A compact combustion chamber

Abstract

A compact combustion chamber belongs to the fields of combustion and aerodynamic technologies of aeroengines and gas turbines. The invention solves the problems of large axial dimensions of the existing combustion chamber and turbine, uneven temperature distribution at the outlet of the combustion chamber, and high NOx emissions. The intake passage is communicated with the air distribution cavity. A main fuel distribution outer cavity, a pilot fuel distribution cavity, and a main fuel distribution inner cavity are sequentially separated along the radial direction of the combustion chamber between the cover plate assembly and the fuel pipe base. The front parts of a plurality of micro-mixing nozzles are inserted on the fuel pipe base, and the rear parts of the plurality of micro-mixing nozzles are correspondingly inserted in a plurality of air distribution holes. The fuel and the oxidant are premixed by internal cross-jet under micro-scale conditions, which can improve the premixing degree of the fuel and the oxidant, increase the average temperature and temperature ratio at the outlet of the combustion chamber, and thus reduce the NOx emissions. By controlling the fuel flow rate in different zones, the temperature distribution at the outlet of the combustion chamber can be controlled and adjusted according to the requirements of the thermal stress distribution of the turbine blades and the operating conditions.

Description

Technical Field

[0001] The present invention relates to a compact combustion chamber, belonging to the fields of combustion and aerodynamics of aero-engines and gas turbines. Background Art

[0002] Gas turbines are widely used in the fields of aviation, aerospace, ships, electric power, natural gas transportation, industrial drive, etc. With the continuous development of gas turbine technology, higher requirements are put forward for the structural compactness and combustion performance of gas turbines, especially for the requirements of gas temperature distribution, nitrogen oxide emissions and total pressure loss.

[0003] In a traditional combustion chamber, the gas generally flows along the axial direction of the engine to ensure its combustion efficiency; at the same time, it is required that the airflow entering the turbine moving blades has a large tangential angle to drive the turbine moving blades to do work; therefore, it is necessary to set turbine stator guide vanes at the outlet of the combustion chamber to rectify the high-temperature gas. This design results in an increase in the axial length of the combustion chamber and the turbine, increases the residence time of the high-temperature gas in the high-temperature area, and further leads to the inability to further reduce the nitrogen oxide emissions. If the combustion chamber intake method is simply changed to oblique intake, limited by the angle of the burner mounting plate, the nozzle flame is extremely easy to burn the adjacent nozzle mounting plate.

[0004] In addition, there are also problems in the design of traditional high-temperature-rise combustion chambers, such as uneven outlet temperature distribution and an increasingly reduced amount of cooling air for the turbine. Therefore, it is necessary to propose a new type of compact combustion chamber to solve the above problems. Summary of the Invention

[0005] The present invention is to solve the above technical problems, and further provides a compact combustion chamber.

[0006] The technical solution adopted by the present invention to solve the above technical problems is as follows:

[0007] A compact combustion chamber, which has an annular structure and includes a casing, a flame tube, an igniter, a cover plate assembly, a fuel pipe base, an air distribution plate and a plurality of micro-mixing nozzles. The casing is located outside the flame tube, and an intake passage is provided between the inner wall of the casing and the flame tube. A plurality of turbine first-stage moving blades are arranged at the outlet of the flame tube.

[0008] The cover plate assembly, the fuel pipe base and the air distribution plate are arranged in parallel from front to back.

[0009] An air distribution cavity is formed between the fuel pipe base and the air distribution plate, and the intake passage is communicated with the air distribution cavity.

[0010] A main fuel distribution outer cavity, a pilot fuel distribution cavity, and a main fuel distribution inner cavity are sequentially arranged in a separated manner along the radial direction of the combustion chamber between the cover plate assembly and the fuel pipe base. An outer cavity main fuel inlet, a pilot fuel inlet, and an inner cavity main fuel inlet are correspondingly formed in the cover plate assembly.

[0011] The igniter guns are sequentially inserted into the cover plate assembly, the fuel pipe base, and the air distribution plate.

