CN116792780A - Oil collecting ring and cooling method thereof, fuel nozzle, combustion chamber and turbine engine - Google Patents

Abstract

The application provides an oil collecting ring, an oil collecting ring cooling method, a fuel nozzle, a combustion chamber and a turbine engine, which can effectively solve the problem of fuel coking of an oil way of the oil collecting ring. The turbine engine includes the combustion chamber including the fuel nozzle including an oil catcher ring. The main oil path channel is used for a main combustion stage, the auxiliary oil path channel is used for a precombustion stage, the auxiliary oil path channel comprises an auxiliary oil path spiral structure, the axis of the auxiliary oil path spiral structure at least partially surrounds the axis of the oil collecting ring, and the auxiliary oil path spiral structure is wound around the main oil path channel. The oil collecting ring is adopted in the oil collecting ring cooling method, the fuel oil in the auxiliary oil path channel flows along the spiral structure of the auxiliary oil path, and exchanges heat with the fuel oil in the main oil path channel and the body of the oil collecting ring, so that the temperature uniformity of an oil path of the oil collecting ring is improved.

Description

Oil collecting ring and cooling method thereof, fuel nozzle, combustion chamber and turbine engine

Technical Field

The application relates to the technical field of turbine engines, in particular to an oil collecting ring, an oil collecting ring cooling method, a fuel nozzle, a combustion chamber and a turbine engine.

Background

In the field of aeroengines, with increasingly strict environmental protection requirements, pollution emission limits of civil aeroengines are also increasingly severe, and modern civil aeroengines widely adopt low-emission combustion technology to meet low-emission requirements.

Among the low-emission combustion technologies, the lean low-emission combustion technology is a very promising low-emission technology in terms of reduction of emissions with maximum potential. Lean oil low emission technology generally needs to adopt a graded fuel nozzle, the nozzle is divided into a precombustion stage and a main combustion stage, oil is supplied to a secondary oil circuit which is only positioned in the precombustion stage under a small working condition, and oil is supplied to the secondary oil circuit in the precombustion stage and a main oil circuit in the main combustion stage under a large working condition.

However, the staged fuel nozzle has a significant problem that fuel coking is easy to occur, thereby reducing the flow area of a fuel pipeline, even blocking the nozzle when serious, affecting the fuel atomization effect and the service life of the nozzle, resulting in deterioration of the combustion efficiency, emission and outlet temperature distribution of a combustion chamber, increase of fuel consumption of an engine and reduction of power performance.

In lean low emission combustion technology, the problem of staged nozzle fuel coking is becoming increasingly important as a point that must be overcome. The main reason for the fuel coking of the graded fuel nozzle is that the main oil way is not supplied with oil under the small working condition, wherein the residual fuel does not flow, is heated by high-temperature air or gas radiation, is extremely easy to produce coking, and the auxiliary oil way has less fuel flow and poor heat exchange effect under the large working condition, and the temperature of the oil Lu Yichao is low. The oil collecting ring positioned at the nozzle head is more prone to over-temperature of an oil way, so that fuel oil in the oil collecting ring is coked.

In order to solve the problem of overtemperature of an oil way in the oil collecting ring, two concentric annular oil ways, namely a main oil way and an auxiliary oil way, are arranged in the oil collecting ring so as to play a certain role in cooling the main oil way through heat exchange between the main oil way and the auxiliary oil way, but the inventor finds that the cooling effect of the scheme is limited in the process of realizing the application, the problem of overtemperature still exists at the local position of the oil way, and the coking of fuel oil in the oil collecting ring still can be caused.

It should be noted that the information disclosed in the above background section is only for enhancing understanding of the background of the present disclosure and thus may include information that does not constitute prior art known to those of ordinary skill in the art.

Disclosure of Invention

The application aims to provide an oil collecting ring which can effectively solve the problem of fuel coking of an oil way of the oil collecting ring.

The oil collecting ring is used for a fuel nozzle, a main oil path channel and an auxiliary oil path channel are arranged in the oil collecting ring, the main oil path channel is used for a main combustion stage, the auxiliary oil path channel is used for a precombustion stage, the auxiliary oil path channel comprises an auxiliary oil path spiral structure, the axis of the auxiliary oil path spiral structure at least partially surrounds the axis of the oil collecting ring, and the auxiliary oil path spiral structure is wound around the main oil path channel.

