Integrally-designed oxygen-enriched turbine engine injector

Abstract

The invention relates to the technical field of turbine engines, in particular to an integrally-designed oxygen-enriched turbine engine injector which comprises an injection head center dovetail structure integrally formed on the inner side of an injector body and an igniter base fixed to one side of the outer wall of the injector body. A first mounting flange and a second mounting flange are fixed to the outer side edges of the upper end and the lower end of the injector body respectively, an oxygen-enriched gas flow channel is formed in the middle of the inner side of the injector body, and a high-pressure air flow channel formed in the injector body is formed in the outer side of the oxygen-enriched gas flow channel. Fuel injection atomization and efficient mixing of fuel gas are effectively achieved, the combustion speed and efficiency are remarkably improved, the injector body is integrally designed based on the 3D printing technology, machining, welding and assembling are not needed, the situations that an existing injector is large in welding deformation and high-temperature and high-pressure sealing is difficult to design are avoided, and the fuel injection efficiency is greatly improved. And the overall reliability of the injector is improved, and the service life of the injector main body is prolonged.

Description

Technical Field

[0001] The invention relates to the technical field of turbine engines, and in particular to an oxygen-rich turbine engine injector with an integrated design. Background Art

[0002] The function of the oxygen-enriched turbine engine injector is to achieve high-quality fuel atomization, efficient mixing of fuel and oxidant gas in a wide range of operating conditions, and inject them into the combustion chamber for combustion. For oxygen-enriched turbine engines, the oxidant consists of two parts, namely: high-pressure air captured from the atmosphere and pressurized by the compressor, and oxygen-enriched gas after the high-temperature oxygen-enriched gas generator works as a turbine. Existing injectors have high integration and complex flow channel structures. Injectors designed based on traditional machining, welding, and assembly process routes cannot avoid problems such as large welding deformation, difficult design of high-temperature and high-pressure seals, and accumulated machining and assembly errors during actual use, resulting in low overall reliability of the injector. The efficiency is not high in the process of mixing high-pressure air, oxygen-enriched gas, and fuel, which has a certain impact on the performance of the engine. Summary of the invention

[0003] In order to overcome the deficiencies of the prior art, the present invention provides an oxygen-rich turbine engine injector with an integrated design, which solves the problems of large welding deformation, difficult design of high-temperature and high-pressure seals, and accumulated machining and assembly errors of existing engine injectors.

[0004] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0005] An oxygen-enriched turbine engine injector of integrated design, comprising an injector head central dovetail structure integrally formed on the inner side of an injector body and an igniter seat fixed to one side of the outer wall of the injector body, the outer edges of the upper and lower ends of the injector body are respectively fixed with mounting flanges 1 and 2, an oxygen-enriched fuel gas flow channel is arranged in the middle of the inner side of the injector body, a high-pressure air flow channel opened in the injector body is arranged on the outer side of the oxygen-enriched fuel gas flow channel, and the oxygen-enriched fuel gas flow channel and the outlet of one end of the high-pressure air flow channel intersect at an angle of 30-45°;

[0006] Among them, a radial support beam for supporting the central dovetail structure of the injector head, the oxygen-rich fuel gas flow channel and the high-pressure air flow channel is fixed through the injector body, a fuel flow channel is integrally formed inside the radial support beam, a circumferentially connected air film ring cavity is provided on the outside of the high-pressure air flow channel, and the igniter seat passes through one side of the air film ring cavity.

[0007] As a further optimization scheme of the present invention, a conical cavity for thermal protection of the injection head is provided at the bottom of the central dovetail structure of the injection head, and the top cone angle of the conical cavity is not greater than 100°, and a blunt head is provided at the top of the central dovetail structure of the injection head. A plurality of through holes arranged at intervals are also provided at the bottom of the central dovetail structure of the injection head, and the through holes respectively penetrate the inner wall surface and the outer wall surface of the central dovetail structure of the injection head.

[0008] As a further optimization scheme of the present invention, the oxygen-rich gas flow channel includes an oxygen-rich gas inlet arranged at the top of the inner side of the injector body, and an oxygen-rich gas annular gap outlet arranged at the bottom of the inner side of the injector body, and the top of the oxygen-rich gas annular gap outlet is provided with an annular flow channel located between the central dovetail structure of the injection head and the inner wall of the injector body, and the cross-section of the annular flow channel gradually decreases toward the oxygen-rich gas annular gap outlet.

