Oil collector ring and method of cooling same, fuel nozzle, combustion chamber, and turbine engine

Abstract

The application provides a collecting ring, a collecting ring cooling method, a fuel nozzle, a combustion chamber and a turbine engine, which can effectively solve the fuel coking problem of the oil circuit of the collecting ring. The turbine engine comprises the combustion chamber, the combustion chamber comprises the fuel nozzle, and the fuel nozzle comprises the collecting ring. The collecting ring is provided with a main oil circuit channel and an auxiliary oil circuit channel. The main oil circuit channel is used for a main combustion stage, and the auxiliary oil circuit channel is used for a pre-combustion stage. The auxiliary oil circuit channel comprises an auxiliary oil circuit spiral structure, the axis of the auxiliary oil circuit spiral structure at least partially surrounds the axis of the collecting ring, and the auxiliary oil circuit spiral structure winds around the main oil circuit channel. The collecting ring cooling method adopts the collecting ring. The fuel in the auxiliary oil circuit channel spirally flows along the auxiliary oil circuit spiral structure and exchanges heat with the fuel in the main oil circuit channel and the body of the collecting ring, so that the temperature uniformity of the oil circuit of the collecting ring is improved.

Description

Technical Field

[0001] This invention relates to the field of turbine engine technology, specifically to an oil collecting ring, an oil collecting ring cooling method, a fuel nozzle, a combustion chamber, and a turbine engine. Background Technology

[0002] In the field of aero-engines, with increasingly stringent environmental protection requirements, the emission limits for civil aero-engines are becoming more and more stringent. Modern civil aero-engines widely adopt low-emission combustion technologies to meet low-emission requirements.

[0003] Among low-emission combustion technologies, lean fuel low-emission combustion technology has the greatest potential for reducing emissions and is a very promising low-emission technology. Lean fuel low-emission technology typically requires the use of staged fuel injectors, which are divided into a pre-combustion stage and a main combustion stage. Under low operating conditions, fuel is supplied only through the auxiliary fuel circuit in the pre-combustion stage, while under high operating conditions, fuel is supplied simultaneously through the auxiliary fuel circuit in the pre-combustion stage and the main fuel circuit in the main combustion stage.

[0004] However, a significant problem with staged fuel injectors is that they are prone to fuel coking, which reduces the flow area of ​​the fuel line and can even clog the injectors in severe cases. This affects the fuel atomization effect and the life of the injectors, leading to a deterioration in combustion efficiency, emissions, and outlet temperature distribution in the combustion chamber, resulting in increased fuel consumption and decreased power performance of the engine.

[0005] In lean fuel combustion technology, fuel coking in staged fuel injectors is a critical challenge that requires overcoming and is receiving increasing attention. The main reason for fuel coking in staged fuel injectors is that under low operating conditions, the main fuel circuit is not supplying fuel, leaving residual fuel stagnant. This stagnant fuel, heated by high-temperature air or combustion gas radiation, easily cokes. Under high operating conditions, the auxiliary fuel circuit has low fuel flow and poor heat exchange, making it prone to overheating. The fuel collecting ring located at the nozzle head is particularly susceptible to overheating, leading to fuel coking within the ring.

[0006] To address the overheating issue within the oil collecting ring, one solution involves setting two concentric annular oil passages within the oil collecting ring, namely a main oil passage and a secondary oil passage. This allows for heat exchange between the main and secondary oil passages, providing some cooling to the main oil passage. However, the inventors discovered during the development of this invention that the cooling effect of this solution is limited, and overheating still occurs in localized areas of the oil passage, leading to coking of the fuel within the oil collecting ring.

[0007] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of this disclosure, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0008] One objective of this invention is to provide an oil collecting ring that can effectively solve the problem of fuel coking in the oil collecting ring's oil passage.

[0009] To achieve the aforementioned purpose, an oil collecting ring is used for a fuel injector. The oil collecting ring is provided with a main oil passage and a secondary oil passage. The main oil passage is used for the main combustion stage, and the secondary oil passage is used for the pre-combustion stage. The secondary oil passage includes a secondary oil passage spiral structure. The axis of the secondary oil passage spiral structure at least partially surrounds the axis of the oil collecting ring, and the secondary oil passage spiral structure is wound around the main oil passage.

[0010] In one or more embodiments of the oil collecting ring, the main oil passage is split in the circumferential direction of the oil collecting ring to form two independent branch oil passages.

