Splitter ring and aircraft engine

Abstract

The present disclosure provides a diverter ring and an aircraft engine. The diverter ring includes a shell. The shell includes an outer peripheral wall, an inner peripheral wall, a first partition wall and a second partition wall. The inner peripheral wall is located at the radial inner side of the outer peripheral wall and is connected to the front end of the outer peripheral wall, and the inner peripheral wall surrounds the inlet flow channel of the diverter ring. The first partition wall is located at the rear side of the second partition wall, the first partition wall and the second partition wall are connected between the outer peripheral wall and the inner peripheral wall, the outer peripheral wall, the inner peripheral wall, the first partition wall and the second partition wall surround a first cavity, and the outer peripheral wall, the inner peripheral wall and the second partition wall surround a second cavity. The first partition wall is provided with an airflow introduction hole, and the airflow introduction hole is connected to the first cavity. The second partition wall is provided with a plurality of connecting holes, and the connecting holes connect the first cavity and the second cavity. The inner peripheral wall is provided with an exhaust channel, and the exhaust channel connects the second cavity and the inlet flow channel. The diverter ring and the aircraft engine are conducive to improving the heat exchange effect between the anti-icing gas and the diverter ring, and reducing the bleed air flow of the anti-icing gas.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft engines, and in particular to a splitter ring and an aircraft engine. Background Art

[0002] The icing of aircraft engines has a huge impact on flight safety. Once icing occurs, it can cause poor air intake in the engine and reduce the engine's operating efficiency. In severe cases, it can cause the engine to shut down or even be physically damaged, leading to serious safety accidents.

[0003] The splitter ring of an aircraft engine is a physical element used to separate the inner and outer airflows after the fan, and is a typical component that needs to be de-iced. The common de-icing form of the splitter ring in the related art is hot gas de-icing. Figure 1 and Figure 2 The principle of splitter ring hot gas anti-icing of aircraft engines is shown.

[0004] like Figure 1 and Figure 2 As shown, the aircraft engine includes a compressor 1, a combustion chamber 2, a turbine 3, a nacelle 4, a support plate 5, a diverter ring 6 and an anti-icing air bleed path 7. The inlet air passage surrounded by the inner peripheral wall of the diverter ring 6 is used to introduce the gas to be compressed by the compressor 1. The outlet end of the anti-icing air bleed pipe of the anti-icing air bleed path 7 is connected to the cavity at the front end of the diverter ring 6, which is used to introduce part of the compressed gas in the compressor 1 into the cavity as anti-icing gas. The anti-icing gas exchanges heat with the leading edge of the shell of the diverter ring 6 to prevent the diverter ring 6 from freezing. In order to save energy, when the diverter ring adopts hot gas anti-icing, it is necessary to reduce the amount of anti-icing gas bleed as much as possible while ensuring the anti-icing effect. Summary of the invention

[0005] The object of the present disclosure is to provide a splitter ring and an aircraft engine, aiming to reduce the bleed air amount of anti-icing gas.

[0006] A first aspect of the present disclosure provides a flow divider ring, comprising a shell, wherein the shell comprises an outer peripheral wall, an inner peripheral wall, a first partition wall and a second partition wall, wherein:

[0007] The inner peripheral wall is located radially inward of the outer peripheral wall and connected to the front end of the outer peripheral wall, and the inner peripheral wall encloses an inlet flow passage of the diverter ring;

[0008] The first partition wall is located at the rear side of the second partition wall, the first partition wall and the second partition wall are connected between the outer peripheral wall and the inner peripheral wall, the outer peripheral wall, the inner peripheral wall, the first partition wall and the second partition wall form a first cavity, and the outer peripheral wall, the inner peripheral wall and the second partition wall form a second cavity;

[0009] The first partition wall is provided with an air flow introduction hole, the air flow introduction hole is in communication with the first cavity and is configured to be connected to an anti-icing air bleed pipe to introduce anti-icing gas into the first cavity;

[0010] The second partition wall is provided with a plurality of communication holes, the communication holes communicating with the first cavity and the second cavity, and configured to introduce the anti-icing gas in the first cavity into the second cavity; and

[0011] An exhaust passage is provided on the inner peripheral wall. The exhaust passage communicates with the second cavity and the intake air passage and is configured to introduce the anti-icing gas in the second cavity into the intake air passage.