In one or more embodiments of the oil collecting ring, the main oil passage is divided in a circumferential direction of the oil collecting ring to form two independent oil dividing passages.

In one or more embodiments of the oil collection ring, the main oil passage includes a partial annular structure located inside the auxiliary oil passage spiral structure.

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 multiple spiral structure.

In one or more embodiments of the oil collection ring, the primary oil way helical structure and the secondary oil way helical structure have profiles that are opposite and shape-matched.

In one or more embodiments of the oil collection ring, the main oil passage includes a main combustion stage nozzle extending from a gap of the auxiliary oil passage spiral structure.

In one or more embodiments of the oil collecting ring, the oil collecting ring includes a plurality of the auxiliary oil passage, and each of the auxiliary oil passage spiral structures of the plurality of auxiliary oil passage is wound with each other to form a multiple spiral structure.

In one or more embodiments of the oil collecting ring, the oil collecting ring is a 3D print.

In one or more embodiments of the oil collecting ring, the cross section of the secondary oil passage spiral structure includes two end points, a connecting line of the two end points is a boundary line between an inner side and an outer side of the cross section, and the boundary line of the cross section protrudes toward the inner side and the outer side.

In one or more embodiments of the oil collecting ring, the main oil path comprises a main oil path spiral structure, the main oil path spiral structure and the auxiliary oil path spiral structure are mutually wound to form a multiple spiral structure, the cross section of the main oil path spiral structure comprises two end points, the connecting line of the two end points is a boundary line between the inner side and the outer side of the cross section, and the boundary line of the cross section protrudes towards the inner side and the outer side.

The application further aims to provide an oil collecting ring cooling method which can effectively solve the problem of fuel coking of an oil way of the oil collecting ring.

In order to achieve the purpose, the oil collecting ring cooling method is adopted, and fuel in the auxiliary oil path channel flows spirally along the auxiliary oil path spiral structure and exchanges heat with the fuel in the main oil path channel and the oil collecting ring body so as to improve the temperature uniformity of an oil path of the oil collecting ring.

In one or more embodiments of the oil-collecting ring cooling method, 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, and the fuel in the first auxiliary oil passage and the fuel in the second auxiliary oil passage flow in opposite directions.

According to the oil collecting ring and the oil collecting ring cooling method, the spiral structure wound around the main oil path channel is arranged on the auxiliary oil path channel, so that the heat exchange area between the main oil path channel and the auxiliary oil path channel can be increased, the fuel in the main oil path channel and the fuel in the auxiliary oil path channel can exchange heat fully and uniformly, the fuel with a lower temperature can play a role in cooling the fuel with a higher temperature, in addition, the spiral structure is arranged on the oil path channel because the surface of the body of the oil collecting ring is different from the heat exchange condition of the outside, the fuel can exchange heat with different parts of the body of the oil collecting ring repeatedly in the flowing process along the spiral structure, the temperature uniformity of the oil path in the oil collecting ring can be improved, the cooling effect is improved, the fuel coking caused by the overtemperature of the oil path in the oil collecting ring can be effectively avoided, the fuel atomizing effect can be ensured, the service life of a fuel nozzle is prolonged, the combustion efficiency of a combustion chamber and the performance of a turbine engine are improved, and the oil collecting ring is small in volume and compact in structure.

The application further aims to provide a fuel nozzle which can effectively solve the problem of fuel coking of an oil collecting ring oil way of the fuel nozzle.

The fuel nozzle for achieving the object comprises the oil collecting ring.

It is still another object of the present application to provide a combustion chamber that can effectively solve the problem of fuel coking in the oil gallery of the oil catcher of the fuel nozzle.

The combustion chamber for achieving the object comprises the fuel nozzle.

It is still another object of the present application to provide a turbine engine that effectively solves the problem of fuel coking in the oil gallery of the oil catcher ring of the fuel nozzle.

A turbine engine for achieving the object comprises a combustion chamber as described above.