[0009] As a further optimization scheme of the present invention, the high-pressure air flow channel includes a high-pressure air inlet arranged on one side of the injector body, and a high-pressure air annular seam outlet arranged on the outside of the bottom of the injector body. The bottom of the high-pressure air inlet is connected to a high-pressure air confluence chamber, and one side of the high-pressure air confluence chamber is provided with an annular distribution orifice plate integrally formed in the injector body, and a high-pressure air outer flow channel is provided on the inner side of the bottom of the high-pressure air flow channel.

[0010] As a further optimization scheme of the present invention, a plurality of spaced-apart connecting holes are provided on the annular distribution orifice plate, and the connecting holes are used to connect the high-pressure air flow channel and the high-pressure air confluence chamber, and the annular cross-section on the inner side of the bottom of the high-pressure air flow channel gradually shrinks toward the high-pressure air annular gap outlet.

[0011] As a further optimization scheme of the present invention, the high-pressure air outer flow channel is provided with a plurality of air holes distributed in a circumferential array and connected to the air film ring cavity, and an air film hole connected to the air film ring cavity is provided on one side of the bottom of the injector body.

[0012] As a further optimization scheme of the present invention, the fuel flow channel includes a fuel inlet arranged on one side of the outside of the injector body, and a fuel confluence cavity arranged on the outside of the radial support beam and opened in the injector body. The fuel confluence cavity is connected to the fuel flow channel and is an annular cavity.

[0013] As a further optimization scheme of the present invention, the bottom of the fuel confluence cavity is connected to a plurality of fuel pipelines distributed in a circular array, the vertical cross-section of the fuel pipeline is set to be L-shaped, the bottoms of the plurality of fuel pipelines are respectively connected to fuel spray holes, and the bottom outlets of the plurality of fuel spray holes are respectively connected to the annular flow channel and the high-pressure air outer flow channel.

[0014] By means of the above technical solution, the present invention provides an oxygen-enriched turbine engine injector with an integrated design, which has at least the following beneficial effects compared with the prior art:

[0015] 1. The present invention arranges an oxygen-rich gas flow channel, a high-pressure air flow channel and a fuel flow channel on the inner side of the injector body. The oxygen-rich gas flow channel sprays out oxygen-rich gas at a high speed, and the high-pressure air flow channel sprays out high-pressure air at a high speed. The fuel is sprayed uniformly through the fuel flow channel, thereby effectively realizing fuel injection atomization and efficient mixing of gas, and significantly improving the speed and efficiency of combustion. The injector body is integratedly designed based on the 3D printing process, and does not require machining, welding and assembly. This not only avoids the large welding deformation and difficult design of high-temperature and high-pressure seals of existing injectors, but also improves the overall reliability of the injector.

[0016] 2. The present invention provides an igniter seat on the injector body so that the igniter can be installed on the injector body for easy use. At the same time, the fuel pipeline can cool the annular flow channel in the oxygen-rich fuel gas flow channel. High-pressure air enters the air film ring cavity 9 through the air hole 11 and is ejected from the air film hole 12 at the bottom of the injector body. It can also form an air film cooling protection for the high-pressure air flow channel, which helps to extend the service life of the injector body. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0018] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0019] In the figure: 1, injector body; 2, dovetail structure in the center of the injector head; 21, conical cavity; 22, through hole; 23, blunt head;

[0020] 3. Ignition seat; 4. Mounting flange 1; 5. Mounting flange 2;

[0021] 6. Oxygen-enriched fuel gas flow channel; 61. Oxygen-enriched fuel gas inlet; 62. Oxygen-enriched fuel gas annular gap outlet; 63. Annular flow channel;

[0022] 7. High-pressure air flow channel; 71. High-pressure air inlet; 72. High-pressure air annular gap outlet; 73. High-pressure air confluence chamber; 74. Annular distribution orifice plate; 75. Connecting hole; 76. High-pressure air outflow channel;

[0023] 8. fuel flow channel; 81. fuel inlet; 82. fuel confluence chamber; 83. fuel pipeline; 84. fuel injection hole;

[0024] 9. Air film ring cavity; 10. Radial support beam; 11. Air hole; 12. Air film hole. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0026] First embodiment

