion section (313) is inserted into the interior of the flame tube.

7. The combustion chamber according to claim 6, characterized in that The connection between the air intake section (311) and the mixing section (312) is configured as a vertical bend.

8. The combustion chamber according to claim 7, characterized in that The mixing section (312) is circumferentially deflected by -30° to -10° around the air inlet section (311), and the expansion section (313) is circumferentially deflected by 30° to 50°.

9. The combustion chamber according to claim 6, characterized in that The expansion section (313) is configured as a structure that contracts first and then expands, with an expansion angle of 35° to 50°.

10. An engine, characterized in that: The invention comprises a compressor (7), a turbine (8) and a combustion chamber (2) according to any one of claims 1 to 9, wherein the combustion chamber (2) is arranged between the compressor (7) and the turbine (8).

Images