[0012] A plurality of air distribution holes are formed in the air distribution plate. The front parts of a plurality of micro-mixing nozzles are all inserted into the fuel pipe base, and the rear parts of the plurality of micro-mixing nozzles are correspondingly inserted into the plurality of air distribution holes. A first annular gap exists between the micro-mixing nozzle and the inner wall of the air distribution hole. A plurality of fuel through holes are circumferentially formed in the rear part of each micro-mixing nozzle. The central axis of the air distribution hole is inclined, and the inclination direction is perpendicular to the blade of the first-stage turbine rotor blade.

[0013] Further, the micro-mixing nozzle includes a first pipe section and a second pipe section which are connected and fixed end to end. The central axis of the second pipe section is inclined with respect to the central axis of the first pipe section. The end of the first pipe section far from the second pipe section is the fuel inlet end, and the end of the second pipe section far from the first pipe section is a closed end. A plurality of fuel through holes are circumferentially formed in the rear part of the second pipe section.

[0014] Further, the included angle between the central axis of the first pipe section and the central axis of the second pipe section is 30° to 60°.

[0015] Further, the number of fuel through holes on each micro-mixing nozzle is 2 to 10.

[0016] Further, the cover plate assembly, the fuel pipe base, the air distribution plate, the flame tube, and the casing are all arranged in an annular structure. A plurality of micro-mixing nozzles are distributed in multiple groups of circumferential arrays centered on the center of the fuel pipe base, and the multiple groups of circumferential arrays are arranged at equal intervals.

[0017] Further, a plurality of nozzle mounting holes are formed in the fuel pipe base, and the plurality of nozzle mounting holes are arranged in one-to-one correspondence with the plurality of air distribution holes. The front parts of the plurality of micro-mixing nozzles are correspondingly inserted into the plurality of nozzle mounting holes.

[0018] Further, the casing includes an outer casing and an inner casing arranged coaxially. The flame tube includes a flame tube inner wall and a flame tube outer wall arranged coaxially. A second annular gap exists between the outer casing and the flame tube outer wall and between the inner casing and the flame tube inner wall, and the second annular gaps are both communicated with the air distribution cavity.

[0019] Further, the number of the outer cavity main fuel inlets, the pilot fuel inlets, and the inner cavity main fuel inlets is 2 to 6 and they are evenly distributed along the circumferential direction of the combustion chamber.

[0020] Furthermore, the number of igniters is multiple and they are circumferentially evenly distributed.

[0021] Furthermore, the inner diameter of the air distribution holes is 9 mm to 36 mm.

[0022] The present invention has the following effects compared with the prior art:

[0023] By obliquely arranging the central axis of the air distribution holes, the generated high-temperature gas swirls as a whole around the central axes of the combustion chamber and the turbine. On the basis of canceling the first-stage stationary guide vanes of the turbine, the high-temperature gas enters the turbine to do work in a direction perpendicular to the blades of the first-stage moving vanes of the turbine, shortening the axial dimensions of the combustion chamber and the turbine, reducing the residence time of the high-temperature gas in the high-temperature zone, and further reducing the generation amount of NOx.

[0024] The fuel and the oxidant are premixed by internal cross-jet under microscale conditions, which can improve the premixing degree of the fuel and the oxidant, further increase the average temperature and temperature ratio at the outlet of the combustion chamber, and thus reduce the NOx emission. At the same time, through the radial arrangement of the main fuel distribution outer cavity, the pilot fuel distribution cavity and the main fuel distribution inner cavity, the combustion chamber is radially divided into an outer main combustion zone, a pilot zone and an inner main combustion zone. By controlling the fuel flow rates in different zones, the temperature distribution at the outlet of the combustion chamber can be controlled and adjusted according to the requirements of the thermal stress distribution of the turbine blades and the operating conditions.

[0025] The structure of the present invention has a high degree of integration, flexible structure and reliable operation. Different combustion characteristics and operating condition requirements can be achieved through different arrangements of the micro-mixing nozzles, different combinations of the micro-mixing nozzle sizes, and different relationships of the micro-mixing nozzle spacings. At the same time, it has a wide operating range and strong fuel adaptability, and can achieve high-efficiency and low-emission combustion of various gaseous fuels.

