Fuel tube assembly, oil collector ring, fuel nozzle, combustion chamber and gas turbine engine

Abstract

The application provides a fuel pipe group, an oil collecting ring, a fuel nozzle, a combustion chamber and a gas turbine engine. The fuel pipe group is installed in the oil collecting ring. The fuel pipe group comprises a body. The body comprises a main fuel stage oil path, a first auxiliary oil path and a second auxiliary oil path. The main fuel stage oil path is adjacent to the first auxiliary oil path and the second auxiliary oil path and is arranged at an angle with respect to each other to form a heat exchange area. At least two heat insulation cavities are further included. The heat insulation cavities are arranged outside the heat exchange area. The heat insulation cavities arranged outside the heat exchange area formed by the main fuel stage oil path, the first auxiliary oil path and the second auxiliary oil path can block the heat transferred from the installation end of the fuel pipe group and the inner ring plate. The oil path temperature is effectively reduced, and the risk of fuel coking is reduced.

Description

Technical Field

[0001] This invention relates to the field of gas turbine engine technology, specifically to a fuel line assembly, a fuel collecting ring, a fuel nozzle, a combustion chamber, and a gas turbine engine. Background Technology

[0002] In an aircraft engine, the fuel nozzle is primarily affected by convective heat transfer from the high-pressure compressor outlet air and radiative heat transfer from the combustion gases within the burner tube. As the combustion chamber inlet temperature increases, the fuel line wall temperature and the fuel temperature also rise. The higher fuel-wet-wall temperature causes the fuel to react with dissolved oxygen, depositing and coking on the fuel line walls. This reduces the flow area of ​​the fuel lines and, in severe cases, can even clog the nozzle, affecting fuel atomization.

[0003] The increasingly poor fuel atomization effect will lead to the deterioration of combustion efficiency, emissions, and outlet temperature distribution in the combustion chamber, resulting in increased engine fuel consumption, decreased power performance, and difficulty in guaranteeing the working life of turbine blades, posing a serious threat to flight safety.

[0004] Based on this, the inventors of this application believe it is necessary to take thermal protection measures for the nozzle to reduce the heating effect of external heat sources on the fuel, thereby avoiding coking. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to overcome the defect in the prior art that the oil collecting ring is in direct contact with the hot air from the high-pressure compressor outlet, which will generate strong convective heat transfer on the outer metal wall of the oil passage, resulting in a high risk of fuel coking inside the oil collecting ring. The present invention provides a fuel pipe assembly, an oil collecting ring, a fuel nozzle, a combustion chamber, and a gas turbine engine.

[0006] The present invention solves the above-mentioned technical problems through the following technical solution:

[0007] This invention provides a fuel line assembly installed within a fuel collection ring, characterized in that it includes:

[0008] The main body includes the main combustion stage fuel circuit, the first auxiliary fuel circuit, and the second auxiliary fuel circuit;

[0009] The main combustion stage oil passage is adjacent to the first and second auxiliary oil passages and is arranged at an angle to each other to form a heat exchange zone; wherein...

[0010] At least two heat insulation cavities are provided, which are located in the space outside the heat exchange zone of the main body.

[0011] According to one embodiment of the present invention, the cross-sectional shape of the heat insulation cavity is arc-shaped, and the arc is concave towards the side facing the heat exchange zone.

[0012] According to one embodiment of the present invention, the number of the heat insulation cavities is at least three;

[0013] Each of the main combustion stage oil passages has a heat insulation cavity on the side facing the first auxiliary oil passage and the second auxiliary oil passage.

[0014] The present invention also provides an oil collecting ring, characterized in that it comprises:

[0015] The outer casing includes an outer ring plate, an inner ring plate, and a rectifier ring, wherein a pre-combustion stage cyclone separator is provided inside the rectifier ring;

[0016] A first chamber is formed between the outer ring plate and the inner ring plate;

[0017] The fuel line assembly as described above is installed in the first chamber;

[0018] A second chamber is formed between the inner ring plate and the rectifier ring. The second chamber is connected to the first chamber. The purge gas in the outer ring cavity enters the first chamber directly or through the second chamber.

