Shunting ring anti-icing device for aero-engine and aero-engine

Abstract

The invention relates to a shunting ring anti-icing device for an aero-engine, comprising: a shunting ring body, the shunting ring body comprising a shunting ring front portion, a shunting ring rear portion and a first matching portion, the shunting ring rear portion comprising a first flange portion; the stator casing is positioned in the radial inner part of the shunt ring body and comprises a second flange part and a third flange part, and a second matching part is formed at the radial outer end of the second flange part; the oil collecting cavity is defined by the flow dividing ring body and the stator casing in a sealed mode, the first matching part is matched with the second matching part in a sealed mode, and the first flange part is matched with the third flange part in a sealed mode; and the oil guide pipe allows the lubricating oil to enter the oil collecting cavity and allows the lubricating oil circularly passing through the oil collecting cavity to leave the oil collecting cavity. The anti-icing structure of the engine is optimized, the reliability of the anti-icing device is improved, and the performance and the heat efficiency of the engine are improved. The invention further relates to an aero-engine comprising the shunt ring anti-icing device.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft engines and relates to a splitter ring anti-icing device for aircraft engines, in particular to an engine fan / boost stage splitter ring anti-icing structure. In addition, the present invention also relates to an aircraft engine comprising such a splitter ring anti-icing device. Background Art

[0002] When an aircraft such as an airplane encounters colder clouds during a flight mission or works on the ground with icing conditions, ice will form on certain surfaces of the engine inlet (such as the head of the splitter ring). If the ice is not cleaned in time, the flow path shape of the iced parts will change, thereby affecting the aerodynamic performance of the iced parts. In more serious cases, if the ice in the iced parts falls off, it may be sucked into the core engine, thereby damaging the engine rotor, or being drawn into the fan blades, thereby hitting the internal structure of the engine casing and causing damage to it.

[0003] The diverter ring is an annular device located at the outlet of the engine fan blades and the inlet of the boost stage to separate the inner and outer flow channels of the turbofan engine. Arranging an anti-icing device at this position can effectively improve the icing of the diverter ring, thereby reducing the interference of ice crystals on the flow field and the risk of ice crystals being inhaled into the core engine.

[0004] The anti-icing structure of the prior art is to introduce the hot air in the high-pressure compressor into the splitter ring, and spray part of the hot air into the front of the first-stage stator guide vane of the inner duct, so as to achieve the purpose of anti-icing.

[0005] For example, in a utility model patent entitled “A diverter ring anti-icing structure” filed by the applicant of the present application on November 6, 2020 and published on July 13, 2021, a diverter ring anti-icing structure is disclosed. The diverter ring anti-icing structure includes a diverter ring, a casing, an anti-icing ring pipe and a plurality of air bleed pipes. The casing and the diverter ring cooperate to form a heating chamber and a hot melt chamber at the front end of the diverter ring. An impact hole is provided on the casing, and the impact hole connects the heating chamber and the hot melt chamber; one end of the air bleed pipe is connected to the anti-icing ring pipe, and the other end is connected to the heating chamber; wherein, high-temperature and high-pressure gas is introduced into the anti-icing ring pipe, flows into the hot melt chamber through a plurality of air bleed pipes, and then reaches the hot melt chamber through the impact hole.

[0006] This type of anti-icing design using engine hot air is widely used, has a relatively simple structure and high reliability. However, this anti-icing structure will have an adverse effect on the aerodynamic performance of the engine and reduce engine performance.

[0007] Therefore, there is an urgent need to optimize the structure of the split-ring anti-icing device for engines in the prior art, so as to provide an improved split-ring anti-icing device for aeroengines, which can overcome one or more drawbacks existing in the prior art. Summary of the Invention

[0008] The object of the present invention is to provide a split-ring anti-icing device for aeroengines, which can optimize the split-ring anti-icing structure, change the anti-icing heat source and anti-icing medium, improve the reliability of the anti-icing device, and reduce its weight and cost. Another object of the present invention is to reduce the influence on the internal aerodynamic performance and improve the engine performance.

[0009] According to one aspect of the present invention, there is provided a split-ring anti-icing device for aeroengines, which may include:

[0010] A split-ring body, which includes a split-ring front part, a split-ring rear part, and a first mating part located between the split-ring front part and the split-ring rear part. Among them, the split-ring rear part includes a first flange part extending radially inwards;

[0011] A stator casing, which is positioned radially inside the split-ring body and includes a second flange part and a third flange part. The radially outer end of the second flange part forms a second mating part extending continuously in the circumferential direction;

[0012] An oil sump, which is formed by being enclosed by the split-ring body and the stator casing. Among them, the first mating part and the second mating part are sealingly mated, and the first flange part and the third flange part are sealingly mated; and

[0013] An oil pipe, which allows the lubricating oil from the aeroengine to enter the oil sump and allows the lubricating oil circulating through the oil sump to leave the oil sump.