[0026] The combustion chamber structure of the present invention cancels the cooling holes and mixing holes on the flame tube in the traditional combustion chamber structure. All the air entering the combustion chamber is put into the head to participate in the combustion organization process, enabling the temperature distribution at the outlet of the combustion chamber to be controllable and adjustable, and thus solving the problems of insufficient turbine cooling air volume and inability to further reduce the NOx emission. Brief Description of the Drawings

[0027] Figure 1 It is a first three-dimensional structure schematic diagram of one sector of the compact combustion chamber of the present invention;

[0028] Figure 2 It is a second three-dimensional structure schematic diagram of one sector of the compact combustion chamber of the present invention;

[0029] Figure 3 It is a sectional schematic diagram of one sector of the compact combustion chamber of the present invention;

[0030] Figure 4Partial cross-sectional view of a micro-hybrid nozzle, fuel pipe base, and air distribution plate;

[0031] Figure 5 Front view schematic of one sector of the fuel pipe base;

[0032] Figure 6 Three-dimensional structure schematic of one sector of the air distribution plate;

[0033] Figure 7 Three-dimensional structure schematic of the micro-hybrid nozzle;

[0034] Figure 8 Cross-sectional view schematic of the micro-hybrid nozzle.

[0035] In the figure:

[0036] 1. Casing; 1-1. Outer casing; 1-2. Inner casing; 2. Combustion chamber; 2-1. Inner wall of the combustion chamber; 2-2. Outer wall of the combustion chamber; 3. Ignition gun; 4. Cover plate assembly; 4-1. Main fuel inlet of the outer cavity; 4-2. Pilot fuel inlet; 4-3. Main fuel inlet of the inner cavity; 4-4. Main fuel outer cavity cover plate; 4-5. Pilot fuel cavity cover plate; 4-6. Outer wall of the pilot fuel cavity; 4-7. Inner wall of the pilot fuel cavity; 4-8. Main fuel inner cavity cover plate; 5. Fuel pipe base; 5-1. Nozzle mounting hole; 6. Air distribution plate; 6-1. Air distribution hole; 7. Micro-hybrid nozzle; 7-1. Fuel through hole; 7-2. First pipe section; 7-3. Second pipe section; 9. First-stage turbine blade; 10. Air distribution cavity; 11. Main fuel distribution outer cavity; 12. Pilot fuel distribution cavity; 13. Main fuel distribution inner cavity; 14. Fixed pipe. Specific implementation mode

[0037] Specific implementation mode one: Combining Figures 1 to 8 To describe the technical solutions in the embodiments of the present invention clearly and completely, it is obvious that the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present invention.

[0038] It should be noted that the descriptions of the present invention regarding directions such as "front", "rear", "left", "right", "inner", "outer", "left side", "right side", "upper part", "lower part", "top", "bottom", etc. are all defined based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the described structure must be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation to the present invention. In the description of the present invention, "a plurality" means more than two, unless otherwise specifically defined.

[0039] In the description of the present invention, unless otherwise clearly specified and defined, the terms "mounted", "connected", and "coupled" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be directly connected, or indirectly connected through an intermediate medium, and may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] A compact combustion chamber, which has an annular structure, includes a casing 1, a flame tube 2, an igniter 3, a cover plate assembly 4, a fuel pipe base 5, an air distribution plate 6, and a number of micro-mixing nozzles 7. The casing 1 is located outside the flame tube 2, and an intake passage is provided between the inner wall of the casing 1 and the flame tube 2. A number of first-stage turbine rotor blades 9 are arranged at the outlet of the flame tube 2.

[0041] The cover plate assembly 4, the fuel pipe base 5, and the air distribution plate 6 are arranged in parallel in sequence from front to back.

[0042] An air distribution cavity 10 is formed between the fuel pipe base 5 and the air distribution plate 6, and the intake passage is communicated with the air distribution cavity 10.

[0043] Between the cover plate assembly 4 and the fuel pipe base 5, a main fuel distribution outer cavity 11, a pilot fuel distribution cavity 12, and a main fuel distribution inner cavity 13 are sequentially separated along the radial direction of the combustion chamber. Corresponding to these, an outer cavity main fuel inlet 4-1, a pilot fuel inlet 4-2, and an inner cavity main fuel inlet 4-3 are opened on the cover plate assembly 4.

[0044] The igniter 3 is sequentially inserted into the cover plate assembly 4, the fuel pipe base 5, and the air distribution plate 6.