[0012] In some embodiments, the plurality of communicating holes are evenly distributed along the circumference of the diverter ring.

[0013] In some embodiments, the communicating hole is located radially outside the second partition wall.

[0014] In some embodiments, the exhaust passage is located at a rear end of the second cavity.

[0015] In some embodiments, the exhaust passage includes a first slit.

[0016] In some embodiments, a guide channel is provided between the inner peripheral wall and the second partition wall, and the guide channel connects the second cavity and the exhaust channel.

[0017] In some embodiments, the guide channel includes a second slit.

[0018] In some embodiments, the volume of the first cavity is greater than the volume of the second cavity.

[0019] In some embodiments, the diverter ring further includes a vortex generating device, which is disposed in the second cavity and configured to generate a vortex in the anti-icing gas in the second cavity.

[0020] In some embodiments, the vortex generating device includes a plurality of vortex generating parts arranged corresponding to the plurality of connecting holes.

[0021] In some embodiments, the vortex generating portion includes two guide plates arranged at circumferential intervals along the diverter ring, the rear end of the interval between the two guide plates is opposite to the outlet of the connecting hole corresponding to the vortex generating portion, and there is a interval between the front end of the guide plate and the outer peripheral wall and / or the inner peripheral wall.

[0022] In some embodiments, the guide piece is connected to the inner peripheral wall at a distance from the outer peripheral wall.

[0023] In some embodiments, the two guide vanes have the same structure and are symmetrically arranged with respect to a plane extending along the radial direction of the diverter ring.

[0024] In some embodiments, a front end distance of the interval between the two guide pieces is greater than a rear end distance.

[0025] In some embodiments, the guide plate is a folded plate-like structure, including a first guide portion and a second guide portion that forms an angle with the first guide portion, the first guide portion is located on the front side of the second guide portion and has an angle with the axial direction of the diverter ring, and the second guide portion extends along the axial direction of the diverter ring.

[0026] In some embodiments, the flow area formed by the interval between the front end of each guide piece and the outer peripheral wall and / or the inner peripheral wall is smaller than 1 / 2 of the flow area formed by the interval between the two guide pieces.

[0027] A second aspect of the present disclosure provides an aircraft engine, comprising:

[0028] The splitter ring according to the first aspect of the present disclosure; and

[0029] An anti-icing air bleed pipe, wherein the outlet end of the anti-icing air bleed pipe is installed at the air flow introduction hole of the diverter ring and is communicated with the first cavity of the diverter ring.

[0030] Based on the diverter ring provided by the present disclosure, a first cavity and a second cavity are provided along the flow direction of the anti-icing gas, and the first cavity and the second cavity are connected through a connecting hole. When the anti-icing gas flows from the first cavity to the second cavity, there is a gas contraction process in the connecting hole, and the airflow velocity of the anti-icing gas will increase. When the anti-icing gas airflow is injected into the second cavity and reaches the front end of the second cavity, the convective heat transfer coefficient will increase due to the high speed, and the heat transfer effect will be enhanced, so that the temperature of the front outer wall surface can be higher. Due to the enhanced heat transfer effect, the air bleed amount of the anti-icing gas can be reduced under the same anti-icing effect.

[0031] The aircraft engine provided by the present disclosure has the same advantages as the splitter ring of the present disclosure. Other features and advantages of the present disclosure will become clear through the following detailed description of exemplary embodiments of the present disclosure with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings described herein are used to provide a further understanding of the present disclosure and constitute a part of the present application. The illustrative embodiments of the present disclosure and their descriptions are used to explain the present disclosure and do not constitute an improper limitation on the present disclosure. In the drawings:

[0033] Figure 1 The present invention is a schematic diagram of the principle structure of the aero-engine's diverter ring being protected from icing by hot gas anti-icing method according to the related technology.

[0034] Figure 2 for Figure 1 The schematic diagram of the partial cross-sectional structure of the diverter ring of an aircraft engine is shown.

[0035] Figure 3 It is a schematic diagram of a partial radial cross-sectional structure of the diverter ring according to an embodiment of the present disclosure.

[0036] Figure 4 for Figure 3 The schematic diagram of the partial three-dimensional structure of the diverter ring with partial cross-section is shown.