[0014] The split-ring anti-icing device according to the present invention optimizes the split-ring anti-icing structure for aeroengines, enabling it to use lubricating oil for split-ring anti-icing. In addition, compared with the engine anti-icing structure of the prior art, the split-ring anti-icing device according to the present invention cancels the air duct. Therefore, the air extraction amount required by the high-pressure compressor is reduced, the efficiency of the high-pressure compressor is improved, the internal structure of the engine is simplified, the reliability is improved, and the engine weight and cost are reduced. Further, compared with the engine anti-icing structure of the prior art, the function of injecting hot air from the split-ring into the core flow is cancelled, the influence of the anti-icing structure on the core flow aerodynamic performance is reduced, and the performance of the compression stage is improved.

[0015] According to the above aspects of the present invention, preferably, the shunt ring anti-icing device may further include a fastening device, wherein the oil guide pipe passes through the openings provided in the first flange portion and the third flange portion and is in fluid communication with the oil collecting cavity, and is fixed by means of the fastening device.

[0016] This arrangement allows the oil collecting cavity to form a sealed space, thereby ensuring that the lubricating oil circulates in the oil collecting cavity without leakage. In addition, by providing openings in the first flange portion and the third flange portion, the strength of the connection and fastening of the oil guide pipe can be ensured.

[0017] According to the above aspects of the present invention, preferably, the oil guide pipe may include a first oil guide pipe and a second oil guide pipe, wherein the first oil guide pipe allows the lubricating oil from the lubricating oil radiator to enter the oil collecting cavity, and the second oil guide pipe allows the lubricating oil to enter the bearing cavity from the oil collecting cavity.

[0018] Through this arrangement, the temperature of the lubricating oil entering the oil collecting cavity is maintained at a desired temperature without being too high, and the waste heat of the lubricating oil is recovered and utilized, improving the thermal efficiency of the engine. In addition, cooling substances such as ice crystals on the surface of the shunt ring can have a cooling effect on the lubricating oil, further reducing the temperature of the lubricating oil and improving the cooling effect of the lubricating oil on the bearing.

[0019] According to the above aspects of the present invention, in order to better control the flow rate of the lubricating oil and thus adjust the anti-icing effect of the anti-icing device according to the operating environment of the aircraft, preferably, a control valve and / or a control pump may be provided on the first oil guide pipe and / or the second oil guide pipe.

[0020] According to the above aspects of the present invention, in order to ensure that the lubricating oil does not leak to the outside, preferably, the shunt ring anti-icing device may further include a sealing device, wherein the sealing device may be arranged in the circumferential direction between the first mating portion and the second mating portion.

[0021] According to the above aspects of the present invention, preferably, the shunt ring anti-icing device may further include a flow disturbing device provided inside the oil collecting cavity.

[0022] This arrangement allows to improve the heat exchange efficiency between the lubricating oil in the oil collecting cavity and the anti-icing ring, thereby improving the de-icing efficiency, and can further reduce the temperature of the lubricating oil, thus improving the cooling effect of the lubricating oil on the bearing.

[0023] According to the above aspects of the present invention, preferably, the flow disturbing device may include a first group of baffles and a second group of baffles, and the first group of baffles and the second group of baffles are alternately arranged along the circumferential direction, wherein,

[0024] the first group of baffles extends backward in the axial direction from the front end of the oil collecting cavity, and a first group of gaps are formed between the free ends of the first group of baffles and the first flange portion, and wherein,

[0025] The second set of baffles extends forward in the axial direction from the rear end of the oil collecting chamber, and a second set of gaps are formed between the free ends of the second set of baffles and the second mating portion.

[0026] With this arrangement, the lubricating oil flows along a tortuous flow path in the oil collecting chamber, reducing the flow rate of the lubricating oil, increasing the heat exchange time, and making the heat exchange more sufficient. In addition, this arrangement increases the contact area between the lubricating oil and the flow dividing ring, improving the heat exchange efficiency.

[0027] According to the above aspect of the present invention, in order to make the flow rate more uniform and consistent, preferably, each of the first set of gaps and the second set of gaps may have an equal cross-sectional area.