[0011] In one or more embodiments of the oil collecting ring, the main oil passage includes a partial annular structure, which is located inside the secondary oil passage spiral structure.

[0012] In one or more embodiments of the oil collecting ring, the main oil passage includes a main oil passage spiral structure, and the main oil passage spiral structure and the auxiliary oil passage spiral structure are intertwined to form a multi-spiral structure.

[0013] In one or more embodiments of the oil collecting ring, the main oil passage spiral structure and the auxiliary oil passage spiral structure have opposite positions and matching shapes.

[0014] In one or more embodiments of the oil collecting ring, the main oil passage includes a main combustion stage nozzle, which extends from the gap of the auxiliary oil passage spiral structure.

[0015] In one or more embodiments of the oil collecting ring, the oil collecting ring includes a plurality of the secondary oil passages, and the spiral structures of each of the plurality of secondary oil passages are intertwined to form a multi-spiral structure.

[0016] In one or more embodiments of the oil collecting ring, the oil collecting ring is a 3D printed part.

[0017] In one or more embodiments of the oil collecting ring, the cross-section of the auxiliary oil passage spiral structure includes two endpoints, the line connecting the two endpoints is the boundary line between the inner and outer sides of the cross-section, and the boundary line of the cross-section protrudes towards the inner and outer sides.

[0018] In one or more embodiments of the oil collecting ring, the main oil passage includes a main oil passage spiral structure, the main oil passage spiral structure and the auxiliary oil passage spiral structure are intertwined to form a multiple spiral structure, the cross-section of the main oil passage spiral structure includes two endpoints, the line connecting the two endpoints is the dividing line between the inner and outer sides of the cross-section, and the boundary line of the cross-section protrudes to the inner and outer sides.

[0019] Another objective of this invention is to provide a cooling method for the oil collecting ring, which can effectively solve the problem of fuel coking in the oil collecting ring's oil passage.

[0020] To achieve the aforementioned objective, the oil collecting ring cooling method employs the aforementioned oil collecting ring. The fuel in the secondary oil passage flows spirally along the spiral structure of the secondary oil passage and exchanges heat with the fuel in the main oil passage and the body of the oil collecting ring, thereby improving the temperature uniformity of the oil passage of the oil collecting ring.

[0021] In one or more embodiments of the oil collecting ring cooling method, the oil collecting ring includes a first secondary oil passage and a second secondary oil passage, the secondary oil passage spiral structures of the first secondary oil passage and the second secondary oil passage are intertwined, and the fuel in the first secondary oil passage flows in the opposite direction to the fuel in the second secondary oil passage.

[0022] This oil collecting ring and its cooling method increase the heat exchange area between the main and auxiliary oil passages by incorporating a spiral structure that winds around the auxiliary oil passage. This allows for thorough and uniform heat exchange between the fuel in the main and auxiliary oil passages, with the cooler fuel cooling the hotter fuel. Furthermore, since the heat exchange conditions between different parts of the oil collecting ring's surface and the outside environment vary, the spiral structure allows for repeated heat exchange between the fuel and different parts of the oil collecting ring as it flows along the spiral. This improves the temperature uniformity of the oil passages within the oil collecting ring, enhances the cooling effect, and effectively prevents overheating and coking of the fuel. Consequently, it ensures good fuel atomization, extends the life of the fuel injectors, improves combustion efficiency in the combustion chamber, and enhances the performance of the turbine engine. Moreover, this oil collecting ring is small in size and has a compact structure.

[0023] Another objective of this invention is to provide a fuel nozzle that can effectively solve the problem of fuel coking in the fuel collecting ring of the fuel nozzle.

[0024] The fuel nozzle for achieving the aforementioned purpose includes the aforementioned fuel collecting ring.

[0025] Another objective of this invention is to provide a combustion chamber that can effectively solve the problem of fuel coking in the fuel collecting ring of the fuel injector.

[0026] The combustion chamber for achieving the aforementioned purpose includes the aforementioned fuel nozzle.

[0027] Another objective of this invention is to provide a turbine engine that can effectively solve the problem of fuel coking in the fuel injection ring oil passage of the fuel injector.

[0028] A turbine engine for achieving the aforementioned purpose includes the aforementioned combustion chamber.