[0019] According to one embodiment of the present invention, at least one flow hole is provided on the outer ring plate, and a flow guiding protrusion is provided on the fuel pipe assembly, one end of the flow guiding protrusion extending to the flow hole;

[0020] The guide protrusion has a guide pipe, which is connected to the main combustion stage fuel line. The fuel in the main combustion stage fuel line flows through the guide pipe and is sprayed outward from the flow hole.

[0021] According to one embodiment of the present invention, one end of the fuel pipe assembly is mounted on the inner ring plate by a support rod, and the circumferential dimension of the flow hole is at least larger than the cross-sectional dimension of the guide protrusion;

[0022] At least one flow guide hole is provided on the inner ring plate, and the flow guide hole is connected to the first chamber and the flow hole.

[0023] According to one embodiment of the present invention, the outer casing is flared towards the side of the flame tube;

[0024] The rectifier ring includes a first horizontal plate, a first inclined plate, and a first baffle, wherein the first inclined plate is connected to the first horizontal plate and the first baffle respectively;

[0025] The inner ring plate includes a second horizontal plate, a second inclined plate, and a second baffle, wherein the second inclined plate is connected to the second horizontal plate and the second baffle respectively;

[0026] The first inclined plate and the second inclined plate together constitute the flared design, and the first horizontal plate and the second horizontal plate, the first inclined plate and the second inclined plate, and the first baffle and the second baffle together form the second chamber;

[0027] The outer casing is equipped with a splash guard on the side facing the flame tube.

[0028] According to one embodiment of the present invention, an impact cavity is provided between the first baffle and the splash deflector;

[0029] The first baffle has a first through hole, which communicates with the second chamber and the impact chamber respectively;

[0030] The second baffle is provided with a second through hole, which communicates with the first chamber and the second chamber respectively.

[0031] According to one embodiment of the present invention, a third baffle and a fourth baffle are further provided in the second chamber. The third baffle is arranged parallel to the first baffle and the second baffle. The fourth baffle is arranged at an angle to the third baffle and is installed on the inner ring plate. The third baffle is installed on the outer ring plate.

[0032] The fourth baffle is provided with a third through hole, and the third through hole is set at an angle to the axial direction of the fuel nozzle.

[0033] The present invention also provides a fuel injector, characterized in that it comprises:

[0034] rod core;

[0035] As described above, the oil collecting ring and the rod core are used to provide fuel to the main combustion stage oil passage, the first auxiliary oil passage, and the second auxiliary oil passage.

[0036] The present invention also provides a combustion chamber, characterized in that it comprises:

[0037] Flame tube;

[0038] The casing is fitted onto the outside of the flame tube;

[0039] As described above, the fuel nozzle outputs fuel that is burned within the flame tube.

[0040] The present invention also provides a gas turbine engine, characterized in that it includes a rotor and a combustion chamber as described above.

[0041] The positive and progressive effects of this invention are as follows:

[0042] The oil collecting ring, fuel nozzle, combustion chamber, and gas turbine engine of this invention have at least the following advantages:

[0043] First, a heat insulation cavity is set outside the heat exchange zone formed by the main combustion stage fuel circuit, the first auxiliary fuel circuit, and the second auxiliary fuel circuit. This can block the heat transferred between the fuel pipe assembly and the mounting end of the inner ring plate, effectively reducing the fuel circuit temperature and reducing the risk of fuel coking.