[0028] According to the above aspect of the present invention, preferably, the flow disturbing device may include a third set of baffles and a fourth set of baffles, which are alternately arranged along the circumferential direction, wherein,

[0029] the third set of baffles extends inward in the radial direction from the flow dividing ring body, and a third set of gaps are formed between the free ends of the third set of baffles and the stator casing, and wherein,

[0030] the fourth set of baffles extends outward in the radial direction from the stator casing, and a fourth set of gaps are formed between the free ends of the fourth set of baffles and the flow dividing ring body.

[0031] Similarly, this arrangement can make the heat exchange between the lubricating oil and the flow dividing ring more sufficient and improve the heat dissipation efficiency.

[0032] According to another aspect of the present invention, an aeroengine is provided, which may include:

[0033] the flow dividing ring anti-icing device according to the above aspect,

[0034] a fan, which is positioned upstream of the flow dividing ring anti-icing device;

[0035] an outlet guide vane, which is positioned in the outer bypass duct and downstream of the flow dividing ring anti-icing device, and

[0036] a booster stage, which is positioned in the core duct and downstream of the flow dividing ring anti-icing device.

[0037] In summary, the beneficial technical effects of the flow dividing ring anti-icing device according to the present invention may include but are not limited to the following aspects:

[0038] 1) The flow dividing ring anti-icing device of the present invention optimizes the anti-icing bleed air structure, enabling it to use lubricating oil for flow dividing ring and engine anti-icing, and recycling the waste heat of the lubricating oil, improving the thermal efficiency of the engine;

[0039] 2) Ice crystals that may exist on the surface of the flow splitting ring or the ram air flow have a cooling effect on the lubricating oil. Thus, through the heat exchange between the flow splitting ring and the lubricating oil, the temperature of the lubricating oil is further reduced, and the cooling effect of the lubricating oil on the bearing is improved.

[0040] 3) Compared with the ice protection structure of the flow splitting ring in the prior art, the air intake pipe is cancelled, the required air intake of the high-pressure compressor is reduced, the efficiency of the high-pressure compressor is improved, the internal structure of the aero-engine is simplified, the reliability is improved, and the weight and cost of the aero-engine are reduced.

[0041] 4) Compared with the ice protection structure in the prior art, the function of injecting hot air from the flow splitting ring into the core flow is cancelled, the influence of the ice protection structure of the flow splitting ring on the core aerodynamic performance is reduced, and the performance of the booster stage is improved.

[0042] Therefore, the ice protection device of the flow splitting ring according to the present invention can meet the usage requirements, overcomes the disadvantages of the prior art and achieves the predetermined purpose. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to further clearly describe the ice protection device of the flow splitting ring according to the present invention, the present invention will be described in detail below in conjunction with the drawings and specific embodiments. In the drawings:

[0044] Figure 1 A schematic diagram of the fan / booster component of an aero-engine according to a non-limiting embodiment of the present invention is shown;

[0045] Figure 2 A schematic diagram of a part of the ice protection device of the flow splitting ring according to a non-limiting embodiment of the present invention as observed in the circumferential direction is shown;

[0046] Figure 3 A schematic diagram of another part of the ice protection device of the flow splitting ring according to a non-limiting embodiment of the present invention as observed in the circumferential direction is shown;

[0047] Figure 4 A schematic flow path of the lubricating oil in the ice protection device of the flow splitting ring according to a non-limiting embodiment of the present invention is shown;

[0048] Figure 5 A schematic front view of the ice protection device of the flow splitting ring according to a non-limiting embodiment of the present invention is shown;

[0049] Figure 6 A schematic diagram of the first set of baffles of the ice protection device of the flow splitting ring according to a non-limiting embodiment of the present invention is shown;

[0050] Figure 7 A schematic diagram of the second set of baffles of the ice protection device of the flow splitting ring according to a non-limiting embodiment of the present invention is shown;

[0051] Figure 8 Shows another schematic front view of the flow splitting ring anti-icing device according to a non-limiting embodiment of the present invention;

[0052] Figure 9 Shows a schematic diagram of the third group of baffles of the flow splitting ring anti-icing device according to a non-limiting embodiment of the present invention; and

[0053] Figure 10 Shows a schematic diagram of the fourth group of baffles of the flow splitting ring anti-icing device according to a non-limiting embodiment of the present invention.

[0054] The above-mentioned drawings are only schematic and are not drawn strictly to scale.