[0045] A number of air distribution holes 6-1 are opened on the air distribution plate 6. The front parts of a number of micro-mixing nozzles 7 are inserted into the fuel pipe base 5, and the rear parts of the number of micro-mixing nozzles 7 are correspondingly inserted into the number of air distribution holes 6-1. And there is a first annular gap between the micro-mixing nozzle 7 and the inner wall of the air distribution hole 6-1. A number of fuel through holes 7-1 are opened along the circumferential direction at the rear part of each micro-mixing nozzle 7.

[0046] The rear end of the casing 1 is designed to be open, and air enters the air distribution cavity 10 from the rear end of the casing 1 in a countercurrent form through the intake passage, and the flame tube wall is cooled in this process.

[0047] The main fuel distribution outer cavity 11, the pilot fuel distribution cavity 12, and the main fuel distribution inner cavity 13 are not communicated with each other.

[0048] The pilot fuel enters the pilot fuel distribution cavity 12 through the pilot fuel inlet 4-2.

[0049] The main external cavity fuel inlet 4-1, the pilot fuel inlet 4-2 and the main internal cavity fuel inlet 4-3 are respectively communicated with the main fuel distribution external cavity 11, the pilot fuel distribution cavity 12 and the main fuel distribution internal cavity 13.

[0050] Fuel enters the main fuel distribution external cavity 11 and the main fuel distribution internal cavity 13 through the main external cavity fuel inlet 4-1 and the main internal cavity fuel inlet 4-3 respectively, and then is sprayed into the air distribution hole 6-1 through a number of micro-mixing nozzles 7 and the fuel through holes 7-1 on the micro-mixing nozzles 7. After premixing with the countercurrent air from the air distribution cavity 10 in the air distribution hole 6-1 in an internal cross-jet mode, it enters the combustion chamber 2 for combustion to generate high-temperature gas, and the high-temperature gas directly drives the first-stage turbine rotor blade 9 to do work.

[0051] The internal cross-jet premixing of fuel and oxidant under micro-scale conditions can improve the premixing degree of fuel and oxidant, further increase the average temperature and temperature ratio at the outlet of the combustion chamber, and thus reduce the NOx emission. At the same time, through the radial arrangement of the main fuel distribution external cavity 11, the pilot fuel distribution cavity 12 and the main fuel distribution internal cavity 13, the combustion chamber is radially divided into an external main combustion zone, a pilot zone and an internal main combustion zone. By controlling the fuel flow rate in different zones, the temperature distribution at the outlet of the combustion chamber can be controlled and adjusted according to the thermal stress distribution requirements of the turbine blades and the operating conditions.

[0052] The structure of the present invention has a high degree of integration, flexible structure and reliable operation. Different combustion characteristics and operating condition requirements can be achieved through different arrangement relationships of the micro-mixing nozzles 7, different size combinations of the micro-mixing nozzles 7 and different spacing relationships of the micro-mixing nozzles 7. At the same time, it has a wide operating range and strong fuel adaptability, and can achieve high-efficiency and low-emission combustion of various gaseous fuels.

[0053] The combustion chamber structure of the present invention cancels the cooling holes and mixing holes on the combustion chamber liner 2 in the traditional combustion chamber structure. All the air entering the combustion chamber is put into the head to participate in the combustion organization process, so that the temperature distribution at the outlet of the combustion chamber can be controlled and adjusted, thus solving the problems of insufficient turbine cooling air volume and inability to further reduce the NOx emission.

[0054] The inner diameter of the air distribution hole 6-1 is 9 mm to 36 mm.

[0055] The cover plate assembly 4 includes a main fuel outer cavity cover plate 4-4, a pilot fuel cavity cover plate 4-5, a pilot fuel cavity outer wall 4-6, a pilot fuel cavity inner wall 4-7, and a main fuel inner cavity cover plate 4-8. The main fuel outer cavity cover plate 4-4, the pilot fuel cavity cover plate 4-5, and the main fuel inner cavity cover plate 4-8 are all annular plates and are spliced in sequence along the radial direction of the combustion chamber. The pilot fuel cavity outer wall 4-6 is fixedly sealed between the outer end of the pilot fuel cavity cover plate 4-5 and the main fuel outer cavity cover plate 4-4 to separate the main fuel outer cavity and the pilot fuel cavity into independent chambers. The pilot fuel cavity inner wall 4-7 is fixedly sealed between the inner end of the pilot fuel cavity cover plate 4-5 and the main fuel inner cavity cover plate 4-8 to separate the main fuel inner cavity and the pilot fuel cavity into independent chambers.