[0029] By employing this oil collecting ring, the turbine engine, combustion chamber, and fuel injector can effectively prevent overheating of the oil passage within the oil collecting ring and avoid fuel coking, thereby ensuring fuel atomization, extending the life of the fuel injector, improving the combustion efficiency of the combustion chamber, and enhancing the performance of the turbine engine. Attached Figure Description

[0030] 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:

[0031] Figure 1 This is a schematic diagram of a combustion chamber according to one or more embodiments.

[0032] Figure 2 This is a schematic diagram of a fuel nozzle according to one or more embodiments.

[0033] Figure 3 This is a schematic diagram of the main oil passage and auxiliary oil passage of the oil collecting ring according to one embodiment.

[0034] Figure 4 yes Figure 3 A schematic diagram of its breakdown.

[0035] Figure 5 yes Figure 3 Schematic diagram of section AA.

[0036] Figure 6 This is a schematic diagram of the main oil passage and auxiliary oil passage of the oil collecting ring according to another embodiment.

[0037] Figure 7 yes Figure 6 A schematic diagram of its breakdown.

[0038] Figure 8 yes Figure 6 Schematic diagram of the BB section. Detailed Implementation

[0039] The following discloses various implementation methods or embodiments of the described subject matter. To simplify the disclosure, specific examples of the elements and arrangements are described below. These are merely examples and are not intended to limit the scope of protection of the present invention. It should be noted that the accompanying drawings are for illustrative purposes only and are not drawn to scale, and should not be construed as limiting the actual scope of protection claimed by the present invention. It should be noted that the same or similar reference numerals denote the same or similar items in the following drawings; therefore, once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings. Furthermore, certain features, structures, or characteristics of one or more embodiments of this application can be appropriately combined.

[0040] A turbine engine (not shown) according to one or more embodiments of the present invention includes, as follows: Figure 1 The combustion chamber 100 is shown. The combustion chamber 100 mainly consists of a fuel nozzle 5, a flame tube 7, and a casing 9. Air 1 from the high-pressure compressor outlet enters the combustion chamber 100 and is divided into three streams: outer annular air 2, head intake air 3, and inner annular air 4. The head intake air 3 mixes with the fuel injected by the fuel nozzle 5 and burns in the flame tube 7. The resulting high-temperature gas flows downstream, thereby driving the turbine to perform work. The air 1 from the high-pressure compressor outlet and the high-temperature gas in the flame tube 7 heat the fuel nozzle 5 through radiation and convection heat exchange.

[0041] In the description of this invention, it should be noted that the terms "upstream" and "downstream" refer to the relative directions of fluid flow in the fluid channel. For example, "upstream" refers to the direction from which the fluid flows, while "downstream" refers to the direction to which the fluid flows.

[0042] Reference Figure 2 The fuel nozzle 5 includes a fuel line 10, a nozzle housing 14, and a nozzle mounting base 17. The nozzle mounting base 17 is used to connect to the casing 9 and provides a fuel inlet (not shown). The fuel line 10 is fluidly connected to the fuel inlet of the nozzle mounting base 17 to deliver fuel to the nozzle head 50, which is then sprayed out through the pre-combustion stage nozzle 11 and the main combustion stage nozzle 123. The nozzle housing 14 is located outside the fuel line 10 and has a gap between it and the fuel line 10. The nozzle housing 14 and the fuel line 10 are partially separated to prevent them from contacting each other, thus preventing the heat of the nozzle housing 14 from being transferred to the fuel line 10 through heat conduction. This allows the nozzle housing 14 to isolate external hot air from the radiation and convection heat transfer of the fuel line 10, reducing the temperature rise of the fuel in the fuel line 10.

[0043] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or a fluid connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0044] Reference Figures 2 to 5 The oil pipe 10 includes a pre-combustion stage nozzle 11, a collecting ring 12, and a fuel rod 13. The pre-combustion stage nozzle 11 and the collecting ring 12 are located at the nozzle head 50, with the pre-combustion stage nozzle 11 located at the center of the nozzle head 50 and the collecting ring 12 surrounding the outside of the pre-combustion stage nozzle 11. The collecting ring 12 includes a body 120 and a main oil passage 121 and a secondary oil passage 122 disposed within the body 120. The main oil passage 121 includes a main combustion stage nozzle 123. The main oil passage 121 and the secondary oil passage 122 are connected to the fuel inlet of the nozzle mounting seat 17 via the fuel rod 13. The fuel flowing in from the fuel inlet is divided into two oil passages: the main oil passage and the secondary oil passage. The fuel in the main oil passage and the secondary oil passage flows along the main oil passage 121 and the secondary oil passage 122, respectively, to supply fuel to the main combustion stage nozzle 123 and the pre-combustion stage nozzle 11.