[0055] List of reference numerals in the drawings and embodiments:

[0056] 1000 - Engine, including:

[0057] 100 - Flow splitting ring anti-icing device, including:

[0058] 10 - Flow splitting ring body, including:

[0059] 11 - Front part of the flow splitting ring;

[0060] 12 - Rear part of the flow splitting ring;

[0061] 13 - First mating part;

[0062] 14 - First flange part;

[0063] 20 - Stator casing, including:

[0064] 21 - Second flange part;

[0065] 22 - Third flange part;

[0066] 23 - Second mating part;

[0067] 20A - Zero-stage stator casing;

[0068] 20B - First-stage stator casing;

[0069] 30 - Oil collecting chamber;

[0070] 40 - Oil guiding pipe, including:

[0071] 40A - Boss;

[0072] 41 - First oil guiding pipe;

[0073] 42 - Second oil guiding pipe;

[0074] 43 - Control valve;

[0075] 44 - Control pump;

[0076] 45 - Partition plate;

[0077] 50 - Fastening device;

[0078] 60 - Lubricating oil radiator;

[0079] 70 - Bearing chamber;

[0080] 80 - Sealing device;

[0081] 90 - Turbulence device;

[0082] 91 - First group of baffles;

[0083] 91A - First group of gaps;

[0084] 92 - Second group of baffles;

[0085] 92A - Second group of gaps;

[0086] 93 - Third group of baffles;

[0087] 93A - Third group of gaps;

[0088] 94 - Fourth group of baffles;

[0089] 94A - Fourth group of gaps;

[0090] 200 - Fan;

[0091] 300 - Outlet guide vane;

[0092] 400 - Boost stage;

[0093] 401 - Zero-stage stator blade;

[0094] 402 - First-stage rotor blade;

[0095] A - Axial direction;

[0096] C - Circumferential direction. Detailed implementation mode

[0097] It should be understood that unless explicitly stated to the contrary, the present invention can adopt various alternative orientations and step sequences. It should also be understood that the specific devices shown in the drawings and described in the specification are only exemplary embodiments of the inventive concept disclosed and defined herein. Thus, unless otherwise explicitly stated, the specific orientations, directions or other physical characteristics involved in the disclosed various embodiments should not be considered as limitations.

[0098] Figure 1Shows a schematic diagram of the fan / booster component of an aeroengine 1000 according to a non - limiting embodiment of the present invention.

[0099] As used herein, the fan / booster stage may refer to the front - stage low - pressure compression component of a turbofan engine. After the air flow passes through the fan, it is divided into two streams, which enter the outer and inner ducts respectively. The outer - duct air flow passes through the exit guide vanes and is discharged to the atmosphere at the outer - duct nozzle, while the inner - duct air flow enters the core engine through the booster stage.

[0100] As shown in the figure and as a non - limiting embodiment of the present invention, the aeroengine 1000 may include a splitter - ring anti - icing device 100, a fan 200, exit guide vanes 300, and a booster stage 400.

[0101] The splitter - ring anti - icing device 100 may be located behind the fan 200, that is, downstream of the fan 200. The splitter ring divides the air flow behind the fan 200 into two streams, which enter the outer and inner ducts respectively. The splitter - ring anti - icing device 100 includes a splitter ring and its internal structure for preventing the splitter ring and the booster stage from icing.

[0102] The fan 200 may be positioned upstream of the splitter - ring anti - icing device 100, the exit guide vanes 300 may be positioned in the outer - duct and downstream of the splitter - ring anti - icing device 100, while the booster stage 400 may be positioned in the inner - duct and downstream of the splitter - ring anti - icing device 100.

[0103] In Figure 1 the illustrated embodiment, the exit guide vanes 300 are shown as 12 - o'clock struts, that is, the guide vanes at the approximate vertical top of the aeroengine.

[0104] Figure 2 Shows a schematic diagram of a part of the splitter - ring anti - icing device 100 according to a non - limiting embodiment of the present invention observed in the circumferential direction; and Figure 3 shows a schematic diagram of another part of the splitter - ring anti - icing device 100 according to a non - limiting embodiment of the present invention observed in the circumferential direction.

[0105] As shown in the figure, the splitter - ring anti - icing device 100 may mainly include: a splitter - ring body 10, a stator casing 20, an oil - collecting chamber 30, and an oil - guiding pipe 40.

[0106] The splitter - ring body 10, or splitter ring, is an annular device located at the exit of the engine fan rotor blades and the inlet of the booster stage for separating the inner and outer flow paths of the turbofan engine. Arranging an anti - icing device at the position of the splitter ring can effectively improve the icing of the splitter ring, thereby reducing the interference of ice crystals on the flow field and the risk of ice crystal ingestion into the core engine.

[0107] As Figure 2 and 3As shown, the splitter ring body 10 may include a splitter ring front portion 11, a splitter ring rear portion 12, and a first mating portion 13 located between the splitter ring front portion 11 and the splitter ring rear portion 12. Since the splitter ring body 10 extends continuously in the circumferential direction, the first mating portion 13 may form a generally circular mounting hole.