[0056] The igniter 3 is an electric igniter, which is fixed on the pilot fuel cavity cover plate 4-5 through a fixed pipe 14, passes through the fuel pipe base 5 and the air distribution plate 6, and its end is located in the flame tube 2.

[0057] The shapes of the flame tube 2 and the casing 1 are determined according to the flow streamlines of air and gas, the resistance loss, the flow rate distribution, and the velocity field distribution.

[0058] The planar air distribution plate effectively avoids the problem of burning adjacent nozzles due to the inclined arrangement of the micro-mixing nozzles 7.

[0059] The central axis of the air distribution hole 6-1 is inclined, and its inclined direction is perpendicular to the blades of the first-stage turbine moving blade 9. Designed in this way, the fuel is sprayed from the fuel through-hole 7-1 on the micro-mixing nozzle 7 into the air distribution hole 6-1 with a circumferential tangential angle, so that the generated high-temperature gas is a rotating gas flow with a certain tangential velocity. The gas swirl angle at the outlet of the flame tube 2 of the high-temperature gas matches the first-stage turbine moving blade 9, and the high-temperature gas directly impacts the pressure surface of the first-stage turbine moving blade 9 to do external work. Therefore, the first-stage turbine stator blade in the traditional gas turbine can be discarded. While ensuring the efficient conversion between the gas thermal energy and kinetic energy and the mechanical energy of the first-stage turbine moving blade 9, the first-stage turbine stator guide vane is cancelled to shorten the axial length of the combustion chamber, the turbine, and the overall gas turbine. Such a design can reduce the self-weight of the gas turbine, reduce the total pressure loss and the consumption of turbine cooling air, and at the same time, it can also reduce the residence time of the gas in the high-temperature area, thereby achieving a significant reduction in NOx emissions and effectively improving the efficiency of the gas turbine.

[0060] The micro-mixing nozzle 7 includes a first pipe section 7-2 and a second pipe section 7-3 that are fixedly connected with their heads and tails communicating. The central axis of the second pipe section 7-3 is inclined to the central axis of the first pipe section 7-2. One end of the first pipe section 7-2 away from the second pipe section 7-3 is the fuel inlet end, and one end of the second pipe section 7-3 away from the first pipe section 7-2 is the closed end. A number of fuel through-holes 7-1 are circumferentially formed in the rear part of the second pipe section 7-3. With such a design, the second pipe section 7-3 is inserted into the air distribution hole 6-1, and fuel enters through one end of the first pipe section 7-2 and is ejected through the fuel through-holes 7-1 on the second pipe section 7-3. The wall thicknesses of both the first pipe section 7-2 and the second pipe section 7-3 are 1 mm to 3 mm, the inner diameter of the first pipe section 7-2 is 3 mm to 12 mm, the diameter of the fuel through-hole 7-1 is 0.5 mm to 2 mm, the vertical distance between the plane where the central axes of a number of fuel through-holes 7-1 are located and the inlet end of the air distribution hole 6-1 is 10 mm to 50 mm, and the vertical distance between the plane where the central axes of a number of fuel through-holes 7-1 are located and the outlet end of the air distribution hole 6-1 is 3 mm to 15 mm.

[0061] The included angle between the central axis of the first pipe section 7-2 and the central axis of the second pipe section 7-3 is 30 to 60°.

[0062] The number of fuel through-holes 7-1 on each micro-mixing nozzle 7 is 2 to 10.

[0063] The cover plate assembly 4, the fuel pipe base 5, the air distribution plate 6, the flame tube 2, and the casing 1 are all arranged in an annular structure. A number of micro-mixing nozzles 7 are distributed in multiple groups of circumferential arrays centered on the center of the fuel pipe base 5, and the multiple groups of circumferential arrays are arranged at equal intervals. With such a design, the stable combustion range of the combustion chamber can be expanded, the combustion stability of the combustion chamber can be enhanced. Especially during the ignition process of the combustion chamber, the ignition stability can be improved, the flame linking and propagation time can be shortened, and the problem of deflagration caused by too high local fuel concentration in the combustion chamber can be prevented.