The turbine engine, the combustion chamber and the fuel nozzle can effectively avoid overtemperature of an oil way in the oil collecting ring and coking of fuel oil by adopting the oil collecting ring, thereby ensuring the fuel atomization effect, prolonging the service life of the fuel nozzle and improving the combustion efficiency of the combustion chamber and the performance of the turbine engine.

Drawings

The above and other features, properties and advantages of the present application will become more apparent from the following description in conjunction with the accompanying drawings and embodiments, in which:

FIG. 1 is a schematic illustration of a combustion chamber according to one or more embodiments.

FIG. 2 is a schematic illustration of a fuel nozzle according to one or more embodiments.

Fig. 3 is a schematic view of the oil collector ring main oil passage and the auxiliary oil passage according to one embodiment.

Fig. 4 is an exploded view of fig. 3.

Fig. 5 is a schematic view of section A-A of fig. 3.

Fig. 6 is a schematic view of a main oil passage and a sub oil passage of an oil collecting ring according to another embodiment.

Fig. 7 is an exploded view of fig. 6.

Fig. 8 is a schematic view of section B-B of fig. 6.

Detailed Description

The following discloses a number of different embodiments or examples of implementing the subject technology. Specific examples of components and arrangements are described below for purposes of simplifying the disclosure, and of course, these are merely examples and are not intended to limit the scope of the application. It is noted that the drawings are by way of example only, are not drawn to scale, and should not be construed to limit the true scope of the application. It should be noted that the same or similar reference numerals indicate the same or similar items in the following drawings, and thus, once an item is defined in one drawing, no further discussion thereof is necessary in the following drawings. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.

A turbine engine (not shown) in accordance with one or more embodiments of the application includes a combustion chamber 100 as shown in fig. 1. The combustion chamber 100 mainly consists of a fuel nozzle 5, a flame tube 7 and a casing 9. The air 1 at the outlet of the high-pressure compressor enters the combustion chamber 100 and is divided into 3 streams, wherein the air comprises outer ring cavity air 2, head air inlet 3 and inner ring cavity air 4, the head air inlet 3 is mixed with fuel oil sprayed out by the fuel oil nozzle 5 and then combusted in the flame tube 7, and the generated high-temperature fuel gas flows downstream, so that the turbine is driven to do work. The air 1 at the outlet of the high-pressure compressor and the high-temperature fuel gas in the flame tube 7 heat-exchange through radiation and convection, and heat the fuel nozzle 5.

In the description of the present application, it is noted that the terms "upstream" and "downstream" refer to the relative directions with respect to the flow of fluid in the fluid channel. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

Referring to fig. 2, the fuel nozzle 5 includes a fuel pipe 10, a nozzle housing 14, a nozzle mount 17, and the like. The nozzle mount 17 is adapted to be connected to the casing 9 and provides a fuel inlet (not shown). The oil pipe 10 is fluidly connected to a fuel inlet of the nozzle mount 17 for delivering fuel to the nozzle head 50 for ejection through the pre-combustion stage nozzle 11 and the main combustion stage nozzle orifice 123. The nozzle housing 14 is located outside the oil pipe 10 with a gap between the nozzle housing 14 and the oil pipe 10, and the nozzle housing 14 and the oil pipe 10 are separated at a part of positions so that the nozzle housing 14 and the oil pipe 10 are not contacted, so that heat of the nozzle housing 14 is prevented from being transferred to the oil pipe 10 through heat conduction, and radiation and convection heat exchange between external hot gas and the oil pipe 10 can be isolated through the nozzle housing 14, and temperature rise of fuel oil in the oil pipe 10 is reduced.

In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or fluidly connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art in a specific case.

Referring to fig. 2 to 5, the oil pipe 10 includes a pre-combustion stage nozzle 11, an oil collecting ring 12, and an oil rod 13. The pre-combustion stage nozzle 11 and the oil collecting ring 12 are located at the nozzle head 50, wherein the pre-combustion stage nozzle 11 is located at the center of the nozzle head 50, and the oil collecting ring 12 surrounds the outer side of the pre-combustion stage nozzle 11. The oil collecting ring 12 includes a body 120, and a main oil passage 121 and a sub oil passage 122 provided in the body 120, the main oil passage 121 including a main combustion stage nozzle 123. The main oil passage 121 and the sub oil passage 122 are connected to the fuel inlet of the nozzle mount 17 through the oil rod 13, and the fuel flowing from the fuel inlet is divided into two passages, namely, a main oil passage and a sub oil passage, and the fuel of the main oil passage and the sub oil passage respectively flow along the main oil passage 121 and the sub oil passage 122 to supply the fuel to the main fuel stage nozzle 123 and the pre-combustion stage nozzle 11, respectively.