[0108] As used herein, the terms "front portion" and "rear portion" are relative to the heading of the aircraft or along the axial direction of the engine. The direction in the heading direction or the intake direction of the engine may be referred to as the "front portion", i.e., the nose direction, and the opposite direction may be referred to as the "rear portion", i.e., the tail direction.

[0109] The splitter ring front portion 11 may include a leading edge nose that tapers towards the front portion, while the splitter ring rear portion 12 may include a first flange portion 14 that extends radially inwardly.

[0110] The stator casing 20 may be positioned radially inside the splitter ring body 10. The stator casing 20 may be a zero-stage (0-stage) stator casing and may include a second flange portion 21 and a third flange portion 22. The 0-stage stator casing may be fixed to the zero-stage (0-stage) stator vane 401 or be integral with the zero-stage stator vane, for example, by welding to form a single unit.

[0111] The radially outer end of the second flange portion 21 forms a second mating portion 23 that extends continuously in the circumferential direction C, i.e., having a circumferential cylindrical surface. The second mating portion 23 may be inserted into the mounting hole formed by the first mating portion 13, thereby forming a hole-shaft type mating connection to ensure reliable centering. In this way, the first mating portion 13 and the second mating portion 23 form a sealed mating.

[0112] As an example, the splitter ring anti-icing device 100 may further include a sealing device 80. The sealing device 80 may be, for example, an O-ring or a sealing strip and is arranged in the circumferential direction C between the first mating portion 13 and the second mating portion 23.

[0113] In this way, the front flange surface of the splitter ring and the flange surface of the zero-stage stator casing 20A form a hole-shaft fit to maintain assembly centering, and the flange surface of the splitter ring keeps the mating surface sealed through an O-ring or a sealing strip to form a closed integral ring structure.

[0114] In addition, as Figure 2 and 3 shown, the first flange portion 14 and the third flange portion 22 may be stacked together, thereby also forming a kind of sealed mating and can be used for the axial positioning of the splitter ring body 10 relative to the stator casing 20.

[0115] More specifically, the first flange portion 14 (i.e., the rear flange surface) of the flow dividing ring body 10 can be fitted with the third flange portion 22 (i.e., its rear flange surface) of the zero-stage stator casing 20A and the flange surface of the first-stage stator casing 20B to form axial positioning, and be fastened by fastening means such as bolts described below to maintain sealing. The first-stage stator casing 20B can be positioned radially outside the first-stage rotor blades 402, and there can be a gap between the first-stage stator casing 20B and the first-stage rotor blades 402.

[0116] With this arrangement, the oil sump 30 can be formed by enclosing the flow dividing ring body 10 and the stator casing 20. The oil sump 30 is formed by the flow dividing ring body 10 on the circumferential outer side, by the stator casing 20 on the circumferential inner side, and a sealing fit is formed by the first mating portion 13 and the second mating portion 23 at the front side, while a sealing fit is formed by the first flange portion 14 and the third flange portion 22 at the rear side, thus forming a sealed accommodation space.

[0117] The oil guide pipe 40 can allow the lubricating oil from the aeroengine 1000 to circulate through the oil sump 30 in the circumferential direction C.

[0118] It can be seen that Figure 2 the view of Figure 3 shows the position where the oil guide pipe 40 is not arranged, while

[0119] As Figure 3 shown in

[0120] the insertion end of the oil guide pipe 40 can be provided with a boss 40A, which can abut against the flange surface of the first-stage stator casing 20B. Additionally, the flow dividing ring anti-icing device 100 can further include fastening means 50, such as threaded fasteners like nuts and bolts. The oil guide pipe 40 can pass through the openings provided in the first flange portion 14 and the third flange portion 22 to be in fluid communication with the oil sump 30, and be fixed by means of the fastening means 50. In this way, with the boss 40A and the fastening means 50, the oil guide pipe 40 is firmly fixed relative to the flange surfaces of the first flange portion 14, the third flange portion 22, and the first-stage stator casing 20B.

[0121] Figure 4 shows a schematic flow path of the lubricating oil in the flow dividing ring anti-icing device 100 according to a non-limiting embodiment of the present invention.

[0122] As shown in the figure, the oil guiding pipe 40 may include a first oil guiding pipe 41 and a second oil guiding pipe 42. The first oil guiding pipe 41 may be used to introduce lubricating oil, while the second oil guiding pipe 42 may be used to discharge lubricating oil. For example, the first oil guiding pipe 41 allows the lubricating oil from the lubricating oil radiator 60 to enter the oil collecting chamber 30, and the second oil guiding pipe 42 allows the lubricating oil to enter the bearing chamber 70 from the oil collecting chamber 30.