[0027] The oxygen-enriched turbine engine injector is a key component that provides efficient combustion for turbine engines. It achieves efficient combustion by injecting a mixture of high-concentration air or oxygen and fuel. It is usually used in aerospace and some high-performance power systems. Due to the problems of large welding deformation, difficult design of high-temperature and high-pressure seals, and machining and assembly errors in traditional machined, welded, and assembled injectors, the overall reliability of the injector is low. In order to avoid the large welding deformation and difficult design of high-temperature and high-pressure seals of existing injectors, the injector is designed based on an integrated 3D printing process, without machining, welding, and assembly. Figure 1 The present embodiment provides an oxygen-rich turbine engine injector with an integrated design, which consists of an injector body 1, an injector head central dovetail structure 2 and an igniter seat 3. The injector head central dovetail structure 2 is integrally formed on the inner side of the injector body 1, and the igniter seat 3 is fixed on one side of the outer wall of the injector body 1.

[0028] The outer edges of the upper and lower ends of the injector body 1 are respectively fixed with mounting flange 1 4 and mounting flange 2 5. The injector body 1 can be stably installed in the intake system of the engine combustion chamber through mounting flange 1 4 and mounting flange 2 5 to facilitate the installation of the injector.

[0029] In order to achieve fuel injection atomization and efficient mixing of fuel gas, and significantly improve the speed and efficiency of combustion, an oxygen-rich fuel gas flow channel 6 is provided in the middle inner side of the injector body 1, and a high-pressure air flow channel 7 is provided on the outer side of the oxygen-rich fuel gas flow channel 6. The oxygen-rich fuel gas flow channel 6 and the high-pressure air flow channel 7 meet at an angle of 30-45° at one end of the outlet. A radial support beam 10 for supporting the central dovetail structure 2 of the injector head, the oxygen-rich fuel gas flow channel 6 and the high-pressure air flow channel 7 is fixed through the injector body 1. The cross-sectional shape of the radial support beam 10 is streamlined, which can reduce the resistance of the support beam to the oxygen-rich fuel gas airflow and help self-support during 3D printing. The radial support beam 10 can be one or multiple beams that equally divide the circumference. A fuel flow channel 8 is integrally formed inside the radial support beam 10, and a circumferentially connected air film ring cavity 9 is provided on the outer side of the high-pressure air flow channel 7, and the igniter seat 3 passes through one side of the air film ring cavity 9.

[0030] Among them, a conical cavity 21 for thermal protection of the injection head is arranged at the bottom of the central dovetail structure 2 of the injection head, and the top cone angle of the conical cavity 21 is not greater than 100°, which can provide thermal protection for the injection head. A blunt head 23 is arranged at the top of the central dovetail structure 2 of the injection head, and a plurality of through holes 22 are arranged at intervals at the bottom of the central dovetail structure 2 of the injection head. The through holes 22 respectively penetrate the inner wall surface and the outer wall surface of the central dovetail structure 2 of the injection head. The oxygen-rich gas passes through the through holes 22 due to the pressure difference between the oxygen-rich gas flow channel 6 and the conical cavity 21, thereby forming an air film protection for the conical cavity 21 inside the central dovetail structure 2 of the injection head.

[0031] The oxygen-rich gas flow channel 6 includes an oxygen-rich gas inlet 61 arranged at the top of the inner side of the injector body 1, and an oxygen-rich gas annular gap outlet 62 arranged at the bottom of the inner side of the injector body 1. The top of the oxygen-rich gas annular gap outlet 62 is provided with an annular flow channel 63 located between the central dovetail structure 2 of the injector head and the inner wall of the injector body 1, and the cross-section of the annular flow channel 63 gradually decreases toward the oxygen-rich gas annular gap outlet 62.

[0032] The oxygen-rich gas enters the oxygen-rich gas flow channel 6 from the oxygen-rich gas inlet 61 , is evenly distributed to the surroundings through the upstream blunt head 23 of the central dovetail structure 2 of the injection head, is gradually accelerated through the annular flow channel 63 , and is ejected at high speed from the oxygen-rich gas annular gap outlet 62 .