The plurality of main stage nozzle holes 123 are distributed along the circumferential direction of the oil collecting ring 12 and extend to the radially outer side of the body 120, and the nozzle housing 14 is provided with a plurality of outlet holes 141 in one-to-one correspondence with the main stage nozzle holes 123 so that the fuel ejected from the main stage nozzle holes 123 is ejected from the nozzle housing 14 through the outlet holes 141.

In the process that fuel flows from the fuel inlet of the nozzle mounting seat 17 to the nozzle head 50, the temperature gradually rises under the radiation heat exchange effect of the air 1 at the outlet of the high-pressure compressor, and the radiation heat exchange effect of the high-temperature fuel gas in the flame tube 7 mainly acts on the nozzle head 50, so that the fuel temperature of the nozzle head 50 is higher, the auxiliary oil channel 122 is required to be arranged in the oil collecting ring 12, and the cooler fuel in the flow path with higher flow rate and lower flow rate plays a role in cooling the hotter fuel in the flow path with lower flow rate by virtue of heat exchange between the fuel in the main oil channel 121 and the fuel in the auxiliary oil channel 122 and the body 120 of the oil collecting ring 12, thereby reducing the highest temperature of the fuel in the oil collecting ring 12 and avoiding fuel coking caused by the overtemperature of an oil path.

Specifically, under the small working condition, the main fuel stage nozzle 123 does not spray fuel, the fuel remaining in the main oil path channel 121 does not flow, the fuel is heated for a longer time, the temperature rise is larger, the temperature is higher, the fuel still flows in the auxiliary oil path channel 122, the heated time is shorter, the temperature rise is less, and the temperature is lower in the fuel flowing process, so that the fuel in the main oil path channel 121 can be cooled by the fuel in the auxiliary oil path channel 122; under large working conditions, the fuel flow in the main oil passage 121 is large, the heat exchange capacity is strong, the temperature rise in the flowing process is small, the temperature is low, the fuel flow in the auxiliary oil passage 122 is small, the heat exchange capacity is poor, the temperature rise is large, and the temperature is high, so that the fuel in the auxiliary oil passage 122 can be cooled through the fuel in the main oil passage 121.

Referring to fig. 3 and 4, alternatively, the main oil passage 121 is divided in the circumferential direction of the oil collecting ring 12 to form two independent oil dividing passages 1210, each oil dividing passage 1210 including one oil inlet section 1211 and one surrounding section 1212. An oil inlet section 1211 is located upstream of the surrounding section 1212 for supplying oil to the surrounding section 1212, and the main combustion stage nozzle 123 is connected to the surrounding section 1212. The surrounding segment 1212 has a partial annular structure extending in a direction parallel to the circumferential direction of the oil collecting ring 12, that is, the surrounding segment 1212 partially surrounds the axis 126 of the oil collecting ring 12, and the surrounding segments 1212 of the two oil-dividing passages 1210 are opposed in the radial direction of the oil collecting ring 12 and enclose a structure close to a full ring.

Thus, the main oil passage 121 is divided into two independent oil-dividing passages 1210, so that the circulation length of the fuel in the main oil passage 121 in the oil collecting ring 12 can be shortened, the heating time of the fuel is reduced, the temperature rise of the fuel in the main oil passage 121 is reduced, the risk of coking of the fuel in the main oil passage 121 is further reduced, and the heat exchange capability of the fuel in the main oil passage 121 is improved under a large working condition.

Alternatively, the two oil-dividing passages 1210 are symmetrical in structure, and the surrounding section 1212 of each oil-dividing passage 1210 approximates a semi-annular shape, i.e., the angle of each surrounding section 1212 in the circumferential direction of the oil collecting ring 12 approximates 180 °, so that the structure of the main oil passage 121 can be simplified.