[0037] Figure 5 for Figure 4 The enlarged structural diagram of part G is shown.

[0038] Figure 6 for Figure 3 The schematic diagram of the partial three-dimensional structure of the diverter ring with partial cross-section is shown.

[0039] Figure 7 for Figure 6 A schematic diagram of the partial cross-sectional structure of section A.

[0040] Figure 8 for Figure 6 A schematic diagram of the partial cross-sectional structure of section B.

[0041] Fig. 9 It is a schematic diagram of a partial radial cross-sectional structure of the diverter ring according to an embodiment of the present disclosure.

[0042] Fig.10 It is a schematic diagram of a partial circumferential cross-sectional structure of the diverter ring according to an embodiment of the present disclosure. DETAILED DESCRIPTION

[0043] The following will be combined with the drawings in the embodiments of the present disclosure to clearly and completely describe the technical solutions in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present disclosure and its application or use. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present disclosure.

[0044] Unless otherwise specifically stated, the relative arrangement of the parts and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present disclosure. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship. The technology, methods and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar numbers and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further discussed in subsequent drawings.

[0045] In the description of the present disclosure, it should be understood that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present disclosure.

[0046] In the description of the present disclosure, it is necessary to understand that the orientation or positional relationship indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present disclosure and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the scope of protection of the present disclosure; the directional words "inside and outside" refer to the inside and outside relative to the outline of each component itself.

[0047] In the following description, unless otherwise specified, the "front" refers to the axial air inlet side of the diverter ring; the "rear" refers to the side opposite to the "front", and the "radial", "axial" and "circumferential" refer to the radial, axial and circumferential directions of the diverter ring.

[0048] Figures 3 to 10 The structure of a diverter ring 100 according to an embodiment of the present disclosure is shown.

[0049] like Figures 3 to 10 As shown, the flow dividing ring 100 includes a housing 101. The housing 101 includes an outer peripheral wall 1011, an inner peripheral wall 1012, a first partition wall 1013 and a second partition wall 1014.

[0050] The inner peripheral wall 1012 is located radially inward of the outer peripheral wall 1011 and connected to the front end of the outer peripheral wall 1011 . The inner peripheral wall 1012 surrounds the inlet flow passage of the splitter ring.

[0051] The first partition wall 1013 is located at the rear side of the second partition wall 1014. The first partition wall 1013 and the second partition wall 1014 are connected between the outer peripheral wall 1011 and the inner peripheral wall 1012. The outer peripheral wall 1011, the inner peripheral wall 1012, the first partition wall 1013 and the second partition wall 1014 surround the first cavity 103. The outer peripheral wall 1011, the inner peripheral wall 1012 and the second partition wall 1014 surround the second cavity 105.

[0052] The first partition wall 1013 is provided with an airflow introduction hole 102 . The airflow introduction hole 102 is in communication with the first cavity 103 and is configured to be connected to the anti-icing air duct 200 to introduce anti-icing gas into the first cavity 103 .

[0053] A plurality of communication holes 104 are formed on the second partition wall 1014 . The communication holes 104 communicate with the first cavity 103 and the second cavity 105 , and are configured to introduce the anti-icing gas in the first cavity 103 into the second cavity 105 .

[0054] An exhaust passage 107 is provided on the inner peripheral wall 1012 . The exhaust passage 107 communicates with the second cavity 105 and the intake air passage, and is configured to introduce the anti-icing gas in the second cavity 105 into the intake air passage.

[0055] In the diverter ring 100 of the disclosed embodiment, a first cavity 103 and a second cavity 105 are provided along the flow direction of the anti-icing gas, and the first cavity 103 and the second cavity 105 are connected through a connecting hole 104. When the anti-icing gas flows from the first cavity 103 to the second cavity 105, there is a gas contraction process in the connecting hole 104, and the airflow velocity of the anti-icing gas will increase. When the anti-icing gas airflow is injected into the second cavity 105 and reaches the front end of the second cavity 105, the convective heat transfer coefficient will increase due to the high speed, and the heat transfer effect will be enhanced, so that the temperature of the front outer wall surface can be higher. Due to the enhanced heat transfer effect, the air bleed amount of the anti-icing gas can be reduced under the same anti-icing effect.

