combustion chamber

Abstract

The application discloses a combustion chamber, which comprises a casing assembly, a flame tube, an oil supply assembly and a premixing and pre-evaporation pipe. The casing assembly is formed with an inner cavity, an air inlet and a fuel gas outlet. The flame tube is arranged in the inner cavity, and the inner part of the flame tube is divided into a main combustion zone, a ring vortex zone and a mixing zone. The oil supply assembly comprises a main combustion stage nozzle and a standby stage nozzle. The main combustion stage nozzle is installed on the flame tube and is communicated with the main combustion zone. The standby stage nozzle is installed on the head of the flame tube and is communicated with the ring vortex zone. The premixing and pre-evaporation pipe is arranged between the main combustion stage nozzle and the flame tube, and is used for premixing and pre-evaporating the air and oil mist mixture. The application provides a premixing and pre-evaporation low-pollution combustion chamber with wide-range oil-gas adaptability, which effectively reduces the NO X emission, has small flow loss and can obtain a relatively ideal outlet temperature field, realizes the ignition and flame coupling of the full-ring combustion chamber, has high ignition height at high altitudes, and can realize the ignition and flame coupling of the combustion chamber within a wide range of oil-gas ratio. The flame stability of the whole combustion chamber is good.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more particularly to a combustion chamber. Background Technology

[0002] With the rapid development of the aviation industry, the operating environment faced by aero engines is becoming increasingly complex. The problems of reliable ignition under multiple operating conditions in the combustion chamber and stable and efficient combustion over a wide range of fuel and gas are becoming more prominent, and there is an urgent need to carry out research on new combustion schemes and technologies.

[0003] Currently, based on different head characteristics, combustion chambers can be divided into two categories: the first is the annular vortex combustion chamber, which organizes the flow field using swirl vanes and impact holes. It performs excellently in high-altitude ignition but suffers from weak head flow, poor fuel-air mixing, and poor outlet temperature field quality. The second is the swirl combustion chamber, which organizes the flow field using vortex generators. It stabilizes the flame through rotating airflow at the head, enhances fuel-air mixing, and achieves more uniform fuel-air mixing in space, significantly improving the outlet temperature field quality. Based on the concept of zoned combustion, a combination of annular vortex and swirl combustion chambers has emerged in recent years. Due to its stable and efficient combustion over a wide fuel-air range, it is called the WFA (Wide-range Fuel-air Adapted) combustion chamber. This wide-range fuel-air adapted combustion chamber combines the advantages of annular vortex and swirl combustion chambers. On the one hand, it can ensure the ignition performance and combustion efficiency of the combustion chamber under multiple operating conditions; on the other hand, it can effectively improve the fuel-air distribution in the flame tube, ultimately achieving a more uniform outlet temperature field.

[0004] The existing WFA combustion chamber includes components such as the inner casing, outer casing, inner ring of the flame tube, outer ring of the flame tube, diffuser, and nozzles. The main combustion stage nozzle is directly connected to the main combustion zone for fuel intake. The fuel is not pre-evaporated and is not uniformly pre-mixed with air. The lean combustion performance in the main combustion zone is low, and the combustion temperature is high, resulting in higher NO levels. X Emissions are high. Summary of the Invention

[0005] The main objective of this invention is to provide a combustion chamber designed to achieve premixed and pre-evaporated combustion of the main combustion stage fuel in a lean atmosphere, thereby reducing the temperature of the main combustion zone and suppressing NO. X The generation of [something] reduces pollution.

[0006] To achieve the above objectives, the present invention proposes a combustion chamber for use in aero engines, comprising:

[0007] The casing assembly has an inner cavity and an air inlet and a gas outlet communicating with the inner cavity;

[0008] A flame tube is disposed within the inner cavity. The interior of the flame tube is divided into a main combustion zone, a vortex zone, and a mixing zone. The flame tube has an airflow inlet, and the mixing zone of the flame tube is connected to the gas outlet.