[0064] A number of nozzle mounting holes 5-1 are formed on the fuel pipe base 5, and a number of nozzle mounting holes 5-1 are arranged in one-to-one correspondence with a number of air distribution holes 6-1. The front parts of a number of micro-mixing nozzles 7 are inserted into a number of nozzle mounting holes 5-1 in one-to-one correspondence. With such a design, the installation and fixation of the micro-mixing nozzle 7 are realized by forming the nozzle mounting holes 5-1.

[0065] The casing 1 includes an outer casing 1-1 and an inner casing 1-2 arranged coaxially. The flame tube 2 includes a flame tube inner wall 2-1 and a flame tube outer wall 2-2 arranged coaxially. There are second annular gaps between the outer casing 1-1 and the flame tube outer wall 2-2 and between the inner casing 1-2 and the flame tube inner wall 2-1, and the second annular gaps are both communicated with the air distribution cavity 10. Designed in this way, the second annular gaps between the outer casing 1-1 and the flame tube outer wall 2-2 and between the inner casing 1-2 and the flame tube inner wall 2-1 are the air intake channels. The inner and outer edges of the fuel pipe base 5 are respectively provided with a plurality of positioning threaded holes, and the fuel pipe base 5 is fixed on the outer casing 1-1 and the inner casing 1-2 by screws. The main fuel outer cavity cover plate 4-4 is connected to the outer casing 1-1, and the main fuel inner cavity cover plate 4-8 is connected to the inner casing 1-2.

[0066] The numbers of the outer cavity main fuel inlet 4-1, the pilot fuel inlet 4-2, and the inner cavity main fuel inlet 4-3 are all 2 to 6 and are evenly distributed along the circumferential direction of the combustion chamber. Designed in this way, the uniformity of fuel distribution along the circumferential direction of the combustion chamber is effectively improved.

[0067] The number of the igniters 3 is multiple and they are evenly distributed along the circumferential direction. Designed in this way, the ignition stability of the combustion chamber is effectively improved, multiple stable ignition flames are established along the circumferential direction of the combustion chamber, and it is beneficial for the ignition flames to spread around, so that the fuel in the entire combustion chamber burns stably.

[0068] Specific Embodiment 2: Combining Figures 1 to 8 This embodiment is described. There are three pilot fuel inlets evenly distributed along the circumferential direction on the pilot fuel cavity cover plate, three outer cavity main fuel inlets evenly distributed along the circumferential direction on the main fuel outer cavity cover plate, and three inner cavity main fuel inlets evenly distributed along the circumferential direction on the main fuel inner cavity cover plate;

[0069] The included angle between the central axis of the first pipe section and the central axis of the second pipe section is 45°. The wall thicknesses of the first pipe section and the second pipe section are both 1 mm. The number of fuel through holes on each micro-mixing nozzle is 6;

[0070] The inner diameter of the first pipe section is 4 mm, the diameter of the fuel through hole is 0.6 mm. The vertical distance between the plane where the central axes of several fuel through holes are located and the inlet end of the air distribution hole is 40 mm, the vertical distance between the plane where the central axes of several fuel through holes are located and the outlet end of the air distribution hole is 10 mm, and the inner diameter of the air distribution hole is 10 mm. Other compositions and connection relationships are the same as those in Specific Embodiment 1.

[0071] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, makes equivalent substitutions or changes, and should be covered by the protection scope of the present invention.