[0056] like Figure 3 As shown, in some embodiments, the volume of the first cavity 103 is greater than the volume of the second cavity 105 .

[0057] Since the volume of the second cavity 105 is relatively small, the airflow of the anti-icing gas quickly returns after entering the second cavity 105, thereby strengthening the degree of airflow disturbance in the second cavity 105, which is beneficial to improving the convective heat transfer coefficient. Furthermore, since the second cavity 105 needs to be provided, the wall thickness of the front edge of the shell 101 (including the front edge of the outer peripheral wall 1011 and the inner peripheral wall 1012) can be thinned, especially when the material of the diverter ring is an alloy with a low thermal conductivity such as titanium alloy, the thinner wall surface is particularly important, which can further improve the heat exchange effect between the anti-icing gas and the front edge of the shell 101, thereby improving the anti-icing effect.

[0058] like Figures 4 to 8 As shown, in some embodiments, a plurality of communication holes 104 are evenly distributed along the circumference of the flow splitter ring 100. Such arrangement of the communication holes 104 can, on the one hand, form a porous impact airflow, which is conducive to multiple high-speed airflows impacting the shell 101 in the second cavity 105 to enhance heat exchange, and on the other hand, the anti-icing gas is more evenly distributed in the second cavity 1015, which is conducive to uniform heat exchange between the anti-icing gas and the leading edge of the shell 101, thereby improving the anti-icing effect.

[0059] like Figure 3 and Fig. 9 As shown, in some embodiments, the connecting hole 104 is located radially outside the second partition wall 1014. Under this arrangement, the anti-icing gas flowing out of the connecting hole 104 flows from the radial outside of the second cavity 105 to the front end of the second cavity and then flows to the exhaust channel 107 located radially inside the second cavity 105, which is conducive to the anti-icing gas forming a vortex that first flows approximately axially, then flows approximately radially, and then flows approximately axially to enhance heat exchange and increase the flow path of the anti-icing gas in the second cavity 105, and is also conducive to destroying the airflow boundary layer of the outer peripheral wall 1011 and the inner peripheral wall 1012 at the second cavity 105, thereby facilitating sufficient heat exchange between the anti-icing gas and the front edge of the shell 101 and improving the anti-icing effect.

[0060] like Figure 3 and Fig. 9 As shown, in some embodiments, the exhaust passage 107 is located at the rear end of the second cavity 1015. This arrangement is conducive to the formation of a vortex in the second cavity 1015 by the anti-icing gas, which can enhance heat exchange on the one hand, and increase the flow path of the anti-icing gas in the second cavity 1015 on the other hand, which is conducive to sufficient heat exchange between the anti-icing gas and the front edge of the shell 101, thereby improving the anti-icing effect.

[0061] like Figure 5 As shown, in some embodiments, the exhaust passage 107 includes a first slit. Providing the exhaust passage in the form of a slit is beneficial to improving the flow speed and uniformity of the anti-icing gas around the inner periphery of the leading edge of the shell 101, and is beneficial to strengthening and uniformizing heat exchange.

[0062] like Figure 5As shown, in some embodiments, a guide channel 106 is provided between the inner peripheral wall 1012 and the second partition wall 1014, and the guide channel 106 connects the second cavity 105 and the exhaust channel 107. This arrangement facilitates the anti-icing gas to flow from the radial outer side of the second cavity 105 to the front end of the second cavity 105 and then to the rear end of the radial inner side of the second cavity 105, and facilitates the anti-icing gas to form a vortex that first flows approximately axially, then flows approximately radially, and then flows approximately axially to enhance heat exchange and increase the flow path of the anti-icing gas in the second cavity 105, thereby facilitating sufficient heat exchange between the anti-icing gas and the leading edge of the shell 101 and improving the anti-icing effect.

[0063] like Figure 5 As shown, the guide channel 106 includes a second slit. The slit-shaped guide channel 106 is provided to evenly distribute the anti-icing gas in the second cavity 105, to improve the flow speed and uniformity of the anti-icing gas around the inner periphery of the leading edge of the shell 101, and to enhance and evenly exchange heat.

[0064] like Figures 3 to 9 As shown, the flow dividing ring 100 further includes a vortex generating device 108. The vortex generating device 108 is disposed in the second cavity 105 and is configured to generate a vortex in the gas in the second cavity 105.