[0123] As an example, the first oil guiding pipe 41 extends through the outlet guide vane 300 (especially the 12 o'clock support plate), and the second oil guiding pipe 42 may extend through the inside of the support plate of the intermediate inner casing.

[0124] As described above, fastening devices 50 are respectively provided at the openings where the first oil guiding pipe 41 and the second oil guiding pipe 42 enter the oil collecting chamber 30 to seal the first oil guiding pipe 41 and the second oil guiding pipe 42 to the oil collecting chamber 30.

[0125] In addition, a control valve 43 and / or a control pump 44 are provided on the first oil guiding pipe 41 and / or the second oil guiding pipe 42 to adjust the flow rate of the lubricating oil entering the oil collecting chamber 30 and adjust the anti-icing effect. For example, the control valve 43 may be a variable flow control valve, etc., and the control pump 44 may be a variable flow control pump. Preferably, the control valve 43 and the control pump 44 may be connected to a controller to adjust the operations of the control valve 43 and the control pump 44 based on data such as temperature sensors and altitude sensors according to a predetermined program, so as to control the flow rate of the lubricating oil circulating in the oil collecting chamber 30.

[0126] Figure 5 A schematic front view of a split ring anti-icing device 100 according to a non-limiting embodiment of the present invention is shown.

[0127] As Figure 5 shown, the first oil guiding pipe 41 and the second oil guiding pipe 42 may be separated by a partition plate 45, so that the lubricating oil entering the oil collecting chamber 30 through the first oil guiding pipe 41 travels counterclockwise for approximately one circle and then leaves the oil collecting chamber 30 through the second oil guiding pipe 42. The power driving the lubricating oil to flow in the oil collecting chamber 30 and the first oil guiding pipe 41 and the second oil guiding pipe 42 may come from a lubricating oil pump, such as the control pump 44 described above.

[0128] Figure 5 It is shown that the lubricating oil in the oil collecting chamber 30 travels counterclockwise. If observed in the forward flight direction, that is, observed from the rear to the front in the axial direction, the lubricating oil will travel / flow approximately clockwise in the oil collecting chamber 30.

[0129] As shown in the figure, the split ring anti-icing device 100 may further include a flow disturbing device 90 provided inside the oil collecting chamber 30.

[0130] As an example, the spoiler device 90 can be a baffle arranged on the wall surface of the annular cavity of the oil collecting cavity 30. For example, a metal baffle. The lubricating oil can flow tortuously along the flow path formed by the baffle. After the lubricating oil flows clockwise along the shunt ring for one circle in the course direction, it still flows out from the 12 o'clock direction and enters the bearing cavity 70 through the second oil guiding pipe 42.

[0131] As a first non-limiting embodiment, the spoiler device 90 can include a first group of baffles 91 and a second group of baffles 92.

[0132] As Figure 5 shown, the first group of baffles 91 and the second group of baffles 92 can be alternately arranged along the circumferential direction C, that is, alternately arranged in the annular cavity of the oil collecting cavity 30. For example, a person skilled in the art can first arrange one baffle of the first group of baffles 91, then one baffle of the second group of baffles 92, and then continue to arrange one baffle of the first group of baffles 91, and so on in a cycle. Or alternatively, a person skilled in the art can first arrange one baffle of the second group of baffles 92, and then arrange one baffle of the first group of baffles 91, and so on in a cycle. In this way, in the entire circumferential direction of the annular cavity of the oil collecting cavity 30, the first group of baffles 91 and the second group of baffles 92 are alternately or spaced apart from each other, and the spacing or angular displacement between adjacent baffles can be substantially the same.

[0133] Figure 6 shows a schematic diagram of the first group of baffles 91 of the shunt ring anti-icing device 100 according to a non-limiting embodiment of the present invention; and Figure 7 shows a schematic diagram of the second group of baffles 92 of the shunt ring anti-icing device 100 according to a non-limiting embodiment of the present invention.

[0134] As Figure 6 clearly shown, the first group of baffles 91 can extend backward in the axial direction from the front end of the oil collecting cavity 30, and a first group of gaps 91A are formed between the free ends of the first group of baffles 91 and the first flange portion 14.

[0135] As Figure 7 clearly shown, the second group of baffles 92 extend forward in the axial direction from the rear end of the oil collecting cavity 30, and a second group of gaps 92A are formed between the free ends of the second group of baffles 92 and the second mating portion 23.