[0044] Second, the path of the purging gas is optimized to ensure that the purging gas flows at a lower velocity and with better uniformity, thus reducing the risk of fuel coking. Attached Figure Description

[0045] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0046] Figure 1 This is a partial structural schematic diagram of the gas turbine engine of the present invention;

[0047] Figure 2 This is a schematic diagram of the structure of the fuel nozzle of the present invention;

[0048] Figure 3 for Figure 2 A schematic diagram of a cross-section of the fuel nozzle is shown below;

[0049] Figure 4 for Figure 2 The diagram shows another cross-section of the fuel nozzle.

[0050] Figure 5 for Figure 4 Enlarged structural diagram at point A;

[0051] Figure 6 for Figure 4 Enlarged structural diagram at point B;

[0052] Figure 7 for Figure 4 Enlarged structural diagram at point C;

[0053] Figure 8 for Figure 2 The diagram shows another cross-sectional view of the fuel nozzle.

[0054] Figure 9 for Figure 4 The diagram shown is a partial schematic diagram;

[0055] Figure 10 for Figure 4 The diagram shows one embodiment of gas flow.

[0056] Figure 11 for Figure 4 A schematic diagram of another embodiment of gas flow is shown.

[0057] 10. Oil collecting ring; 110. Main combustion stage fuel passage; 120. First auxiliary fuel passage; 130. Second auxiliary fuel passage; 140. Heat insulation cavity; 150. Heat exchange zone; 160. Flow guide protrusion; 161. Flow guide pipe; 170. Support rod; 180. Fuel pipe assembly;

[0058] 20. Fuel injector; 210. Housing; 211. Outer ring plate; 212. Inner ring plate; 213. Rectifying ring; 214. First chamber; 215. Second chamber; 216. Flow hole; 217. Guide hole; 218. Splash deflector; 219. Impact chamber; 220. Rod core;

[0059] 2120. First horizontal plate; 2121. First inclined plate; 2122. First baffle; 2123. First through hole;

[0060] 2110. Second horizontal plate; 2111. Second inclined plate; 2112. Second baffle; 2113. Second through hole;

[0061] 2150, Third baffle; 2151, Fourth baffle; 2152, Third through hole;

[0062] 30. Combustion chamber;

[0063] 40. Casing. Detailed Implementation

[0064] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0065] Embodiments of the invention will now be described in detail with reference to the accompanying drawings. Preferred embodiments of the invention will now be described in detail, examples of which are illustrated in the drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts. Furthermore, although the terminology used herein is selected from commonly known and used terminology, some terms mentioned in this specification may have been chosen by the applicant at his or her discretion, and their detailed meanings are explained in the relevant sections of the description herein. Moreover, the invention should be understood not only by the actual terms used, but also by the meaning implied by each term.

[0066] Please refer to Figures 1 to 11 The present invention proposes a gas turbine engine, including a rotor and a combustion chamber 30.

[0067] Combustion chamber 30 includes a flame tube, a casing 40, and a fuel nozzle 20. The airflow entering combustion chamber 30 is divided into three streams: the first stream is the outer annular cavity airflow, the second stream is the inner annular cavity airflow, and the third stream is the head intake airflow. The fuel nozzle 20 is composed of a rod core 220 and a fuel collecting ring 10. Air is compressed by the compressor and enters combustion chamber 30. After mixing with fuel, it is burned in the flame tube. The high-temperature gas produced flows backward to drive the turbine to do work.

[0068] Specifically, the fuel injector 20 includes a rod core 220 and a fuel collection ring 10, wherein the rod core 220 is used to supply fuel to the fuel line assembly 180 of the fuel collection ring 10.

[0069] Please refer to Figures 2 to 4 Specifically, the fuel line assembly 180 includes a body, which includes a main combustion stage fuel line 110, a first auxiliary fuel line 120 and a second auxiliary fuel line 130. The main combustion stage fuel line 110 is adjacent to the first auxiliary fuel line 120 and the second auxiliary fuel line 130 and is arranged at an angle to each other to form a heat exchange zone 150. The fuel line assembly 180 has at least two heat insulation cavities 140 outside the heat exchange zone 150.