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

In still another embodiment, the main oil passage 121 is one complete oil passage, i.e., the main oil passage 121 includes only one oil inlet section 1211 and one surrounding section 1212, and the surrounding section 1212 is nearly annular, i.e., the angle in the circumferential direction of the oil collecting ring 12 is nearly 360 °, so that the structure of the main oil passage 121 can be simplified.

Referring to fig. 3 to 5, the auxiliary oil passage 122 includes two sub-oil passage passages, namely, a first auxiliary oil passage 124 and a second auxiliary oil passage 125, respectively, the first auxiliary oil passage 124 includes a first auxiliary oil passage spiral structure 1241, the second auxiliary oil passage 125 includes a second auxiliary oil passage spiral structure 1251, a first axis 1244 of the first auxiliary oil passage spiral structure 1241 and a second axis 1254 of the second auxiliary oil passage spiral structure 1251 coincide and at least partially surround the axis 126 of the oil collecting ring 12, i.e., the first auxiliary oil passage spiral structure 1241 and the second auxiliary oil passage spiral structure 1251 extend in a direction parallel to the circumferential direction of the oil collecting ring 12 while being spiral.

The first auxiliary oil circuit spiral structure 1241 and the second auxiliary oil circuit spiral structure 1251 are mutually wound to form a double-spiral structure, and the double-spiral structure is wound around the surrounding section 1212 of the main oil circuit channel 121, so that the heat exchange area between the main oil circuit channel 121 and the auxiliary oil circuit channel 122 can be greatly increased in a limited space, the cooling effect is improved, and fuel coking caused by oil circuit overtemperature in the oil collecting ring 12 is effectively avoided.

In addition, the surrounding section 1212 of the main oil path 121 is located inside the double-spiral structure of the auxiliary oil path 122, so that heat exchange between each part of the cross section of the main oil path 121 in the circumferential direction and the auxiliary oil path 122 is uniform, the temperature of fuel in the main oil path 121 is uniform, local overtemperature of fuel in the main oil path 121 is avoided, or the main oil path 121 provides more uniform cooling effect on the auxiliary oil path 122, and the internal space of the double-spiral structure can be fully utilized, and the double-spiral structure has small volume and compact structure.

Optionally, the cross section of the surrounding 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, i.e. 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 heat exchange uniformity in the circumferential direction 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.

In other embodiments, the auxiliary 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 auxiliary oil passage 122, improving the cooling effect and the temperature uniformity of the fuel within the main oil passage 121. In still another embodiment, the auxiliary oil passage 122 is only one oil passage, so that the structure of the auxiliary oil passage 122 can be simplified.

In the description of the present application, it should be noted that, the terms "first," "second," and the like are used for defining the components, and are merely for convenience in distinguishing the corresponding components, and unless otherwise stated, the terms have no special meaning, and therefore should not be construed as limiting the scope of the present application.

With continued reference to fig. 3 to 5, alternatively, the plurality of primary fuel nozzles 123 extend out of the double spiral structure of the secondary oil passage 122 from the gap of the double spiral structure, that is, the secondary oil passage 122 is located at two radial sides of the primary fuel nozzle 123, so that the fuel in the secondary oil passage 122 and the fuel in the primary fuel nozzle 123 can be subjected to sufficient heat exchange to sufficiently cool the fuel in the primary fuel nozzle 123, so that the fuel in the primary fuel nozzle 123 is prevented from coking, and the structure is simple and easy to form. In another embodiment, not shown, the main fuel nozzle 123 extends through the body portion of the double helix structure, i.e., the main fuel nozzle 123 extends through the secondary fuel passage 122, but the fuel in the main fuel nozzle 123 is not in communication with the fuel in the secondary fuel passage 122, so that the fuel in the secondary fuel passage 122 and the fuel in the main fuel nozzle 123 can exchange heat sufficiently.

The first sub oil passage 124 further includes a first oil inlet passage 1242 and a first oil outlet passage 1243, which are connected to both ends of the first sub oil passage spiral structure 1241, respectively. The first oil intake passage 1242 is for inputting fuel into the first sub-gallery spiral structure 1241. The first oil outlet passage 1243 is connected to the pre-combustion nozzle 11, and is used for guiding the fuel oil flowing out of the first auxiliary oil path spiral structure 1241 to the pre-combustion nozzle 11.