Claims

1. A compact combustion chamber, characterized in that: It has an annular structure, including a casing (1), a combustion liner (2), an igniter (3), a cover plate assembly (4), a fuel pipe base (5), an air distribution plate (6) and a number of micro-mixing nozzles (7). The casing (1) is located outside the combustion liner (2), and an air intake passage is provided between the inner wall of the casing (1) and the combustion liner (2). A number of first-stage turbine moving blades (9) are arranged at the outlet of the combustion liner (2). The cover plate assembly (4), the fuel pipe base (5) and the air distribution plate (6) are arranged in parallel in sequence from front to back. An air distribution cavity (10) is formed between the fuel pipe base (5) and the air distribution plate (6), and the air intake passage is communicated with the air distribution cavity (10). A main fuel distribution outer cavity (11), a pilot fuel distribution cavity (12) and a main fuel distribution inner cavity (13) are sequentially separated along the radial direction of the combustion chamber between the cover plate assembly (4) and the fuel pipe base (5). An outer cavity main fuel inlet (4-1), a pilot fuel inlet (4-2) and an inner cavity main fuel inlet (4-3) are correspondingly provided on the cover plate assembly (4). The igniter (3) is sequentially inserted on the cover plate assembly (4), the fuel pipe base (5) and the air distribution plate (6). A number of air distribution holes (6-1) are provided on the air distribution plate (6). The front parts of a number of micro-mixing nozzles (7) are all inserted on the fuel pipe base (5), and the rear parts of the number of micro-mixing nozzles (7) are correspondingly inserted in the number of air distribution holes (6-1). And there is a first annular gap between the micro-mixing nozzle (7) and the inner wall of the air distribution hole (6-1). A number of fuel through holes (7-1) are circumferentially provided on the rear part of each micro-mixing nozzle (7). The central axis of the air distribution hole (6-1) is inclined, and its inclination direction is perpendicular to the blade of the first-stage turbine moving blade (9).

2. The compact combustion chamber according to claim 1, characterized in that: The micro-mixing nozzle (7) includes a first pipe section (7-2) and a second pipe section (7-3) which are connected and fixed at the head and the tail. The central axis of the second pipe section (7-3) is inclined to the central axis of the first pipe section (7-2). The end of the first pipe section (7-2) far from the second pipe section (7-3) is the fuel inlet end, and the end of the second pipe section (7-3) far from the first pipe section (7-2) is the closed end. A number of fuel through holes (7-1) are circumferentially provided on the rear part of the second pipe section (7-3).

3. The compact combustion chamber according to claim 2, characterized in that: The included angle between the central axis of the first pipe section (7-2) and the central axis of the second pipe section (7-3) is 30 to 60°.

4. The compact combustion chamber according to claim 1, 2 or 3, characterized in that: The number of fuel through holes (7-1) on each micro-mixing nozzle (7) is 2 to 10.

5. The compact combustion chamber according to claim 1, characterized in that: The cover plate assembly (4), the fuel pipe base (5), the air distribution plate (6), the combustion liner (2) and the casing (1) are all arranged in an annular structure. A number of micro-mixing nozzles (7) are distributed in multiple groups of circumferential arrays centered on the center of the fuel pipe base (5), and the multiple groups of circumferential arrays are arranged at equal intervals.

6. The compact combustion chamber according to claim 1, characterized in that: A plurality of nozzle mounting holes (5-1) are formed in the fuel pipe base (5), and the plurality of nozzle mounting holes (5-1) are arranged in one-to-one correspondence with the plurality of air distribution holes (6-1). The front parts of the plurality of micro-mixing nozzles (7) are inserted into the plurality of nozzle mounting holes (5-1) in one-to-one correspondence.

7. The compact combustion chamber according to claim 1, characterized in that: The casing (1) includes an outer casing (1-1) and an inner casing (1-2) arranged coaxially. The combustion liner (2) includes a combustion liner inner wall (2-1) and a combustion liner outer wall (2-2) arranged coaxially. A second annular gap exists between the outer casing (1-1) and the combustion liner outer wall (2-2) and between the inner casing (1-2) and the combustion liner inner wall (2-1), and the second annular gaps are both communicated with the air distribution cavity (10).

8. The compact combustion chamber according to claim 1, characterized in that: The numbers of the outer cavity main fuel inlets (4-1), the pilot fuel inlets (4-2), and the inner cavity main fuel inlets (4-3) are all 2 to 6 and are evenly distributed along the circumference of the combustion chamber.

9. The compact combustion chamber according to claim 1, characterized in that: The number of the igniters (3) is multiple and they are evenly distributed along the circumference.

10. The compact combustion chamber according to claim 1, characterized in that: The inner diameter of the air distribution hole (6-1) is 9 mm to 36 mm.

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