[0033] Second embodiment

[0034] In order to spray high-pressure air at high speed and mix it with oxygen-rich gas efficiently, refer to Figure 1The specific implementation method is that the high-pressure air flow channel 7 includes a high-pressure air inlet 71 arranged on one side of the injector body 1, and a high-pressure air annular gap outlet 72 arranged on the outer side of the bottom of the injector body 1. The bottom of the high-pressure air inlet 71 is connected to a high-pressure air confluence chamber 73, and one side of the high-pressure air confluence chamber 73 is provided with an annular distribution orifice plate 74 integrally formed in the injector body 1, and a plurality of spaced connection holes 75 are provided on the annular distribution orifice plate 74, and the connection holes 75 are used to connect the high-pressure air flow channel 7 and the high-pressure air confluence chamber. 73, and the annular cross-section of the inner side of the bottom of the high-pressure air flow channel 7 gradually shrinks toward the high-pressure air annular gap outlet 72, so that the high-pressure air flows through the connecting hole 75 and enters the annular high-pressure air flow channel 7 with a gradually shrinking cross-section in a circumferentially uniform manner, and is finally ejected at a high speed from the high-pressure air annular gap outlet 72. A high-pressure air outer flow channel 76 is provided on the inner side of the bottom of the high-pressure air flow channel 7. The cross-section of the connecting hole 75 on the annular distribution orifice plate 74 is circular, diamond-shaped or raindrop-shaped, and the axis of the connecting hole 75 can be along the normal direction of the annular distribution orifice plate 74, or at a certain angle to the annular distribution orifice plate 74.

[0035] The high-pressure air outer flow channel 76 is provided with a plurality of air holes 11 distributed in a circumferential array and connected to the air film ring cavity 9. An air film hole 12 connected to the air film ring cavity 9 is provided on one side of the bottom of the injector body 1. The high-pressure air enters the air film ring cavity 9 through the air hole 11 and is ejected from the air film hole 12 at the bottom of the injector body 1, forming an air film cooling protection for the high-pressure air outer flow channel 76, which helps to extend the service life of the injector body 1.

[0036] Third embodiment

[0037] In order to spray the fuel evenly and mix it with high pressure air and oxygen-rich gas efficiently, refer to Figure 1 The specific implementation method is that the fuel flow channel 8 includes a fuel inlet 81 arranged on one side of the outside of the injector body 1, the cross-section of the fuel flow channel 8 is circular or raindrop-shaped, and a fuel confluence cavity 82 arranged on the outside of the radial support beam 10 and opened in the injector body 1, the fuel confluence cavity 82 is connected to the fuel flow channel 8 and is an annular cavity, the cross-section of the fuel confluence cavity 82 can be rectangular, raindrop-shaped or circular, the bottom of the fuel confluence cavity 82 is connected to a plurality of fuel pipelines 83 distributed in a circumferential array, the vertical cross-section of the fuel pipeline 83 is set to be L-shaped, the bottoms of the plurality of fuel pipelines 83 are respectively connected to fuel spray holes 84, the cross-section of the fuel spray holes 84 is raindrop-shaped or circular, and the bottom outlets of the plurality of fuel spray holes 84 are respectively connected to the annular flow channel 63 and the high-pressure air outer flow channel 76, and the fuel pipeline 83 not only transports the fuel from the fuel confluence cavity 82 to the fuel spray holes 84, but also cools the annular flow channel 63 in the oxygen-rich fuel gas flow channel 6.

[0038] The fuel enters the fuel flow channel 8 from the fuel inlet 81 , flows through the fuel confluence cavity 82 and the fuel pipeline 83 , and is then sprayed out from the horizontal fuel spray hole 84 .

[0039] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0040] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An oxygen-enriched turbine engine injector of an integrated design, comprising an injector head central dovetail structure (2) integrally formed on the inner side of an injector body (1) and an igniter seat (3) fixed to one side of the outer wall of the injector body (1), characterized in that: An oxygen-enriched fuel gas flow channel (6) is provided in the middle of the inner side of the injector body (1), and a high-pressure air flow channel (7) is provided outside the oxygen-enriched fuel gas flow channel (6) and is opened in the injector body (1). The outlets of one end of the oxygen-enriched fuel gas flow channel (6) and the high-pressure air flow channel (7) intersect at an angle of 30-45 degrees. A radial support beam (10) for supporting the central dovetail structure (2) of the injection head, the oxygen-enriched fuel gas flow channel (6) and the high-pressure air flow channel (7) is fixedly penetrated on the injector body (1), a fuel flow channel (8) is integrally formed inside the radial support beam (10), a circumferentially connected air film ring cavity (9) is arranged on the outer side of the high-pressure air flow channel (7), and the igniter seat (3) penetrates one side of the air film ring cavity (9).