[0009] The fuel supply assembly includes a main combustion stage nozzle and a shift nozzle. The main combustion stage nozzle is mounted on the flame tube and communicates with the main combustion zone. The shift nozzle is mounted on the head of the flame tube and communicates with the annular vortex zone.

[0010] A premixing and pre-evaporation tube is located between the main combustion stage nozzle and the flame tube. The premixing and pre-evaporation tube is provided with a mixing and evaporation channel for premixing and pre-evaporating the air-oil mist mixture.

[0011] Optionally, the outlet end of the premixed pre-evaporation tube is provided with a shrinkage nozzle for preventing backfire.

[0012] Optionally, the outlet end of the premixed preevaporation tube is mounted on the flame tube via a swirling assembly. The swirling assembly includes an inner head swirler and an outer head swirler surrounding the inner head swirler. The inner head swirler is connected to the outlet end of the premixed preevaporation tube.

[0013] Optionally, the swirling assembly further includes an inlet swirler, which is disposed at the inlet end of the main combustion stage nozzle and the premixed pre-evaporation tube.

[0014] Optionally, the fuel distribution ratio between the main combustion stage nozzle and the duty nozzle is 4:1.

[0015] Optionally, the head of the flame tube is radially divided into an annular vortex flow head and a swirling flow head. The annular vortex flow head forms the annular vortex region, and the swirling flow head forms the main combustion region. The annular vortex flow head and the swirling flow head are connected by a support plate, and the support plate has a support plate air inlet.

[0016] Optionally, an annular vortex vane is installed inside the top of the annular vortex flow head, an annular vortex air inlet is provided at the top of the annular vortex flow head, an annular vortex front wall jet hole is provided on the front wall of the annular vortex flow head, and an annular vortex rear wall jet hole is provided on the rear wall of the annular vortex flow head.

[0017] Optionally, the duty nozzle is a single-oil-path centrifugal nozzle or a dual-oil-path centrifugal nozzle. The duty nozzle is installed on the front wall of the concave cavity of the annular vortex flow head, and its spray direction is to spray towards the vicinity of the annular vortex swirl plate.

[0018] The main combustion stage nozzle is a single-oil-path centrifugal nozzle or a dual-oil-path centrifugal nozzle, and the main combustion stage nozzle is inserted into the mixing and evaporation channel along the center line of the inlet cyclone separator.

[0019] Optionally, the combustion chamber further includes an igniter, the casing assembly is provided with an ignition nozzle hole, the igniter is installed in the ignition nozzle hole and extends into the annular vortex region, and the ignition nozzle of the igniter is flush with the inner wall surface of the annular vortex flow head.

[0020] Optionally, the inner ring wall of the flame tube is provided with an inner ring main combustion hole, an inner ring mixing hole, and a cooling hole, and the outer ring wall of the flame tube is provided with an outer ring mixing hole; wherein, the inner ring main combustion hole is used to cut off the mainstream reflux zone, supplement combustion, and enhance mainstream oil-gas mixing, and the inner ring mixing hole and the outer ring mixing hole are used to adjust the outlet temperature field; the cooling hole is a fully divergent multi-oblique hole;

[0021] The airflow inlet includes the support plate air inlet, the annular vortex air inlet, the inner ring main combustion inlet, the inner ring mixing inlet, the outer ring mixing inlet, and the cooling inlet.

[0022] In the technical solution of the present invention, the combustion chamber includes a casing assembly, a flame tube, a fuel supply assembly, and a premixing and preevaporation pipe; the casing assembly forms an inner cavity and an air inlet and a gas outlet communicating with the inner cavity; the flame tube is disposed in the inner cavity, and the inner cavity of the flame tube is divided into a main combustion zone, an annular vortex zone, and a mixing zone, and the flame tube has an airflow inlet, and the mixing zone of the flame tube is communicating with the gas outlet; the fuel supply assembly includes a main combustion stage nozzle and a shift nozzle, the main combustion stage nozzle is installed on the flame tube and communicates with the main combustion zone, and the shift nozzle is installed at the head of the flame tube and communicates with the annular vortex zone; the premixing and preevaporation pipe is disposed between the main combustion stage nozzle and the flame tube, and the premixing and preevaporation pipe has a mixing and evaporation channel for premixing and preevaporating the air-fuel mist mixture.