[0065] A vortex generating device 108 is arranged in the second cavity 105, which is beneficial to destroying the boundary layer of the airflow, improving the heat exchange capacity between the anti-icing gas and the leading edge of the shell 101, and balancing the poor local heat exchange effect when the anti-icing gas directly impacts the leading edge of the shell 101, thereby improving the uniformity of heat exchange while strengthening heat exchange.

[0066] like Figures 3 to 10 As shown, the vortex generating device 108 includes a plurality of vortex generating parts 1081 arranged corresponding to the plurality of connecting holes 104. The connecting holes 104 and the vortex generating parts 1081 are arranged in this way, so that the anti-icing gas entering the second cavity 105 from each connecting hole 104 generates vortices, which is beneficial to strengthening the heat exchange between the anti-icing gas and the leading edge of the shell 101, and improving the anti-icing effect.

[0067] like Figures 4 to 8 , Fig.10 As shown, in some embodiments, the vortex generating portion 1081 includes two guide pieces spaced apart along the circumferential direction of the diverter ring 100, and the two guide pieces are a first guide piece 10811 and a second guide piece 10812. The rear end of the interval between the two guide pieces is opposite to the outlet of the communicating hole 104 corresponding to the vortex generating portion 1081, and there is a gap between the front end of the guide piece and the outer peripheral wall 1011 and / or the inner peripheral wall 1012.

[0068] In some embodiments, the flow area formed by the interval between the front end of the guide piece and the outer peripheral wall 1011 and / or the inner peripheral wall 1012 is smaller than 1 / 2 of the flow area formed by the interval between two guide pieces.

[0069] like Fig.10 As shown, the main flow path of the anti-icing gas entering the second cavity 105 from each connecting hole 104 is: first flowing forward into the gap between the two guide plates, and then respectively entering between the adjacent guide plates of two adjacent vortex generating parts 1081 from the gap between the front ends of the two guide plates and the outer peripheral wall 1011 and / or the inner peripheral wall 1012, flowing backward along the gap between the adjacent guide plates of the two adjacent vortex generating parts 1081, and then entering the guide channel 106 (if any) and the exhaust channel 107, and finally flowing into the inlet flow channel of the diverter ring 100 through the exhaust channel 107, and being compressed by the compressor together with the compressor intake.

[0070] After the airflow of the anti-icing gas flows into the second cavity 105 from the connecting hole 104, it impacts the leading edge of the shell 101, and then moves along the circumference of the diverter ring 100 to the two sides of the vortex generating part 1081. The airflow passing through the gap between the vortex generating part 1081 and the leading edge of the shell 101 will form a vortex under the guidance of the vortex generating part 1081. The vortex will destroy the airflow boundary layer on the inner wall of the leading edge of the shell 101, thereby improving the heat exchange capacity; at the same time, since the vortex generating part 1081 plays a certain guiding role, the gas can still move a certain distance along the circumference of the diverter ring 100 along the leading edge of the shell 101, thereby enhancing the heat exchange effect at the position where the leading edge of the shell 101 cannot be impacted by the airflow.

[0071] When the flow area formed by the gap between the front end of each guide plate and the outer peripheral wall 1011 and / or the inner peripheral wall 1012 is less than 1 / 2 of the flow area formed by the gap between two guide plates, the flow area is reduced when the airflow flows through the gap between the front end of the guide plate and the outer peripheral wall 1011 and / or the inner peripheral wall 1012, and the airflow speed will be accelerated. At this time, a pressure difference will be formed on both sides of the guide plate of the vortex generating part 1081, which is beneficial to the flow of airflow and thus more conducive to the formation of vortex.

[0072] The vortex generating portion 1081 is configured to include two guide blades, which is conducive to the formation of a vortex in which the anti-icing gas first flows along the circumferential direction of the diverter ring 100 and then flows along the axial direction, which is conducive to strengthening heat exchange and increasing the flow path length of the anti-icing gas in the second cavity 105, thereby facilitating sufficient heat exchange between the anti-icing gas and the leading edge of the shell 101, and improving the anti-icing effect. In addition, while strengthening the air flow disturbance of the wall surface directly impacted by the anti-icing gas airflow in the second cavity 105, it is conducive to improving the heat exchange capacity at the position between the two impacted wall surfaces, thereby facilitating reducing the degree of heat exchange unevenness while improving the heat exchange capacity.