[0045] Multiple main combustion stage nozzles 123 are distributed circumferentially along the oil collecting ring 12 and extend to the radial outer side of the body 120. The nozzle housing 14 is provided with multiple outlet holes 141 corresponding one-to-one with the main combustion stage nozzles 123, so that the fuel injected from the main combustion stage nozzles 123 is ejected from the nozzle housing 14 through the outlet holes 141.

[0046] As fuel flows from the fuel inlet of the nozzle mounting seat 17 to the nozzle head 50, its temperature gradually increases due to the radiative heat exchange of the air 1 at the high-pressure compressor outlet. Meanwhile, the radiative heat exchange of the high-temperature gas in the flame tube 7 mainly affects the nozzle head 50. Therefore, the fuel temperature at the nozzle head 50 is relatively high. It is necessary to set up a secondary oil passage 122 in the oil collecting ring 12 to exchange heat between the fuel in the main oil passage 121, the fuel in the secondary oil passage 122, and the body 120 of the oil collecting ring 12. This allows the cooler fuel in the flow path with a larger flow rate and higher velocity to cool the hotter fuel in the flow path with a smaller flow rate or lower velocity, thereby reducing the maximum temperature of the fuel in the oil collecting ring 12 and preventing the fuel from overheating and coking.

[0047] Specifically, under low operating conditions, the main combustion stage injector 123 does not inject fuel, and the fuel remaining in the main fuel passage 121 does not flow. The fuel is heated for a longer time, resulting in a larger temperature rise and a higher temperature. Meanwhile, fuel continues to flow in the auxiliary fuel passage 122. The fuel is heated for a shorter time during its flow, resulting in a smaller temperature rise and a lower temperature. Thus, the fuel in the auxiliary fuel passage 122 can be used to cool the fuel in the main fuel passage 121. Under high operating conditions, the fuel flow rate in the main fuel passage 121 is larger, resulting in stronger heat exchange capacity and a smaller temperature rise during its flow. Meanwhile, the fuel flow rate in the auxiliary fuel passage 122 is smaller, resulting in weaker heat exchange capacity and a larger temperature rise and a higher temperature. Thus, the fuel in the main fuel passage 121 can be used to cool the fuel in the auxiliary fuel passage 122.

[0048] Reference Figure 3 and Figure 4 Optionally, the main oil passage 121 splits circumferentially in the oil collecting ring 12 to form two independent branch oil passages 1210. Each branch oil passage 1210 includes an inlet section 1211 and an enclosing section 1212. The inlet section 1211 is located upstream of the enclosing section 1212 and is used to supply oil to the enclosing section 1212. The main combustion stage nozzle 123 is connected to the enclosing section 1212. The enclosing section 1212 has a partially annular structure, which extends in a direction parallel to the circumference of the oil collecting ring 12. That is, the enclosing section 1212 partially surrounds the axis 126 of the oil collecting ring 12. The enclosing sections 1212 of the two branch oil passages 1210 are opposite each other radially in the oil collecting ring 12 and form a structure close to a complete ring.

[0049] Therefore, dividing the main oil passage 121 into two independent branch oil passages 1210 can shorten the flow length of fuel in the oil collecting ring 12 within the main oil passage 121, reduce the time the fuel is heated, thereby reducing the temperature rise of the fuel in the main oil passage 121, further reducing the risk of coking of the fuel in the main oil passage 121, and improving the heat exchange capacity of the fuel in the main oil passage 121 under heavy operating conditions.

[0050] Optionally, the two oil distribution channels 1210 are symmetrical structures, and the surrounding section 1212 of each oil distribution channel 1210 is close to semi-circular, that is, the angle of each surrounding section 1212 in the circumferential direction of the oil collecting ring 12 is close to 180°, which can simplify the structure of the main oil distribution channel 121.

[0051] In other embodiments, the main oil passage 121 includes more than two branch oil passages 1210, thereby further shortening the flow length of fuel in the main oil passage 121 in the oil collecting ring 12, reducing the fuel heating time, and lowering the temperature rise of fuel in the main oil passage 121.

[0052] In another embodiment, the main oil passage 121 is a complete oil passage, that is, the main oil passage 121 includes only an oil inlet section 1211 and an enclosing section 1212. The enclosing section 1212 is close to a complete ring, that is, the angle in the circumferential direction of the oil collecting ring 12 is close to 360°, thereby simplifying the structure of the main oil passage 121.