[0023] This invention adds a premixing and pre-evaporation pipe between the main combustion stage nozzle and the main combustion zone, enabling premixed and pre-evaporated combustion of the main combustion stage fuel in a lean atmosphere. This ensures that the fuel in the main combustion zone deviates as much as possible from its stoichiometric ratio during combustion, effectively reducing flame temperature and thus suppressing NO. X The generation of NO ultimately reduces the overall NO emissions in the combustion chamber. X emission. Attached Figure Description

[0024] 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.

[0025] Figure 1 This is a schematic diagram of the structure of an embodiment of the combustion chamber of the present invention;

[0026] Figure 2This is a schematic diagram of the structure of the premixing and pre-evaporation tube, the main combustion stage nozzle, and the swirl assembly in one embodiment of the combustion chamber of the present invention;

[0027] Figure 3 This is a schematic diagram of the structure of the flame tube head in one embodiment of the combustion chamber of the present invention.

[0028] Explanation of icon numbers:

[0029] 10. Casing assembly; 20. Flame tube; 40. Premixed pre-evaporation tube; 60. Diffuser; 201. Main combustion zone; 202. Circular vortex zone; 203. Mixing zone; 31. Main combustion stage nozzle; 32. Shift nozzle; 401. Mixing and evaporation channel; 402. Contraction nozzle; 51. Head inner swirler; 52. Head outer swirler; 53. Inlet swirler; 23. Support plate; 23a. Support plate air inlet; 24. Circular vortex vane; 24a. Circular vortex air inlet; 24b. Circular vortex front wall jet hole; 24c. Circular vortex rear wall jet hole; 10d. Electric nozzle hole; 25a. Inner ring main combustion hole; 25b. Inner ring mixing hole; 25c. Outer ring mixing hole; 25d. Cooling hole.

[0030] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0031] 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.

[0032] It should be noted that if the embodiments of the present invention involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0033] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are 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 those features. Additionally, if the word "and / or" appears throughout the text, it means including three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies A and B. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0034] In recent years, the Aviation Protection Committee (CAEP) of the International Civil Aviation Organization (ICAO) has formulated a series of pollution emission standards and regulations for aircraft power plants, including those for NO. X With increasingly stringent emission restrictions, the European Aviation Research and Advisory Council (ACARE) has proposed that by 2050, NO... X Emissions need to be reduced by 90% compared to 2000 levels. Therefore, low NOx emissions are necessary. X Emissions are a key performance indicator for low-emission combustion chambers. Multiple studies on low-emission combustion technologies have shown that improving lean combustion performance and lowering combustion temperature in the main combustion zone can effectively suppress NOx emissions. X The formation of fuels, and lean premixed pre-evaporation (LPP) combustion is the most promising combustion method. The basic mode of achieving lean premixed pre-evaporation is to pre-evaporate the fuel, mix it evenly with air, enter the main combustion zone, and burn it in a lean atmosphere.

[0035] To address this issue, this invention proposes a combustion chamber applicable to aero-engines, particularly gas turbines. Based on the concept of zoned combustion, this invention relates to a combustion chamber combining annular vortex and swirl types. Due to its stable and efficient combustion over a wide fuel-air range, it belongs to the WFA (Wide-Air-Fuel-Air) combustion chamber category. This combustion chamber integrates the advantages of both annular vortex and swirl-type combustion chambers. On the one hand, it ensures ignition performance and combustion efficiency under various operating conditions; on the other hand, it effectively improves the fuel-air distribution within the flame tube, ultimately achieving a more uniform outlet temperature field.