The second sub oil passage 125 further includes a second oil inlet passage 1252 and a second oil outlet passage 1253, which are connected to both ends of the second sub oil passage spiral structure 1251, respectively. The second oil intake passage 1252 is for inputting fuel into the second sub-oil passage spiral structure 1251. The second oil outlet passage 1253 is connected to the pre-combustion nozzle 11, and is used for guiding the fuel oil flowing out of the second auxiliary oil path spiral structure 1251 to the pre-combustion nozzle 11.

Alternatively, the fuel flow direction in the first auxiliary fuel path spiral structure 1241 and the second auxiliary fuel path spiral structure 1251 is opposite, for example, according to the orientation shown in fig. 3, the fuel in the first auxiliary fuel path spiral structure 1241 flows around the axis 126 of the oil collecting ring 12 in the clockwise direction while spirally flowing, and the fuel in the second auxiliary fuel path spiral structure 1251 flows around the axis 126 of the oil collecting ring 12 in the counterclockwise direction while spirally flowing, so as to obtain a better cooling effect.

Specifically, under the small working condition, as the fuel in the first auxiliary oil way spiral structure 1241 and the second auxiliary oil way spiral structure 1251 cool the fuel in the main oil way channel 121 in the flowing process and are radiated by external hot gas, the nozzle housing 14 and the like, the temperature is gradually increased, the heat exchange capacity is gradually reduced, and the fuel flow directions in the first auxiliary oil way spiral structure 1241 and the second auxiliary oil way spiral structure 1251 are set to be opposite, the part with poor fuel heat exchange capacity of the first auxiliary oil way spiral structure 1241 is adjacent to the part with strong fuel heat exchange capacity of the second auxiliary oil way spiral structure 1251, and heat exchange can be performed between the fuel in the first auxiliary oil way spiral structure 1241 and the fuel in the second auxiliary oil way spiral structure 1251, so that the overall heat exchange capacity of the double-spiral structure formed by the first auxiliary oil way spiral structure 1241 and the second auxiliary oil way spiral structure 1251 is balanced in the circumferential direction of the oil collecting ring 12, and local overtemperature of the fuel in the main oil way channel 121 is avoided; under the large working condition, the fuel oil in the first auxiliary oil way spiral structure 1241 and the second auxiliary oil way spiral structure 1251 is subjected to the cooling effect of the fuel oil in the main oil way channel 121 and the external heat radiation, and the fuel oil flow directions in the first auxiliary oil way spiral structure 1241 and the second auxiliary oil way spiral structure 1251 are set to be opposite, so that heat exchange can occur between the fuel oil in the first auxiliary oil way spiral structure 1241 and the fuel oil in the second auxiliary oil way spiral structure 1251, and the temperature of the fuel oil in the first auxiliary oil way spiral structure 1241 and the second auxiliary oil way spiral structure 1251 is balanced in the circumferential direction of the oil collecting ring 12, thereby avoiding local overtemperature of the fuel oil in the auxiliary oil way channel 122.

Referring to fig. 6 to 8, in another embodiment, the surrounding section 1212 of the main oil passage 121 includes a main oil passage spiral structure 1213, and the main oil passage spiral structure 1213 and the first and second auxiliary oil passage spiral structures 1241 and 1251 are wound with each other to form a multiple spiral structure, so that the heat exchange area between the main oil passage 121 and the auxiliary oil passage 122 can be greatly increased in a limited space, and the cooling effect is improved, so as to effectively avoid fuel coking caused by oil passage overtemperature in the oil collecting ring 12. The main oil passage spiral structure 1213 may be the same as or different from the fuel flow direction in the first sub oil passage spiral structure 1241 and the second sub oil passage spiral structure 1251.

The main oil passage spiral structure 1213 has a matching profile with the first and second sub oil passage spiral structures 1241, 1251, for example, the first side 1214 of the main oil passage spiral structure 1213 is located opposite and shape-matched to the first surface 1249 of the first sub oil passage spiral structure 1241, and the second side 1215 of the main oil passage spiral structure 1213 is located opposite and shape-matched to the second surface 1259 of the second sub oil passage spiral structure 1251. Therefore, the main oil passage 121 and the auxiliary oil passage 122 have larger heat exchange area and are closer in distance, so that the cooling effect can be improved, and fuel coking of fuel in the main oil passage 121 or the auxiliary oil passage 122 is effectively avoided, and the device is small in volume and compact in structure.