[0053] Reference Figures 3 to 5 The auxiliary oil passage 122 includes two sub-oil passages, namely the first auxiliary oil passage 124 and the second auxiliary oil passage 125. The first auxiliary oil passage 124 includes a first auxiliary oil passage spiral structure 1241, and the second auxiliary oil passage 125 includes a second auxiliary oil passage spiral structure 1251. The first axis 1244 of the first auxiliary oil passage spiral structure 1241 and the second axis 1254 of the second auxiliary oil passage spiral structure 1251 overlap and at least partially surround the axis 126 of the oil collecting ring 12. That is, the first auxiliary oil passage spiral structure 1241 and the second auxiliary oil passage spiral structure 1251 extend in a direction parallel to the circumference of the oil collecting ring 12 while spiraling.

[0054] The first auxiliary oil circuit spiral structure 1241 and the second auxiliary oil circuit spiral structure 1251 are intertwined to form a double spiral structure. This double spiral structure is wrapped around the surrounding section 1212 of the main oil circuit channel 121, thereby greatly increasing the heat exchange area between the main oil circuit channel 121 and the auxiliary oil circuit channel 122 in a limited space, improving the cooling effect, and effectively preventing the oil circuit in the oil collecting ring 12 from overheating and causing fuel coking.

[0055] Furthermore, the surrounding section 1212 of the main oil passage 121 is located inside the double helix structure of the auxiliary oil passage 122, which can make the heat exchange between the various parts of the cross-section of the main oil passage 121 and the auxiliary oil passage 122 more uniform, making the temperature of the fuel in the main oil passage 121 more uniform, avoiding local overheating of the fuel in the main oil passage 121, or making the main oil passage 121 provide a more uniform cooling effect to the auxiliary oil passage 122, and can make full use of the internal space of the double helix structure, resulting in a small volume and compact structure.

[0056] Optionally, the cross-section of the enclosing section 1212 of the main oil passage 121 is circular, and the center of the circle is located on the first axis 1244 of the first auxiliary oil passage spiral structure 1241 and the second axis 1254 of the second auxiliary oil passage spiral structure 1251. That is, the main oil passage 121 is located at the center of the first auxiliary oil passage spiral structure 1241 and the second auxiliary oil passage spiral structure 1251, thereby further increasing the circumferential heat transfer uniformity of the cross-section of the main oil passage 121, or enabling the main oil passage 121 to provide a more uniform cooling effect to the auxiliary oil passage 122.

[0057] In other embodiments, the secondary oil passage 122 includes more than two sub-oil passages, thereby further increasing the heat exchange area between the main oil passage 121 and the secondary oil passage 122, improving the cooling effect and the temperature uniformity of the fuel in the main oil passage 121. In yet another embodiment, the secondary oil passage 122 is only a single oil passage, thereby simplifying the structure of the secondary oil passage 122.

[0058] In the description of this invention, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0059] Continue to refer to Figures 3 to 5 Optionally, multiple main combustion stage nozzles 123 extend from the gaps in the double-helix structure of the auxiliary fuel passage 122. That is, the auxiliary fuel passage 122 is located on both radial sides of the main combustion stage nozzles 123. This allows for sufficient heat exchange between the fuel in the auxiliary fuel passage 122 and the fuel in the main combustion stage nozzles 123, thus adequately cooling the fuel in the main combustion stage nozzles 123 and preventing coking. This design is simple and easy to mold. In another embodiment (not shown), the main combustion stage nozzles 123 pass through the body portion of the double-helix structure, i.e., the main combustion stage nozzles 123 penetrate the auxiliary fuel passage 122. However, the fuel in the main combustion stage nozzles 123 is not connected to the fuel in the auxiliary fuel passage 122, allowing for sufficient heat exchange between the fuel in the auxiliary fuel passage 122 and the fuel in the main combustion stage nozzles 123.

[0060] The first auxiliary oil passage 124 further includes a first inlet oil passage 1242 and a first outlet oil passage 1243, which are respectively connected to the two ends of the first auxiliary oil passage spiral structure 1241. The first inlet oil passage 1242 is used to input fuel into the first auxiliary oil passage spiral structure 1241. The first outlet oil passage 1243 is connected to the pre-combustion stage nozzle 11 and is used to guide the fuel flowing out of the first auxiliary oil passage spiral structure 1241 to the pre-combustion stage nozzle 11.