[0036] refer to Figure 1 and Figure 2In one embodiment of the present invention, the combustion chamber includes a casing assembly 10, a flame tube 20, a fuel supply assembly, and a premixing and preevaporation pipe 40. The casing assembly 10 forms an inner cavity and an air inlet and a gas outlet communicating with the inner cavity. The flame tube 20 is disposed in the inner cavity, and the inner cavity of the flame tube 20 is divided into a main combustion zone 201, an annular vortex zone 202, and a mixing zone 203. The flame tube 20 has an airflow inlet, and the mixing zone 203 of the flame tube 20 communicates with the gas outlet. The fuel supply assembly includes a main combustion stage nozzle 31 and a shift nozzle 32. The main combustion stage nozzle 31 is installed on the flame tube 20 and communicates with the main combustion zone 201, and the shift nozzle 32 is installed at the head of the flame tube 20 and communicates with the annular vortex zone 202. The premixing and preevaporation pipe 40 is disposed between the main combustion stage nozzle 31 and the flame tube 20, and the premixing and preevaporation pipe 40 has a mixing and evaporation channel 401 for premixing and preevaporating the air-fuel mist mixture.

[0037] In this embodiment, the casing assembly 10 may include an inner casing and an outer casing. An air inlet is provided at one end of the casing assembly 10, and a diffuser 60 is installed at the air inlet to pressurize and decelerate the incoming air. A gas outlet is provided at the other end of the casing assembly 10, and the gas outlet end of the flame tube 20 is installed at the gas outlet.

[0038] The flame tube 20 may include an inner ring, an outer ring, and a head. The inner ring and the outer ring of the flame tube 20 form a mixing zone 203. The head of the flame tube 20 is divided into a vortex flow head and a swirl flow head in the radial direction. The vortex flow head forms a vortex zone 202, and the swirl flow head forms a main combustion zone 201.

[0039] The fuel supply assembly also includes a main combustion stage fuel main pipe and a shift fuel main pipe for delivering fuel. The main combustion stage fuel main pipe is connected to the main combustion stage nozzle 31, and the shift fuel main pipe is connected to the shift nozzle 32. The number of both the main combustion stage nozzle 31 and the shift nozzle 32 is at least one, and this is not limited here.

[0040] The shape of the mixing and evaporation channel 401 of the premixing and pre-evaporation tube 40 is not limited, but a circular channel is preferred. The outlet end of the premixing and pre-evaporation tube 40 is provided with a converging nozzle 402, which can play a certain role in preventing backfire. By setting a premixing and pre-evaporation tube 40 with a converging nozzle 402 in the main combustion stage, complete atomization of the fuel in the main combustion stage can be achieved, and the fuel can be fully mixed with air. Furthermore, the design takes into account both backfire and auto-ignition issues, ensuring the normal operation of the LPP working mode.

[0041] This invention combines the main combustion stage of the WFA combustion chamber with LPP combustion technology to achieve premixed and pre-evaporated combustion of the main combustion stage fuel in a lean atmosphere, thereby reducing the 201 temperature in the main combustion zone and suppressing NO. X The generation of [something] reduces pollution.

[0042] Main reference Figure 2 In one embodiment, the outlet end of the premixed pre-evaporation tube 40 can be mounted on the flame tube 20 via a swirling assembly. The swirling assembly includes an inner head swirler 51 and an outer head swirler 52 surrounding the inner head swirler 51. The inner head swirler 51 is connected to the outlet end of the premixed pre-evaporation tube 40.

[0043] In this embodiment, the swirling assembly may further include an inlet swirler 53, which is disposed at the inlet end of the main combustion stage nozzle 31 and the premixed pre-evaporation tube 40.

[0044] The present invention employs an inner head swirler 51 and an outer head swirler 52 design, which can enhance the oil-gas mixing in the main combustion zone 201 without causing significant flow loss, and can also obtain a more ideal outlet temperature field.