[0073] like Figures 3 to 10 As shown, the guide blade is connected to the inner peripheral wall 1012 at intervals from the outer peripheral wall 1011. This arrangement is conducive to increasing the flow direction of the anti-icing airflow in the second cavity 105, enriching the vortex form formed by the anti-icing gas, and thus facilitating the heat exchange effect between the anti-icing gas and the front edge of the shell 101.

[0074] like Figure 8 and Fig.10 As shown, in some embodiments, the two guide fins have the same structure and are symmetrically arranged relative to a plane extending along the radial direction of the splitter ring 100. This arrangement is conducive to improving the overall uniformity of the anti-icing gas in the second cavity 105, thereby facilitating the uniformity of heat exchange between the anti-icing gas and the leading edge of the housing 101. In addition, this arrangement is also conducive to the processing and manufacturing of the splitter ring 100.

[0075] like Figure 8 and Fig.10 As shown, in some embodiments, the front end distance between the two guide vanes is greater than the rear end distance. This arrangement is conducive to the anti-icing gas forming a vortex flowing along the circumferential direction at the front end of the second cavity 105.

[0076] like Figure 8 and Fig.10 As shown, the guide piece is a folded plate structure, including a first guide portion 1081A and a second guide portion 1081B which is at an angle to the first guide portion 1081A, the first guide portion 1081A is located in front of the second guide portion 1081B and has an angle with the axial direction of the splitter ring 100, and the second guide portion 1081B extends along the axial direction of the splitter ring 100. This form of guide piece has a simple structure and is easy to process and install while ensuring the effect of generating eddy currents.

[0077] The embodiment of the present disclosure also provides an aircraft engine, comprising the aforementioned diverter ring 100 and an anti-icing air duct 200. The outlet end of the anti-icing air duct 200 is installed at the airflow introduction hole 102 of the diverter ring 100 and communicates with the first cavity 103 of the diverter ring. The aircraft engine has the advantages of the diverter ring 100 of the embodiment of the present disclosure.

[0078] According to the above description, the splitter ring 100 and the aircraft engine having the splitter ring 100 according to the embodiment of the present disclosure have at least one of the following advantages:

[0079] Since the anti-icing gas in the first cavity 103 is injected into the second cavity 105 through the connecting hole 104 and reaches the front end of the second cavity 105 at a high speed, it impacts the inner wall surface of the front edge of the shell 101, and the convection heat transfer coefficient becomes larger, thereby enhancing the heat transfer effect. Since the heat transfer effect is enhanced, it is beneficial to reduce the anti-icing air intake amount and improve the utilization rate of the anti-icing hot air.

[0080] Since the vortex generating device 108 is arranged in the second cavity 105, it is beneficial to destroy the boundary layer of the airflow, improve the heat exchange capacity between the anti-icing gas and the leading edge of the shell 101, and balance the situation where the local heat exchange effect is poor when the anti-icing gas directly impacts the inner wall of the leading edge of the shell 101, thereby improving the uniformity of heat exchange while strengthening the heat exchange.

[0081] Since the volume of the second cavity 105 is set to be relatively small, and since the second cavity 105 is provided, the thickness of the front edge of the shell 101 can be designed to be relatively thinner, the convection heat transfer coefficient will become larger, and the heat exchange effect will be enhanced.

[0082] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present disclosure rather than to limit it. Although the present disclosure has been described in detail with reference to the preferred embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the present disclosure can still be modified or some technical features can be replaced by equivalents, which should all be included in the scope of the technical solution for protection requested by the present disclosure.