The main combustion stage nozzle 123 protrudes 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 secondary oil gallery spiral structure 1241 further includes a third surface 1240 and the second secondary oil gallery spiral structure 1251 further includes a fourth surface 1250 with the primary fuel stage nozzle 123 being located between the third surface 1240 and the fourth surface 1250, the third surface 1240 and the fourth surface 1250 being parallel or approximately parallel, respectively, to a centerline of the primary fuel stage nozzle 123 and proximate to the primary fuel stage nozzle 123. Therefore, the auxiliary oil passage 122 and the main combustion stage nozzle 123 have larger heat exchange area and are closer in distance, so that the cooling effect can be improved, the occurrence of fuel coking in the main combustion stage nozzle 123 is effectively avoided, and the main combustion stage nozzle 123 is small in volume and compact in structure.

Thus, according to the oil collecting ring 12 and the oil collecting ring cooling method according to one or more embodiments of the present application, by arranging the spiral structure wound around the main oil path 121 in the auxiliary oil path 122, the heat exchange area between the main oil path 121 and the auxiliary oil path 122 can be increased, so that the fuel in the main oil path 121 and the fuel in the auxiliary oil path 122 exchange heat sufficiently and uniformly, the fuel with a relatively high temperature can be cooled by the fuel with a relatively low temperature, in addition, since the surface of the body 120 of the oil collecting ring 12 is different from the heat exchange condition of the outside, by arranging the spiral structure in the oil path, the fuel can exchange heat repeatedly between the fuel and different parts of the body 120 of the oil collecting ring 12 in the process of flowing along the spiral structure, the temperature uniformity of the oil path in the oil collecting ring 12 can be improved, the cooling effect can be improved, the fuel coking caused by the super-temperature of the oil path in the oil collecting ring 12 can be effectively avoided, the atomization effect can be ensured, the service life of the fuel nozzle 5 can be prolonged, the combustion efficiency of the combustion chamber 100 and the performance of the turbine engine can be improved, and the oil collecting ring 12 can be compact.

The oil collecting ring 12 and the main oil path passage 121 (except for the main combustion stage nozzle 12) and the sub oil path passage 122 inside thereof may be integrally formed by 3D printing for easy manufacture, and the main combustion stage nozzle 123 may be processed by processes such as spark drilling or laser drilling to secure dimensional accuracy of the main combustion stage nozzle 123.

Referring to fig. 5, a first cross section of first sub-oil passage spiral structure 1241, i.e., a cross section perpendicular to first axis 1244 of first sub-oil passage spiral structure 1241, includes a first boundary line 1246 and two first end points 1247. The first connecting line 1248 connecting the two first end points 1247 is a boundary between the inner side and the outer side of the first cross section, wherein the inner side is a side close to the first axis 1244 of the first sub-oil passage spiral structure 1241, and the outer side is a side far from the first axis 1244 of the first sub-oil passage spiral structure 1241. The first boundary line 1246 is formed in a convex shape toward the inner side and the outer side of the first connecting line 1248, for example, the first boundary line 1246 is formed in an olive-like shape, so that the first auxiliary oil path spiral structure 1241 is convenient to be formed through 3D printing, and the forming quality is improved.

Similarly, the second cross section of the second sub-oil passage spiral structure 1251 includes a second boundary line 1256 and two second end points 1257, the second boundary line 1256 protruding inward and outward with respect to a second connection line 1258 connecting the two second end points 1257, so as to facilitate molding by 3D printing, improving molding quality.

Similarly, in the embodiment shown in fig. 6 to 8, boundary lines of the cross sections of the main oil passage spiral structure 1213, the first sub oil passage spiral structure 1241, and the second sub oil passage spiral structure 1251 are respectively protruded inward and outward with respect to the corresponding lines, so as to facilitate molding by 3D printing, and improve molding quality.