[0061] The second auxiliary oil passage 125 also includes a second oil inlet passage 1252 and a second oil outlet passage 1253, which are respectively connected to the two ends of the second auxiliary oil passage spiral structure 1251. The second oil inlet passage 1252 is used to input fuel into the second auxiliary oil passage spiral structure 1251. The second oil outlet passage 1253 is connected to the pre-combustion stage nozzle 11 and is used to guide the fuel flowing out of the second auxiliary oil passage spiral structure 1251 to the pre-combustion stage nozzle 11.

[0062] Optionally, the fuel flow directions within the first auxiliary oil passage spiral structure 1241 and the second auxiliary oil passage spiral structure 1251 are opposite, for example, according to... Figure 3 As shown, the fuel in the first auxiliary oil circuit spiral structure 1241 flows spirally while rotating clockwise around the axis 126 of the oil collecting ring 12, and the fuel in the second auxiliary oil circuit spiral structure 1251 flows spirally while rotating counterclockwise around the axis 126 of the oil collecting ring 12, in order to achieve a better cooling effect.

[0063] Specifically, under low operating conditions, as the fuel in the first auxiliary oil circuit spiral structure 1241 and the second auxiliary oil circuit spiral structure 1251 cools the fuel in the main oil circuit channel 121 during its flow, and is subjected to heat radiation from external hot air and the nozzle shell 14, the temperature gradually increases and the heat exchange capacity gradually decreases. By setting the fuel flow direction in the first auxiliary oil circuit spiral structure 1241 and the second auxiliary oil circuit spiral structure 1251 to be opposite, the part with poor fuel heat exchange capacity in the first auxiliary oil circuit spiral structure 1241 can be adjacent to the part with strong fuel heat exchange capacity in the second auxiliary oil circuit spiral structure 1251. This allows heat exchange to occur between the fuel in the first auxiliary oil circuit spiral structure 1241 and the second auxiliary oil circuit spiral structure 1251, thereby forming the first auxiliary oil circuit spiral structure 1241 and the second auxiliary oil circuit spiral structure 1251. The overall heat exchange capacity of the double helix structure is relatively balanced in the circumferential direction of the oil collecting ring 12, so as to avoid local overheating of the fuel in the main oil passage 121. Under heavy operating conditions, the fuel in the first auxiliary oil passage helical structure 1241 and the second auxiliary oil passage helical structure 1251 is cooled by the fuel in the main oil passage 121 and is also subjected to external heat radiation. By setting the fuel flow direction of the first auxiliary oil passage helical structure 1241 and the second auxiliary oil passage helical structure 1251 to be opposite, heat exchange can occur between the fuel in the first auxiliary oil passage helical structure 1241 and the second auxiliary oil passage helical structure 1251, so that the temperature of the fuel in the first auxiliary oil passage helical structure 1241 and the second auxiliary oil passage helical structure 1251 is relatively balanced in the circumferential direction of the oil collecting ring 12, thereby avoiding local overheating of the fuel in the auxiliary oil passage 122.

[0064] Reference Figures 6 to 8 In another embodiment, the surrounding section 1212 of the main oil passage 121 includes a main oil passage spiral structure 1213. The main oil passage spiral structure 1213, the first auxiliary oil passage spiral structure 1241, and the second auxiliary oil passage spiral structure 1251 are intertwined to form a multiple spiral structure. This greatly increases the heat exchange area between the main oil passage 121 and the auxiliary oil passage 122 within a limited space, improving the cooling effect and effectively preventing fuel coking caused by overheating in the oil passage within the oil collecting ring 12. The fuel flow direction in the main oil passage spiral structure 1213 and the first auxiliary oil passage spiral structure 1241 and the second auxiliary oil passage spiral structure 1251 can be the same or different.

[0065] The main oil passage spiral structure 1213 has matching surfaces with the first auxiliary oil passage spiral structure 1241 and the second auxiliary oil passage spiral structure 1251. For example, the first side surface 1214 of the main oil passage spiral structure 1213 and the first surface 1249 of the first auxiliary oil passage spiral structure 1241 are positioned opposite each other and have matching shapes. Similarly, the second side surface 1215 of the main oil passage spiral structure 1213 and the second surface 1259 of the second auxiliary oil passage spiral structure 1251 are positioned opposite each other and have matching shapes. Therefore, the main oil passage channel 121 and the auxiliary oil passage channel 122 have a large heat exchange area and are close together, which improves the cooling effect, effectively prevents fuel coking in the main oil passage channel 121 or the auxiliary oil passage channel 122, and results in a small volume and compact structure.