2. The oxygen-enriched turbine engine injector of an integrated design according to claim 1, characterized in that: The bottom of the central dovetail structure (2) of the injection head is provided with a conical cavity (21) for thermal protection of the injection head, and the top cone angle of the conical cavity (21) is not greater than 100 degrees. The top of the central dovetail structure (2) of the injection head is provided with a blunt head (23). The bottom of the central dovetail structure (2) of the injection head is also provided with a plurality of through holes (22) arranged at intervals, and the through holes (22) respectively penetrate the inner wall surface and the outer wall surface of the central dovetail structure (2) of the injection head.

3. The oxygen-enriched turbine engine injector of an integrated design according to claim 1, characterized in that: The oxygen-enriched fuel gas flow channel (6) comprises an oxygen-enriched fuel gas inlet (61) arranged at the top of the inner side of the injector body (1), and an oxygen-enriched fuel gas annular gap outlet (62) arranged at the bottom of the inner side of the injector body (1), and an annular flow channel (63) located between the central dovetail structure (2) of the injector head and the inner wall of the injector body (1) is arranged at the top of the oxygen-enriched fuel gas annular gap outlet (62), and the cross section of the annular flow channel (63) gradually decreases towards the oxygen-enriched fuel gas annular gap outlet (62).

4. The oxygen-enriched turbine engine injector of an integrated design according to claim 3 is characterized in that: The high-pressure air flow channel (7) comprises a high-pressure air inlet (71) arranged on one side of the injector body (1), and a high-pressure air annular gap outlet (72) arranged on the outer side of the bottom of the injector body (1); the bottom of the high-pressure air inlet (71) is connected to a high-pressure air confluence chamber (73); one side of the high-pressure air confluence chamber (73) is provided with an annular distribution orifice plate (74) integrally formed in the injector body (1); and a high-pressure air outer flow channel (76) is provided on the inner side of the bottom of the high-pressure air flow channel (7).

5. The oxygen-enriched turbine engine injector of an integrated design according to claim 4 is characterized in that: The annular distribution orifice plate (74) is provided with a plurality of connection holes (75) spaced apart from each other, and the connection holes (75) are used to connect the high-pressure air flow channel (7) and the high-pressure air confluence chamber (73), and the annular cross-section of the inner side of the bottom of the high-pressure air flow channel (7) gradually shrinks toward the high-pressure air annular gap outlet (72).

6. The oxygen-enriched turbine engine injector of an integrated design according to claim 4, characterized in that: The high-pressure air outer flow channel (76) is provided with a plurality of air holes (11) distributed in a circumferential array and connected to the air film ring cavity (9), and an air film hole (12) connected to the air film ring cavity (9) is provided on one side of the bottom of the injector body (1).

7. The oxygen-enriched turbine engine injector of an integrated design according to claim 4, characterized in that: The fuel flow channel (8) comprises a fuel inlet (81) arranged on one side of the outside of the injector body (1), and a fuel confluence cavity (82) arranged on the outside of the radial support beam (10) and opened in the injector body (1); the fuel confluence cavity (82) is connected to the fuel flow channel (8) and is an annular cavity.

8. The oxygen-enriched turbine engine injector of an integrated design according to claim 7 is characterized in that: The bottom of the fuel confluence cavity (82) is connected to a plurality of fuel pipelines (83) distributed in a circumferential array, the vertical cross-section of the fuel pipeline (83) is arranged in an L-shape, the bottoms of the plurality of fuel pipelines (83) are respectively connected to fuel injection holes (84), and the bottom outlets of the plurality of fuel injection holes (84) are respectively connected to the annular flow channel (63) and the high-pressure air outer flow channel (76).

9. The oxygen-enriched turbine engine injector of an integrated design according to claim 1, characterized in that: The outer edges of the upper and lower ends of the injector body (1) are respectively fixed with a mounting flange 1 (4) and a mounting flange 2 (5).

Images