[0136] In this way, the lubricating oil entering the oil collecting cavity 30 through the first oil guiding pipe 41 can be blocked by the first group of baffles 91 to flow through the first group of gaps 91A, then be blocked by the second group of baffles 92 to flow through the second group of gaps 92A, and so on in a cycle, and enter the second oil guiding pipe 42 through the last gap, so as to leave the oil collecting cavity 30, as Figure 5 shown by the curved arrows in.

[0137] As a preferred embodiment, each of the first set of gaps 91A and the second set of gaps 92A has an equal cross-sectional area.

[0138] The functions of the first set of baffles 91 and the second set of baffles 92 may include: providing a tortuous flow path for the lubricating oil, reducing the flow rate of the lubricating oil, increasing the heat exchange time, and making the heat exchange more sufficient; increasing the contact area between the lubricating oil and the flow splitting ring, and improving the heat exchange efficiency. It should be noted that the partition plate 45 arranged between the first oil guiding pipe 41 and the second oil guiding pipe 42 and the oil collecting chamber 30 is closed to prevent the lubricating oil from directly injecting from the inlet to the outlet without circulating circumferentially along the oil collecting chamber 30.

[0139] As a second non-limiting embodiment, the flow disturbing device 90 may include a third set of baffles 93 and a fourth set of baffles 94.

[0140] Figure 8 Another schematic front view of the flow splitting ring anti-icing device 100 according to a non-limiting embodiment of the present invention is shown.

[0141] As shown in the figure, the third set of baffles 93 and the fourth set of baffles 94 may be alternately arranged along the circumferential direction C, that is, alternately arranged in the annular cavity of the oil collecting chamber 30. For example, a person skilled in the art may first arrange one baffle of the third set of baffles 93, then one baffle of the fourth set of baffles 94, and then continue to arrange one baffle of the third set of baffles 93 in this cycle. Alternatively, a person skilled in the art may first arrange one baffle of the fourth set of baffles 94, and then arrange one baffle of the third set of baffles 93 in this cycle. In this way, the third set of baffles 93 and the fourth set of baffles 94 are alternately or spaced apart from each other in the entire circumferential annular cavity of the oil collecting chamber 30, and the spacing or angular displacement between adjacent baffles may be substantially the same.

[0142] In this way, the lubricating oil entering the oil collecting chamber 30 via the first oil guiding pipe 41 can be blocked by the third set of baffles 93 to flow through the third set of gaps 93A, and then be blocked by the fourth set of baffles 94 to flow through the fourth set of gaps 94A in this cycle, and enter the second oil guiding pipe 42 via the last gap, so as to leave the oil collecting chamber 30, as Figure 5 shown by the curved arrow in.

[0143] Figure 9 A schematic diagram of the third set of baffles of the flow splitting ring anti-icing device according to a non-limiting embodiment of the present invention is shown; while Figure 10 A schematic diagram of the fourth set of baffles of the flow splitting ring anti-icing device according to a non-limiting embodiment of the present invention is shown.

[0144] As Figure 9 clearly shown in, the third set of baffles 93 extends radially inwards from the flow splitting ring body 10 (in Figure 10extends downward (in the middle), and a third set of gaps 93A are formed between the free ends of the third set of baffles 93 and the stator casing 20.

[0145] As Figure 10 clearly shown in, the fourth set of baffles 94 extend radially outward (upward in the middle) from the stator casing 20, and a fourth set of gaps 94A are formed between the free ends of the fourth set of baffles 94 and the diverter ring body 10. Figure 10 extends upward (in the middle), and a fourth set of gaps 94A are formed between the free ends of the fourth set of baffles 94 and the diverter ring body 10.

[0146] Additionally, although not shown herein, those skilled in the art can alternatively arrange the first set of baffles 91, the second set of baffles 92, the third set of baffles 93, and the fourth set of baffles 94 in combination to form a more tortuous and complex flow path to further improve the heat exchange effect.

[0147] As used herein, the terms "axial direction", "radial direction", "front", "rear" representing orientation or direction, and the terms "first", "second", etc. used to represent order are only for enabling those of ordinary skill in the art to better understand the concept of the present invention shown in the preferred embodiments, rather than for limiting the present invention. Unless otherwise specified, all orders, orientations or directions are only for the purpose of distinguishing one element / component / structure from another element / component / structure, and unless otherwise specified, do not represent any specific order, operation sequence, direction or orientation. For example, in an alternative embodiment, the "first oil conduit" can be the "second oil conduit", and the "first set of baffles" can alternatively refer to the "second set of baffles".

[0148] In summary, the diverter ring anti-icing device 100 according to the embodiments of the present invention overcomes the disadvantages in the prior art and achieves the intended invention purpose.