[0045] The duty nozzle 32 can be installed on the front wall of the concave cavity. It can be a single-oil-path centrifugal nozzle or a dual-oil-path centrifugal nozzle. The spray direction is a three-dimensional angle including a certain tangential angle, spraying towards the vicinity of the top swirl vane. The main combustion stage nozzle 31 can also be a single-oil-path centrifugal nozzle or a dual-oil-path centrifugal nozzle. It is inserted into the mixing and evaporation channel 401 along the center line of the inlet swirler 53. After passing through the premixing and pre-evaporation section, most of the fuel is completely evaporated. There may be a small number of droplets hitting the wall of the premixing and pre-evaporation tube 40, which are then atomized again at the outlet.

[0046] Since the main combustion stage nozzle 31 uses a centrifugal nozzle to atomize fuel, in LPP operating mode, the main combustion zone 201 can operate in a lean state by adjusting the fuel-air ratio. The fuel mist sprayed from the centrifugal nozzle is atomized under the action of swirling air, and the air-fuel mist mixture enters the mixing and evaporation channel 401 for thorough mixing and evaporation. The fuel distribution ratio between the main combustion stage nozzle 31 and the shift nozzle 32 is approximately 4:1. The equivalence ratio of the premixing and pre-evaporation section is designed to be outside the flammability limit to prevent backfire in this section. At the same time, the residence time of fuel vapor in this section is designed to be outside the auto-ignition time to prevent auto-ignition. The outlet end of the premixing and pre-evaporation pipe 40 adopts a converging nozzle 402 design, which also plays a certain role in preventing backfire.

[0047] In addition, an inner swirler 51 is designed on the outside of the contraction nozzle 402. This inner swirler features a strong swirling, opaque design. A small portion of the main combustion stage air, after passing through the inner swirler, forms a recirculation zone of a certain size downstream. This recirculation zone enhances flame stability and, as an ignition source, independently stabilizes the fuel-air mixture in the main combustion stage, facilitating mutual support between the main combustion stage and the shift control system. Furthermore, it results in a relatively regular spatial distribution of the flow field structure, making it easier to control and organize combustion. The outer swirler 52 can employ a weak swirling, transparent design. This type of swirler combines the advantages of swirling and direct current flow, enhancing fuel-air mixing without causing significant total pressure loss. The LPP design of the main combustion stage incorporates a premixing and pre-evaporation pipe 40, which is structurally convenient for replacement and installation. Simultaneously, the fuel in the main combustion zone 201 is burned as far away from its stoichiometric ratio as possible, effectively reducing flame temperature and thus suppressing NO. X The generation of NO ultimately reduces the overall NO emissions in the combustion chamber. X emission.

[0048] refer to Figure 3 In one embodiment, the annular vortex flow head and the swirling flow head can be connected by a support plate 23, and the support plate 23 has a support plate air inlet 23a.

[0049] The flame control chamber and the main combustion stage are connected by a support plate 23. A small amount of direct airflow can enter the flame tube 20 through the support plate inlet 23a on the front and rear walls of the support plate 23. The design of the support plate 23 serves two purposes: firstly, it protects the flow within the flame control chamber from the influence of the mainstream flow, thus helping the flame control chamber maintain good ignition and extinction performance and wide-range flame stability; secondly, the presence of the support plate 23 enhances the radial flow between adjacent areas of the flame control chamber and the main combustion stage, allowing the flame in the concave cavity to propagate smoothly to the main combustion stage, which is beneficial for flame transfer between the flame control chamber and the main combustion stage. In addition, an axial recirculation zone can be formed downstream of the support plate 23, so the support plate 23 also has a certain flame stabilization capability. Since the flame control chamber, the main combustion stage, and the support plate 23 all have a certain flame stabilization capability, and are spatially independent yet have radial flow, the three can support each other, which can significantly enhance flame stability.

[0050] In other words, the support plate 23 structure protects the independence of the duty shift and the LPP main combustion stage, and also provides the combustion chamber flame stability with "triple protection". At the same time, the "triple protection" can support each other, so the flame stability of the entire combustion chamber is good.