[0066] The main combustion stage nozzle 123 extends from the main oil passage spiral structure 1213 into the gap between the first auxiliary oil passage spiral structure 1241 and the second auxiliary oil passage spiral structure 1251, and extends to the outer surface of the body 120 of the oil collecting ring 12. The first auxiliary oil passage spiral structure 1241 also includes a third surface 1240, and the second auxiliary oil passage spiral structure 1251 also includes a fourth surface 1250. The main combustion stage nozzle 123 is located between the third surface 1240 and the fourth surface. The third surface 1240 and the fourth surface 1250 are parallel to or approximately parallel to the centerline of the main combustion stage nozzle 123, and are close to the main combustion stage nozzle 123. As a result, the auxiliary oil passage channel 122 and the main combustion stage nozzle 123 have a large heat exchange area and are close to each other, thereby improving the cooling effect, effectively preventing fuel coking in the main combustion stage nozzle 123, and having a small volume and compact structure.

[0067] Therefore, the oil collecting ring 12 and the oil collecting ring cooling method according to one or more embodiments of the present invention can increase the heat exchange area between the main oil passage 121 and the auxiliary oil passage 122 by setting a spiral structure that winds around the main oil passage 121 in the auxiliary oil passage 122, so that the fuel in the main oil passage 121 and the fuel in the auxiliary oil passage 122 can exchange heat fully and evenly, and the lower temperature fuel can cool the higher temperature fuel. In addition, since the heat exchange conditions between different parts of the surface of the oil collecting ring 12 body 120 and the outside are different, by setting a spiral structure in the oil passage, the fuel can exchange heat repeatedly with different parts of the oil collecting ring 12 body 120 during the flow along the spiral structure, which can improve the temperature uniformity of the oil passage in the oil collecting ring 12, improve the cooling effect, effectively avoid the oil passage in the oil collecting ring 12 from overheating and causing fuel coking, thereby ensuring the fuel atomization effect, extending the life of the fuel nozzle 5, improving the combustion efficiency of the combustion chamber 100 and the performance of the turbine engine, and the oil collecting ring 12 is small in size and compact in structure.

[0068] The oil collecting ring 12 and its internal main oil passage 121 (excluding the main combustion stage nozzle 12) and auxiliary oil passage 122 can be integrally formed by 3D printing for easy manufacturing. The main combustion stage nozzle 123 can be processed by processes such as electrical discharge machining or laser drilling to ensure the dimensional accuracy of the main combustion stage nozzle 123.

[0069] Reference Figure 5 The first cross-section of the first auxiliary oil circuit spiral structure 1241, that is, the cross-section perpendicular to the first axis 1244 of the first auxiliary oil circuit spiral structure 1241, includes a first boundary line 1246 and two first endpoints 1247. The first connecting line 1248 connecting the two first endpoints 1247 is the dividing line between the inner and outer sides of the first cross-section, wherein the inner side is the side closer to the first axis 1244 of the first auxiliary oil circuit spiral structure 1241, and the outer side is the side away from the first axis 1244 of the first auxiliary oil circuit spiral structure 1241. The first boundary line 1246 is convex in both the inner and outer sides of the first connecting line 1248, for example, the first boundary line 1246 is similar to an olive shape, thereby making the first auxiliary oil circuit spiral structure 1241 easier to form by 3D printing and improving the forming quality.

[0070] Similarly, the second cross section of the second auxiliary oil circuit spiral structure 1251 includes a second boundary line 1256 and two second endpoints 1257. The second boundary line 1256 protrudes inward and outward relative to the second connecting line 1258 connecting the two second endpoints 1257, so as to facilitate 3D printing and improve the molding quality.

[0071] Similarly, in Figures 6 to 8 In the embodiment shown, the boundary lines of the cross sections of the main oil circuit spiral structure 1213, the first auxiliary oil circuit spiral structure 1241, and the second auxiliary oil circuit spiral structure 1251 protrude inward and outward relative to the corresponding connecting lines, respectively, so as to facilitate 3D printing and improve the molding quality.