[0149] Although the diverter ring anti-icing device of the present invention has been described above in combination with the preferred embodiments, those of ordinary skill in the art should recognize that the above examples are only for illustration and cannot be used to limit the present invention. Therefore, various modifications and variations can be made to the present invention within the scope of the spirit of the claims, and these modifications and variations will all fall within the scope required by the claims of the present invention.

Claims

1. A split ring anti-icing device (100) for an aeroengine (1000), comprising: A split ring body (10), the split ring body includes a split ring front part (11), a split ring rear part (12) and a first mating part (13) located between the split ring front part (11) and the split ring rear part (12), wherein, the split ring rear part (12) includes a first flange part (14) extending radially inwards; A stator casing (20), the stator casing is positioned radially inside the split ring body (10), and includes a second flange part (21) and a third flange part (22), the radially outer end of the second flange part (21) forms a second mating part (23) extending continuously in the circumferential direction (C); An oil sump (30), the oil sump is formed by enclosing the split ring body (10) and the stator casing (20), wherein, the first mating part (13) is in sealing cooperation with the second mating part (23) and the first flange part (14) is in sealing cooperation with the third flange part (22); and An oil guiding pipe (40), the oil guiding pipe allows lubricating oil from the aeroengine (1000) to enter the oil sump (30), and allows the lubricating oil circulating through the oil sump (30) to leave the oil sump (30).

2. The split ring anti-icing device (100) according to claim 1, characterized in that, The split ring anti-icing device further includes a fastening device (50), wherein, the oil guiding pipe (40) passes through openings provided in the first flange part (14) and the third flange part (22) to be in fluid communication with the oil sump (30), and is fixed by means of the fastening device (50).

3. The split ring anti-icing device (100) according to claim 2, characterized in that, The oil guiding pipe (40) includes a first oil guiding pipe (41) and a second oil guiding pipe (42), wherein, the first oil guiding pipe (41) allows lubricating oil from a lubricating oil radiator (60) to enter the oil sump (30), while the second oil guiding pipe (42) allows lubricating oil to enter a bearing chamber (70) from the oil sump (30).

4. The split ring anti-icing device (100) according to claim 3, characterized in that, A control valve (43) and / or a control pump (44) are provided on the first oil guiding pipe (41) and / or the second oil guiding pipe (42).

5. The split ring anti-icing device (100) according to claim 1, characterized in that, The split ring anti-icing device further includes a sealing device (80), wherein, the sealing device is arranged between the first mating part (13) and the second mating part (23) in the circumferential direction (C).

6. The split ring anti-icing device (100) according to any one of claims 1-5, characterized in that, The split ring anti-icing device further includes a flow disturbing device (90) provided inside the oil sump (30).

7. The split ring anti-icing device (100) according to claim 6, characterized in that, The spoiler device (90) includes a first set of baffles (91) and a second set of baffles (92), and the first set of baffles (91) and the second set of baffles (92) are arranged alternately along the circumferential direction (C), wherein, the first set of baffles (91) extends backward in the axial direction from the front end of the oil collecting chamber (30), and a first set of gaps (91A) are formed between the free ends of the first set of baffles (91) and the first flange portion (14), and wherein, the second set of baffles (92) extends forward in the axial direction from the rear end of the oil collecting chamber (30), and a second set of gaps (92A) are formed between the free ends of the second set of baffles (92) and the second mating portion (23).

8. The split ring anti-icing device (100) according to claim 7, wherein, each of the first set of gaps (91A) and the second set of gaps (92A) has an equal cross-sectional area.

9. The split ring anti-icing device (100) according to claim 6, wherein, the spoiler device (90) includes a third set of baffles (93) and a fourth set of baffles (94), and the third set of baffles (93) and the fourth set of baffles (94) are arranged alternately along the circumferential direction (C), wherein, the third set of baffles (93) extends inward in the radial direction from the split ring body (10), and a third set of gaps (93A) are formed between the free ends of the third set of baffles (93) and the stator casing (20), and wherein, the fourth set of baffles (94) extends outward in the radial direction from the stator casing (20), and a fourth set of gaps (94A) are formed between the free ends of the fourth set of baffles (94) and the split ring body (10).

10. An aeroengine (1000), the aeroengine comprising: the split ring anti-icing device (100) according to any one of claims 1-9, a fan (200) positioned upstream of the split ring anti-icing device (100); an outlet guide vane (300) positioned in the bypass duct and downstream of the split ring anti-icing device (100), and a booster stage (400) positioned in the core duct and downstream of the split ring anti-icing device (100).

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