[0070] In one embodiment, the main combustion stage oil passage 110, the first auxiliary oil passage 120 and the second auxiliary oil passage 130 are preferably arranged adjacently in a triangular and close arrangement, which is conducive to better heat exchange between them.

[0071] Meanwhile, the cross-sectional corners of the main combustion stage fuel line 110, the first auxiliary fuel line 120, and the second auxiliary fuel line 130 are rounded and smooth, without right angles or sharp angles. This reduces the contact area and heat-receiving area between the fuel and the pipe wall at the corners, eliminates the low-speed zone of fuel flow in these areas, enhances the ability of the fuel to carry away heat, reduces the fuel wet wall temperature, and reduces the risk of fuel coking.

[0072] Furthermore, the heat insulation cavity 140 set outside the heat exchange zone 150 can effectively reduce the heat brought by the purging air from the outside of the fuel line 180, and at the same time effectively reduce the fuel line temperature and reduce the risk of fuel coking.

[0073] In one embodiment, the heat insulation cavity 140 has an arc-shaped cross-section, with the arc-shaped section concave towards the heat exchange zone 150.

[0074] The heat insulation cavity 140 is curved and oriented toward the main combustion stage oil passage 110, the first auxiliary oil passage 120, and the second auxiliary oil passage 130. Thus, the multiple heat insulation cavities 140 are arranged in a ring around the main combustion stage oil passage 110, the first auxiliary oil passage 120, and the second auxiliary oil passage 130, thereby forming a heat exchange zone 150 around the main combustion stage oil passage 110, the first auxiliary oil passage 120, and the second auxiliary oil passage 130. The heat insulation cavity 140 outside the heat exchange zone 150 can provide heat insulation protection for the main combustion stage oil passage 110, the first auxiliary oil passage 120, and the second auxiliary oil passage 130 within the heat exchange zone 150.

[0075] In one embodiment, the fuel line assembly 180 is connected to the inner ring plate 212 via a support rod 170. Since the support rod 170 is connected to the inner ring plate 212, the heat on the inner ring plate 212 will be transferred through the support rod 170. Therefore, a heat insulation cavity 140 is provided inside the installation position of the support rod 170 and the fuel line assembly 180 to block the heat transferred from the support rod 170 and prevent the heat from the support rod 170 side from being transferred to the main combustion stage fuel line 110, the first auxiliary fuel line 120 and the second auxiliary fuel line 130, effectively reducing the fuel line temperature and reducing the risk of fuel coking.

[0076] Furthermore, a heat insulation cavity 140 is provided on each side of the main combustion stage oil circuit 110 facing the first auxiliary oil circuit 120 and the second auxiliary oil circuit 130, thereby improving the heat insulation effect on the periphery of the main combustion stage oil circuit 110.

[0077] The oil collecting ring 10 includes a housing 210 and the aforementioned fuel pipe assembly 180. The housing 210 has an outer ring plate 211, an inner ring plate 212, and a rectifier ring 213. A pre-combustion stage cyclone separator is provided inside the rectifier ring 213. A first chamber 214 is formed between the outer ring plate 211 and the inner ring plate 212. The fuel pipe assembly 180 is installed in the first chamber 214. A second chamber 215 is formed between the inner ring plate 212 and the rectifier ring 213. The second chamber 215 communicates with the first chamber 214. The purging gas in the outer ring chamber enters the first chamber 214 directly or through the second chamber 215.

[0078] The gas in the outer annular cavity is blown into the first chamber 214 through the second chamber 215, then flows through the first chamber 214 into the fuel pipe assembly 180, and then blown through the outer annular plate 211 to the outside of the fuel nozzle 20 to carry away the heat around the fuel pipe assembly 180.