[0051] In addition, the present invention adopts radial grading, which has a compact structure and a small cooling area. The LPP main combustion stage adopts an internal strong and external weak cyclone design scheme, and is matched with a premixed pre-evaporation tube 40. The oil and gas mixing in the main combustion zone 201 is enhanced by using a small total pressure loss, and the outlet temperature distribution of the flame tube 20 is more ideal, effectively reducing the wall temperature of the flame tube 20.

[0052] refer to Figures 1 to 3 In one embodiment, an annular vortex vane 24 is installed at the top of the annular vortex flow head of the combustion chamber, an annular vortex inlet 24a is provided at the top of the annular vortex flow head, an annular vortex front wall jet hole 24b is provided on the front wall of the annular vortex flow head, and an annular vortex rear wall jet hole 24c is provided on the rear wall of the annular vortex flow head.

[0053] The duty nozzle 32 in the combustion chamber can use a centrifugal nozzle for tangential fuel supply. The annular vortex zone 202 forms a large-scale tangential flow in space through the static pressure intake of the annular vortex inlet 24a and the combination of circumferential swirl vanes. Under the interception effect of the jet holes 24b and 24c on the front and rear walls of the annular vortex, multiple recirculation zones of different sizes are formed in the annular vortex zone 202. The duty annular vortex head can achieve reliable ignition and flame connection at high altitudes above 8km with a relatively small number of fuel nozzles, and can also achieve efficient and stable combustion under low operating conditions. It can better undertake the function of flame stabilization to adapt to the variable and complex working environment.

[0054] refer to Figure 1 and Figure 3 In one embodiment, the casing assembly 10 may be provided with a ignition nozzle hole 10d, an igniter is installed in the ignition nozzle hole 10d and extends into the vortex region 202, and the ignition nozzle of the igniter is flush with the inner wall surface of the vortex flow head.

[0055] In this embodiment, the combustion chamber ignition adopts direct ignition using a high-energy ignition nozzle, and the nozzle hole 10d can be opened on the outer casing.

[0056] Main reference Figure 1 In one embodiment, according to the needs of flow, mixing and cooling, the inner ring wall of the flame tube 20 is provided with an inner ring main combustion hole 25a, an inner ring mixing hole 25b and a cooling hole 25d, and the outer ring wall of the flame tube 20 is provided with an outer ring mixing hole 25c. The inner ring main combustion hole 25a is used to cut off the mainstream reflux zone, supplement combustion and enhance the mainstream oil and gas mixing, and the inner ring mixing hole 25b and the outer ring mixing hole 25c are used to adjust the outlet temperature field. The cooling hole 25d is a fully divergent multi-oblique hole, and the angle of the multi-oblique hole is a composite angle with three-dimensional spatial angle.

[0057] refer to Figure 1 and Figure 3 In this embodiment, the airflow inlet of the flame tube 20 includes a support plate air inlet 23a, a ring vortex air inlet 24a, an inner ring main combustion hole 25a, an inner ring mixing hole 25b, an outer ring mixing hole 25c, and a cooling hole 25d.

[0058] In this embodiment, the combustion chamber is designed with six airflow inlets, thus the flame tube 20 can be divided into a main combustion zone 201, an annular vortex zone 202, and a mixing zone 203. The annular vortex zone 202 mainly undertakes the ignition and flame-coupling function, while the main combustion zone 201 can achieve low NO through LPP technology. X Therefore, it plays a key role in reducing NO. X The effect of emissions, and the mixing zone 203 helps to obtain a more uniform outlet temperature field of the flame tube 20.

[0059] This invention provides a wide-range, low-emission LPP combustor that adapts to both oil and gas environments. It combines the characteristics of both annular vortex and swirl combustors, and aerodynamically shares similarities with conventional combustors. Air is pressurized and decelerated by a diffuser 60 before entering the combustor, and is also divided into three paths, entering the interior of the flame tube 20 through the inner ring, outer ring, and head of the flame tube 20. Fuel enters the interior of the flame tube 20 radially through the duty nozzle 32 and the main combustion stage nozzle 31. The duty nozzle is located on the outer side of the inner cavity of the casing assembly 10, while the main combustion stage is located on the inner side of the inner cavity of the casing assembly 10.