Referring to fig. 1 and 2, the fuel nozzle 5 further includes a splash guard 15, where the splash guard 15 is located downstream of the oil collecting ring 12 and is used to isolate heat radiation of high-temperature fuel gas in the flame tube 7 to the nozzle head 50, so as to further reduce temperature rise of fuel in the oil collecting ring 12 and avoid coking of fuel in an oil path in the oil collecting ring 12. The main fuel nozzle 123 of oil collection ring 12 is directed to spray away from splash plate 15.

In other embodiments, where splash plate 15 is not disposed downstream of oil collection ring 12, primary fuel nozzle 123 of oil collection ring 12 may be sprayed radially, axially, or diagonally between the radial and axial directions of oil collection ring 12.

By adopting the oil collecting ring 12, the turbine engine, the combustion chamber 100 and the fuel nozzle 5 can effectively avoid the overtemperature of an oil way in the oil collecting ring 12 and avoid fuel coking, thereby ensuring the fuel atomization effect, prolonging the service life of the fuel nozzle 5 and improving the combustion efficiency of the combustion chamber 100 and the performance of the turbine engine.

While the application has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the application, as will occur to those skilled in the art, without departing from the spirit and scope of the application. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present application fall within the protection scope defined by the claims of the present application.

Claims (15)

1. 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 oil collecting ring, and the auxiliary oil circuit spiral structure is wound around the main oil circuit channel.

2. The oil collecting ring as set forth in claim 1, wherein said main oil passage is divided in a circumferential direction of said oil collecting ring to form two independent oil-dividing passages.

3. The oil collecting ring as set forth in claim 1, wherein said main oil passage includes a partial annular structure located inside said auxiliary oil passage spiral structure.

4. The oil collecting ring as set forth in claim 1, wherein said main oil passage includes a main oil passage spiral structure, said main oil passage spiral structure and said auxiliary oil passage spiral structure being intertwined to form a multiple spiral structure.

5. The oil collecting ring as set forth in claim 4, wherein said main oil path helical structure and said auxiliary oil path helical structure have profiles which are opposite and form-matched.

6. The oil collecting ring as set forth in any one of claims 1 to 5, characterized in that said main oil passage includes a main combustion stage nozzle extending from a gap of said auxiliary oil spiral structure.

7. The oil collecting ring as set forth in any one of claims 1 to 5, wherein said oil collecting ring includes a plurality of said secondary oil passage, each of said secondary oil passage spiral structures of said plurality of secondary oil passage being intertwined to form a multiple spiral structure.

8. The oil collecting ring as claimed in any one of claims 1 to 5, characterized in that the oil collecting ring is a 3D print.

9. The oil collecting ring as set forth in claim 8, wherein a cross section of said secondary oil passage spiral structure includes two end points, a line connecting said two end points being a boundary line between an inner side and an outer side of said cross section, said boundary line of said cross section protruding toward said inner side and said outer side.

10. The oil collecting ring as set forth in claim 8, wherein said main oil passage includes a main oil passage spiral structure, said main oil passage spiral structure and said sub oil passage spiral structure being intertwined to form a multiple spiral structure, a cross section of said main oil passage spiral structure including two end points, a line connecting said two end points being a boundary between an inner side and an outer side of said cross section, said boundary between said cross section being convex toward said inner side and said outer side.

11. A method for cooling an oil collecting ring, characterized in that the oil collecting ring according to any one of claims 1 to 10 is adopted, and the fuel in the secondary oil passage flows spirally along the secondary oil passage spiral structure and exchanges heat with the fuel in the main oil passage and the body of the oil collecting ring to improve the temperature uniformity of the oil passage of the oil collecting ring.

12. The oil collecting ring cooling method according to claim 11, wherein the oil collecting ring includes a first sub oil passage and a second sub oil passage, the sub oil passage spiral structures of the first sub oil passage and the second sub oil passage are intertwined with each other, and the fuel in the first sub oil passage and the fuel in the second sub oil passage flow in opposite directions.

13. A fuel nozzle comprising an oil collecting ring according to any one of claims 1 to 10.

14. A combustion chamber comprising the fuel nozzle of claim 13.

15. A turbine engine comprising a combustion chamber as claimed in claim 14.