[0079] Please refer to Figures 4 to 7 The outer ring plate 211 has at least one flow hole 216, and the fuel pipe assembly 180 has a guide protrusion 160, one end of which extends to the flow hole 216. A guide pipe 161 is provided inside the guide protrusion 160, and the guide pipe 161 is connected to the main combustion stage fuel passage 110. The fuel in the main combustion stage fuel passage 110 flows through the guide pipe 161 and is sprayed outward from the flow hole 216.

[0080] That is, the fuel in the main combustion stage fuel line 110 flows through the guide pipe 161 to the flow hole 216, and then is sprayed into the flame tube through the flow hole 216. One end of the guide protrusion 160 at least abuts against the flow hole 216 to prevent fuel from entering the first chamber 214.

[0081] Furthermore, one end of the fuel line assembly 180 is mounted on the inner ring plate 212 via a support rod 170, and the circumferential dimension of the flow hole 216 is at least larger than the cross-sectional dimension of the guide protrusion 160. At least one guide hole 217 is provided on the inner ring plate 212, and the guide hole 217 communicates with the first chamber 214 and the flow hole 216.

[0082] The size of the flow hole 216 is larger than the cross-sectional size of the guide protrusion 160 to allow space for the gas in the first chamber 214 to communicate with the flame tube. Thus, the cooling gas entering the first chamber 214 can flow into the flame tube through the flow hole 216 after carrying away the heat around the fuel pipe.

[0083] Specifically, the outer casing 210 has an flared design facing the flame tube, which facilitates increasing the volume of fuel injected into the flame tube, thereby improving combustion efficiency.

[0084] The rectifier ring 213 includes a first horizontal plate 2120, a first inclined plate 2121, and a first baffle 2122, with the first inclined plate 2121 connected to both the first horizontal plate 2120 and the first baffle 2122. The inner ring plate 212 includes a second horizontal plate 2110, a second inclined plate 2111, and a second baffle 2112, with the second inclined plate 2111 connected to both the second horizontal plate 2110 and the second baffle 2112.

[0085] The first inclined plate 2121 and the second inclined plate 2111 together form a flared design. The first horizontal plate 2120, the second horizontal plate 2110, the first inclined plate 2121 and the second inclined plate 2111, and the first baffle 2122 and the second baffle 2112 together form a second chamber 215. The outer shell 210 is provided with a splash deflector 218 on the side facing the flame tube.

[0086] The key to the air path design of the fuel injector 20 is to reduce the impact and convection of the purging air entering the injector on the oil collecting ring 10 and its internal fuel pipe assembly 180, so that the purging air is evenly distributed in the injector and flows around the fuel pipe assembly 180, thereby reducing the heating effect of the purging air on the oil passage inside the fuel pipe assembly 180.

[0087] Specifically, an impact cavity 219 is provided between the first baffle 2122 and the splash plate 218. The first baffle 2122 is provided with a first through hole 2123, which communicates with the second chamber 215 and the impact cavity 219 respectively; the second baffle 2112 is provided with a second through hole 2113, which communicates with the first chamber 214 and the second chamber 215 respectively.

[0088] Furthermore, the second chamber 215 is also provided with a third baffle 2150 and a fourth baffle 2151. The third baffle 2150 is arranged parallel to the first baffle 2122 and the second baffle 2112. The fourth baffle 2151 is angled with the third baffle 2150 and installed on the inner ring plate 212. The third baffle 2150 is installed on the outer ring plate 211. The fourth baffle 2151 has a third through hole 2152, which is angled with the axial direction of the fuel injector 20.