[0072] Reference Figure 1 and Figure 2 The fuel nozzle 5 also includes a splash guard 15, located downstream of the fuel collecting ring 12. The splash guard 15 is used to isolate the high-temperature combustion gases within the flame tube 7 from the heat radiation emitted by the nozzle head 50, thereby further reducing the temperature rise of the fuel within the fuel collecting ring 12 and preventing fuel coking within the fuel passage of the fuel collecting ring 12. The injection direction of the main combustion stage nozzle 123 of the fuel collecting ring 12 must avoid the splash guard 15.

[0073] In some other embodiments, a splash guard 15 is not provided downstream of the oil collecting ring 12, and the main combustion stage nozzle 123 of the oil collecting ring 12 can spray along the radial direction, or the axial direction, or the oblique direction between the radial and axial directions of the oil collecting ring 12.

[0074] By employing the oil collecting ring 12, the turbine engine, the combustion chamber 100, and the fuel nozzle 5 can effectively prevent overheating of the oil passage within the oil collecting ring 12, avoid fuel coking, thereby ensuring fuel atomization, extending the life of the fuel nozzle 5, improving the combustion efficiency of the combustion chamber 100, and enhancing the performance of the turbine engine.

[0075] 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. A fuel collecting ring for use with a fuel injector, wherein the fuel collecting ring has a main fuel passage and a secondary fuel passage, the main fuel passage being used for the main combustion stage and the secondary fuel passage being used for the pre-combustion stage, characterized in that... The auxiliary oil passage includes an auxiliary oil passage spiral structure, the axis of which at least partially surrounds the axis of the oil collecting ring, and the auxiliary oil passage spiral structure is wound around the main oil passage. The main oil passage includes a partially annular structure, which is located inside the auxiliary oil passage spiral structure. The oil collecting ring includes multiple auxiliary oil passages, and the spiral structures of each of the multiple auxiliary oil passages are intertwined to form a multi-spiral structure, extending in a direction parallel to the circumference of the oil collecting ring while spiraling.

2. The oil collecting ring as described in claim 1, characterized in that, The main oil passage splits circumferentially in the oil collecting ring to form two independent branch oil passages.

3. The oil collecting ring as described in claim 1, characterized in that, The main oil passage includes a main oil passage spiral structure, which is intertwined with the auxiliary oil passage spiral structure to form a multi-spiral structure.

4. The oil collecting ring as described in claim 3, characterized in that, The main oil passage spiral structure and the auxiliary oil passage spiral structure have opposite positions and matching shapes.

5. The oil collecting ring as described in any one of claims 1 to 4, characterized in that, The main oil passage includes a main combustion stage nozzle, which extends out of the secondary oil passage spiral structure from the gap in the secondary oil passage spiral structure.

6. The oil collecting ring according to any one of claims 1 to 4, characterized in that, The oil collecting ring is a 3D printed part.

7. The oil collecting ring as described in claim 6, characterized in that, The cross-section of the auxiliary oil passage spiral structure includes two endpoints, and the line connecting the two endpoints is the dividing line between the inner and outer sides of the cross-section. The boundary line of the cross-section protrudes to the inner and outer sides.

8. The oil collecting ring as described in claim 6, characterized in that, The main oil passage includes a main oil passage spiral structure, which is intertwined with the auxiliary oil passage spiral structure to form a multi-spiral structure. The cross-section of the main oil passage spiral structure includes two endpoints, and the line connecting the two endpoints is the dividing line between the inner and outer sides of the cross-section. The boundary line of the cross-section protrudes to the inner and outer sides.

9. A cooling method for an oil collecting ring, characterized in that, Using the oil collecting ring as described in any one of claims 1 to 8, the fuel in the secondary oil passage flows spirally along the spiral structure of the secondary oil passage and exchanges heat with the fuel in the main oil passage and the body of the oil collecting ring, so as to improve the temperature uniformity of the oil passage of the oil collecting ring.

10. The oil collecting ring cooling method as described in claim 9, characterized in that, The oil collecting ring includes a first auxiliary oil passage and a second auxiliary oil passage. The auxiliary oil passage spiral structures of the first auxiliary oil passage and the second auxiliary oil passage are intertwined. The fuel in the first auxiliary oil passage flows in the opposite direction to the fuel in the second auxiliary oil passage.

11. A fuel nozzle, characterized in that, Includes the oil collecting ring as described in any one of claims 1 to 8.

12. A combustion chamber, characterized in that, Includes the fuel nozzle as described in claim 11.

13. A turbine engine, characterized in that, Includes the combustion chamber as described in claim 12.

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