[0060] The above description is merely an optional embodiment of the present invention and does not limit the patent scope of the present invention. All 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 combustion chamber used in an aero engine, characterized in that, include: The casing assembly has an inner cavity and an air inlet and a gas outlet communicating with the inner cavity; A flame tube is disposed within the inner cavity. The interior of the flame tube is divided into a main combustion zone, a vortex zone, and a mixing zone. The flame tube has an airflow inlet. The mixing zone of the flame tube is connected to the gas outlet. The head of the flame tube is radially divided into a vortex flow head and a swirl flow head. The vortex flow head forms a vortex zone, and the swirl flow head forms a main combustion zone. The vortex flow head and the swirl flow head are connected by a support plate, which has a support plate air inlet. A vortex vane is installed inside the top of the vortex flow head, and a vortex air inlet is provided at the top of the vortex flow head. A vortex inlet is provided on the front wall of the vortex flow head. The flame tube has a rear wall jet orifice, and the rear wall of the annular vortex flow head is provided with an annular vortex rear wall jet orifice; the inner annular wall of the flame tube is provided with an inner annular main combustion orifice, an inner annular mixing orifice, and a cooling orifice, and the outer annular wall of the flame tube is provided with an outer annular mixing orifice; wherein, the inner annular main combustion orifice is used to cut off the mainstream recirculation zone, supplement combustion, and enhance mainstream oil-gas mixing, and the inner annular mixing orifice and the outer annular mixing orifice are used to adjust the outlet temperature field; the cooling orifice is a fully divergent multi-oblique orifice, and the angle of the multi-oblique orifice is a composite angle with three-dimensional spatial angles; the airflow inlet includes the support plate air inlet, the annular vortex air inlet, the inner annular main combustion orifice, the inner annular mixing orifice, the outer annular mixing orifice, and the cooling orifice; and The fuel supply assembly includes a main combustion stage nozzle and a shift nozzle. The main combustion stage nozzle is mounted on the flame tube and communicates with the main combustion zone. The shift nozzle is mounted on the head of the flame tube and communicates with the annular vortex zone. A premixing and pre-evaporating tube is disposed between the main combustion stage nozzle and the flame tube. The premixing and pre-evaporating tube is provided with a mixing and evaporation channel for premixing and pre-evaporating the air-oil mist mixture. The outlet end of the premixing and pre-evaporating tube is provided with a converging nozzle for preventing backfire. The outlet end of the premixing and pre-evaporating tube is mounted on the flame tube through a swirling assembly. The swirling assembly includes an inner swirling head and an outer swirling head surrounding the inner swirling head. The inner swirling head is connected to the outlet end of the premixing and pre-evaporating tube.

2. The combustion chamber as described in claim 1, characterized in that, The swirling assembly also includes an inlet swirler, which is located at the inlet end of the main combustion stage nozzle and the premixed pre-evaporation tube.

3. The combustion chamber as described in claim 1, characterized in that, The fuel distribution ratio between the main combustion stage nozzle and the duty nozzle is 4:

1.

4. The combustion chamber as described in claim 2, characterized in that, The duty nozzle is a single-oil-path centrifugal nozzle or a dual-oil-path centrifugal nozzle. The duty nozzle is installed on the front wall of the concave cavity of the annular vortex flow head, and its spray direction is to spray towards the vicinity of the annular vortex swirl plate. The main combustion stage nozzle is a single-oil-path centrifugal nozzle or a dual-oil-path centrifugal nozzle, and the main combustion stage nozzle is inserted into the mixing and evaporation channel along the center line of the inlet cyclone separator.

5. The combustion chamber as described in claim 1, characterized in that, The combustion chamber also includes an igniter. The casing assembly is provided with an ignition nozzle hole. The igniter is installed in the ignition nozzle hole and extends into the annular vortex region. The ignition nozzle of the igniter is flush with the inner wall surface of the annular vortex flow head.

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