[0089] Please refer to Figures 8 to 11 The purging air in the outer annular cavity moves axially along the fuel nozzle 20 between the first horizontal plate 2120 and the second horizontal plate 2110, and changes its flow direction at the positions of the first inclined plate 2121 and the second inclined plate 2111, undergoing a first deceleration. Then, the purging air undergoes a first split at the first baffle 2122. One stream of purging air flows towards the splash plate 218, impacting and cooling the splash plate 218; the other stream of purging air flows to the second baffle 2112 and enters the first chamber 21 through the second through hole 2113. Inside the fourth chamber, under the action of the third baffle 2150 and the fourth baffle 2151, the airflow is slowed down and split again at the fourth baffle 2151. Part of the airflow flows to the inside of the fuel pipe assembly 180, and the other part flows to the outside space of the fuel pipe assembly 180, forming an envelopment around the fuel pipe assembly 180. At the same time, the purge gas initially flows directly to the first chamber 214 through the guide hole 217, forming a convection with the purge gas flowing in through the fourth baffle 2151, further slowing down the flow, and finally flowing into the flame tube from the flow hole 216.

[0090] Please refer to the details. Figure 10 The purge air from the guide hole 217 and one of the purge air streams passing through the fourth baffle 2151 form a convection flow inside the fuel line assembly 180, thus slowing down the two air streams and preventing the purge air from heating the fuel line assembly 180.

[0091] Or you can refer to Figure 11 The purge gas from the guide hole 217 crosses the inner side of the fuel line 180 and forms a convection with one of the purge gases passing through the fourth baffle 2151, and then flows out of the outer ring plate 211 through the flow hole 216.

[0092] This configuration significantly reduces the direct impact of the purging air on the fuel line assembly 180, making the airflow around the fuel line assembly 180 more uniform and reducing the heating effect of the purging air on the fuel lines inside the fuel line assembly 180.

[0093] That is, the present invention provides thermal protection for the fuel line assembly 180 in three directions.

[0094] The first method involves closely arranging the main combustion stage fuel line 110, the first auxiliary fuel line 120, and the second auxiliary fuel line 130, and rounding off the corners of the cross-sections of the fuel lines to avoid right angles and sharp angles. This reduces the contact area and heat-receiving area between the fuel and the pipe wall at the corners, eliminates the low-speed zone of fuel flow in these areas, enhances the fuel's ability to carry away heat, reduces the fuel's wet wall temperature, and reduces the risk of fuel coking.

[0095] The second method involves setting heat insulation chambers 140 on the outer periphery of the main combustion stage fuel line 110, the first auxiliary fuel line 120, and the second auxiliary fuel line 130. The multiple heat insulation chambers 140 form a protective enclosure around the three fuel lines on the fuel line assembly 180, which can effectively reduce the heat brought by the purge gas from the outside of the fuel line assembly 180. At the same time, the heat insulation chambers 140 arranged axially upstream of the auxiliary fuel line can also block the heat transmitted from the support rod 170, effectively reducing the fuel line temperature and reducing the risk of fuel coking.

[0096] The third approach involves designing the flow of the purging gas to ensure that it flows through the outside of the fuel line 180 at a lower velocity and with better uniformity, thereby reducing the risk of fuel coking.

[0097] In summary, the oil collecting ring, fuel injector, combustion chamber, and gas turbine engine of the present invention have at least the following advantages:

[0098] 1. A heat insulation cavity 140 is provided outside the heat exchange zone 150 formed by the main combustion stage oil circuit 110, the first auxiliary oil circuit 120 and the second auxiliary oil circuit 130. This can block the heat transferred between the fuel pipe assembly 180 and the mounting end of the inner ring plate 212, effectively reducing the oil circuit temperature and reducing the risk of fuel coking.

[0099] Second, the path of the purging gas is optimized to ensure that the purging gas flows at a lower velocity and with better uniformity, thus reducing the risk of fuel coking.