Claims

1. A flow divider ring, comprising a housing (101), characterized in that: The housing (101) comprises an outer peripheral wall (1011), an inner peripheral wall (1012), a first partition wall (1013) and a second partition wall (1014), wherein: The inner peripheral wall (1012) is located radially inward of the outer peripheral wall (1011) and connected to the front end of the outer peripheral wall (1011), and the inner peripheral wall (1012) encloses an inlet flow passage of the flow splitter ring (100); The first partition wall (1013) is located at the rear side of the second partition wall (1014); the first partition wall (1013) and the second partition wall (1014) are connected between the outer peripheral wall (1011) and the inner peripheral wall (1012); the outer peripheral wall (1011), the inner peripheral wall (1012), the first partition wall (1013) and the second partition wall (1014) form a first cavity (103); the outer peripheral wall (1011), the inner peripheral wall (1012) and the second partition wall (1014) form a second cavity (105); The first partition wall (1013) is provided with an air flow introduction hole (102), the air flow introduction hole (102) is in communication with the first cavity (103), and is configured to be connected to an anti-icing air bleed pipe (200) to introduce anti-icing gas into the first cavity (103); The second partition wall (1014) is provided with a plurality of communication holes (104), the communication holes (104) communicating with the first cavity (103) and the second cavity (105), and being configured to introduce the anti-icing gas in the first cavity (103) into the second cavity (105); and An exhaust passage (107) is provided on the inner peripheral wall (1012), and the exhaust passage (107) is connected with the second cavity (105) and the intake flow passage, and is configured to introduce the anti-icing gas in the second cavity (105) into the intake flow passage.

2. The flow divider ring according to claim 1, characterized in that: The plurality of communication holes (104) are evenly distributed along the circumference of the diverter ring (100).

3. The flow divider ring according to claim 1, characterized in that: The communicating hole (104) is located radially outside the second partition wall (1014).

4. The flow divider ring according to claim 1, characterized in that: The exhaust passage (107) is located at the rear end of the second cavity (105).

5. The flow divider ring according to claim 1, characterized in that: The exhaust passage (107) includes a first slit.

6. The flow divider ring according to claim 1, characterized in that: A flow guide channel (106) is provided between the inner peripheral wall (1012) and the second partition wall (1014), and the flow guide channel (106) communicates with the second cavity (105) and the exhaust channel (107).

7. The flow divider ring according to claim 6, characterized in that: The flow guiding channel (106) comprises a second slit.

8. The flow divider ring according to claim 7, characterized in that: The volume of the first cavity (103) is greater than the volume of the second cavity (105).

9. The flow divider ring according to any one of claims 1 to 8, characterized in that: The diverter ring (100) further comprises a vortex generating device (108), which is disposed in the second cavity (105) and is configured to generate a vortex in the anti-icing gas in the second cavity (105).

10. The flow divider ring according to claim 9, characterized in that: The vortex generating device (108) comprises a plurality of vortex generating parts (1081) arranged corresponding to the plurality of communication holes (104).

11. The flow divider ring according to claim 10, characterized in that: The vortex generating portion (1081) includes two guide plates arranged at intervals along the circumference of the diverter ring (100), the rear end of the interval between the two guide plates is opposite to the outlet of the connecting hole (104) corresponding to the vortex generating portion (1081), and there is a gap between the front end of the guide plate and the outer peripheral wall (1011) and / or the inner peripheral wall (1012).

12. The flow divider ring according to claim 11, characterized in that: The guide piece is connected to the inner peripheral wall (1012) at a distance from the outer peripheral wall (1011).

13. The flow divider ring according to claim 11, characterized in that: The two guide plates have the same structure and are arranged symmetrically with respect to a plane extending along the radial direction of the diverter ring (100).

14. The flow divider ring according to claim 11, characterized in that: The front end distance of the interval between the two guide pieces is greater than the rear end distance.

15. The flow divider ring according to claim 14, characterized in that: The guide plate is a folded plate structure, comprising a first guide portion (1081A) and a second guide portion (1081B) which forms an angle with the first guide portion (1081A), wherein the first guide portion (1081A) is located in front of the second guide portion (1081B) and has an angle with the axial direction of the diverter ring (100), and the second guide portion (1081B) extends along the axial direction of the diverter ring (100).

16. The flow divider ring according to claim 11, characterized in that: The flow area formed by the interval between the front end of each guide piece and the outer peripheral wall (1011) and / or the inner peripheral wall (1012) is smaller than 1 / 2 of the flow area formed by the interval between the two guide pieces.

17. An aircraft engine, characterized in that: include: A splitter ring (100), which is a splitter ring (100) according to any one of claims 1 to 16; and An anti-icing air bleed pipe (200), wherein the outlet end of the anti-icing air bleed pipe (200) is installed at the air flow introduction hole (102) of the splitter ring (100) and is in communication with the first cavity (103) of the splitter ring.

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