[0100] This application uses specific terms to describe embodiments of the application. Terms such as "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic associated with at least one embodiment of the application. Therefore, it should be emphasized and noted that references to "an embodiment," "one embodiment," or "an alternative embodiment" in different locations throughout this specification do not necessarily refer to the same embodiment. Furthermore, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0101] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. An oil collecting ring, characterized in that, include: The outer casing includes an outer ring plate, an inner ring plate, and a rectifier ring, wherein a pre-combustion stage cyclone separator is provided inside the rectifier ring; A first chamber is formed between the outer ring plate and the inner ring plate; A fuel line assembly is installed in the first chamber. The fuel line assembly includes a body, which includes a main combustion stage fuel line, a first auxiliary fuel line, and a second auxiliary fuel line. The main combustion stage fuel line is adjacent to the first auxiliary fuel line and the second auxiliary fuel line and is arranged at an angle to each other to form a heat exchange zone. The assembly also includes at least two heat insulation cavities, which are opened in the space outside the heat exchange zone of the body. A second chamber is formed between the inner ring plate and the rectifier ring. The second chamber is connected to the first chamber. The purge gas in the outer ring cavity enters the first chamber directly or through the second chamber.

2. The oil collecting ring according to claim 1, characterized in that, The heat insulation cavity has an arc-shaped cross-section, and the arc is concave towards the heat exchange zone.

3. The oil collecting ring according to claim 1, characterized in that, The number of the heat insulation cavities is at least three; Each of the main combustion stage oil passages has a heat insulation cavity on the side facing the first auxiliary oil passage and the second auxiliary oil passage.

4. The oil collecting ring according to claim 1, characterized in that, At least one flow hole is provided on the outer ring plate, and a flow guide protrusion is provided on the fuel pipe assembly, with one end of the flow guide protrusion extending to the flow hole; The guide protrusion has a guide pipe, which is connected to the main combustion stage fuel line. The fuel in the main combustion stage fuel line flows through the guide pipe and is sprayed outward from the flow hole.

5. The oil collecting ring according to claim 4, characterized in that, One end of the fuel line assembly is mounted on the inner ring plate via a support rod, and the circumferential dimension of the flow hole is at least larger than the cross-sectional dimension of the guide protrusion. At least one flow guide hole is provided on the inner ring plate, and the flow guide hole is connected to the first chamber and the flow hole.

6. The oil collecting ring according to claim 4, characterized in that, The outer casing is flared towards the flame tube side; The rectifier ring includes a first horizontal plate, a first inclined plate, and a first baffle, wherein the first inclined plate is connected to the first horizontal plate and the first baffle respectively; The inner ring plate includes a second horizontal plate, a second inclined plate, and a second baffle, wherein the second inclined plate is connected to the second horizontal plate and the second baffle respectively; The first inclined plate and the second inclined plate together constitute the flared design, and the first horizontal plate and the second horizontal plate, the first inclined plate and the second inclined plate, and the first baffle and the second baffle together form the second chamber; The outer casing is equipped with a splash guard on the side facing the flame tube.

7. The oil collecting ring according to claim 6, characterized in that, An impact cavity is provided between the first baffle and the splash deflector; The first baffle has a first through hole, which communicates with the second chamber and the impact chamber respectively; The second baffle is provided with a second through hole, which communicates with the first chamber and the second chamber respectively.

8. The oil collecting ring according to claim 7, characterized in that, The second chamber is also provided with a third baffle and a fourth baffle. The third baffle is arranged parallel to the first baffle and the second baffle. The fourth baffle is arranged at an angle to the third baffle and is installed on the inner ring plate. The third baffle is installed on the outer ring plate. The fourth baffle is provided with a third through hole, and the third through hole is set at an angle to the axial direction of the rectifier ring.

9. A fuel nozzle, characterized in that, include: rod core; The oil collecting ring as described in any one of claims 1-8, wherein the rod core is used to provide fuel to the main combustion stage oil passage, the first auxiliary oil passage, and the second auxiliary oil passage.

10. A combustion chamber, characterized in that, include: Flame tube; The casing is fitted onto the outside of the flame tube; The fuel nozzle as described in claim 9, wherein the fuel output from the fuel nozzle is burned within the flame tube.

11. A gas turbine engine, characterized in that, It includes a rotor and a combustion chamber as described in claim 10.

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