Splitter ring and aircraft engine

Abstract

The present invention discloses a diverter ring and an aircraft engine, which relate to the field of aircraft engines and are used to optimize the structure of the diverter ring. The diverter ring includes an outer ring and an inner ring. The outer ring is constructed in an annular shape; the inner ring is constructed in an annular shape; the inner ring is located inside the outer ring, and the inner ring and the outer ring form an annular flow channel; the wall of the inner ring is provided with a circle of swirl flow channels along its own circumference, so that the hot air in the inner ring enters the annular flow channel through the swirl flow channel. The diverter ring provided by the above technical solution allows for more sufficient heat exchange between the hot air and the metal surface of the diverter ring, thereby achieving the purpose of reducing the bleed air flow rate while ensuring the anti-icing effect.

Description

Technical Field

[0001] The invention relates to the field of aeroengines, and in particular to a splitter ring and an aeroengine. Background Art

[0002] Since clouds may contain metastable supercooled liquid water with a temperature below the freezing point, when an aircraft passes through these clouds, ice is likely to form on the surface of the windward parts of the aircraft. For aircraft engine intake parts, such as intake fairings, fan blades, intake support plates, and engine splitter rings, the probability of ice formation is greater because the airflow will be accelerated and cooled when it is sucked by the engine. Ice formation will deteriorate the starting performance of the components and cause the center of gravity of the rotating parts to shift and intensify vibration. These phenomena are very unfavorable to flight safety. Therefore, anti-icing systems are installed on aircraft and their engines currently in service.

[0003] The hot air anti-icing system draws hot air from the engine air system and delivers it to the inner cavity of the anti-icing component through specific pipes and valves, thereby increasing the surface temperature of the anti-icing component and preventing ice from forming on the surface of the component. After flowing out of the anti-icing cavity, the anti-icing bleed air is usually merged into other air system flow paths, or directly discharged to the external atmosphere and the engine main flow channel.

[0004] The splitter ring of a turbofan engine is a typical anti-icing component, and its anti-icing form is hot gas anti-icing. The hot gas is directly introduced into the inner cavity of the splitter ring through the bleed air pipeline, and then a smaller annular flow channel is set near the leading edge of the splitter ring to make the air flow pass through the leading edge of the splitter ring at high speed and exchange heat with it, and finally discharged into the main flow channel of the engine.

[0005] The inventors have found that there are at least the following problems in the prior art: since the size of the diverter ring is usually small, it is not feasible to arrange mature and efficient anti-icing elements such as flute tubes inside it. Therefore, the anti-icing heat exchange efficiency can only be improved by constructing and optimizing the anti-icing flow channel in the inner cavity of the diverter ring, or by increasing the bleed air flow and temperature to ensure the anti-icing effect. Summary of the invention

[0006] The present invention provides a splitter ring and an aircraft engine, which are used to optimize the structure of the splitter ring.

[0007] An embodiment of the present invention provides a shunt ring, comprising:

[0008] an outer ring configured in a ring shape; and

[0009] The inner ring is constructed in an annular shape; the inner ring is located inside the outer ring, and the inner ring and the outer ring form an annular flow channel; the wall of the inner ring is provided with a circle of swirl flow channel along its own circumference, so that the hot air in the inner ring enters the annular flow channel through the swirl flow channel.

[0010] In some embodiments, a direct current channel is provided at the leading edge of the inner ring, and the direct current channel penetrates through the wall of the inner ring and is in fluid communication with the annular flow channel.

[0011] In some embodiments, an inner wall of the outer ring is provided with an inner recess, and the inner recess corresponds to the straight flow channel, so that the fluid flowing out through the straight flow channel enters the inner recess.

[0012] In some embodiments, a plurality of the direct current channels are provided along the circumference of the inner ring.

[0013] In some embodiments, the inner loop comprises:

[0014] an outer wall located inside the outer ring, with one end of the outer wall separated from the inner wall of the outer ring and the other end of the outer wall in contact with the inner wall of the outer ring to form the annular flow channel; and

[0015] An inner wall, located on the inner side of the outer wall, one end of the inner wall is fixedly connected to one end of the outer wall, and the other end of the inner wall is separated from the other end of the outer wall;

[0016] Wherein, the portion between the outer wall and the inner wall is a gas collecting cavity.

[0017] In some embodiments, the diverter ring further comprises:

[0018] A support member is arranged between the outer wall and the inner wall; one end of the support member abuts against the other end of the inner wall, and the other end of the support member abuts against the other end of the outer wall, so that the other end of the outer wall abuts against the inner wall of the outer ring.

[0019] In some embodiments, the support member is configured in a strip shape, and a plurality of the support members are disposed along a radial direction of the diverter ring.

[0020] In some embodiments, the diverter ring further comprises:

[0021] A sealing member is arranged between the other end of the outer side wall and the inner wall of the outer ring.

[0022] In some embodiments, one end of the outer ring is configured to be bent so that an end portion of the one end of the outer ring and an outer side wall of the inner ring form an air outlet.

[0023] In some embodiments, the swirl flow channel runs through the outer side wall of the inner ring, and the length direction of each swirl flow channel is configured to be spiral.

[0024] An embodiment of the present invention further provides an aircraft engine, comprising a splitter ring provided by any technical solution of the present invention.

[0025] The diverter ring provided by the above technical solution, by setting a swirl flow channel on the inner ring, makes the heat exchange between the hot gas and the metal surface of the diverter ring more sufficient, thereby achieving the purpose of reducing the bleed air flow rate under the premise of ensuring the anti-icing effect. In addition, there is no need to bleed air from the high-pressure stage of the compressor to increase the temperature and pressure, which improves the thermal energy utilization method, reduces the waste of bleed air heat, and is beneficial to the performance of the engine. Especially when the engine is frozen, there will be no excessive bleed air, so the engine exhaust temperature margin will not be insufficient due to the diverter ring anti-icing; and the diverter ring anti-icing dependence on the high-temperature and high-pressure gas source is reduced from the source, improving the operating conditions of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0027] Figure 1 A schematic cross-sectional view of the meridian structure of an anti-icing ring provided in an embodiment of the present invention;

[0028] Figure 2 A schematic diagram of a front view of an anti-icing ring provided in an embodiment of the present invention;

[0029] Figure 3 A schematic diagram of the three-dimensional structure of the inner ring of the anti-icing ring provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0030] Combine the following Figure 1 to Figure 3 The technical solution provided by the present invention is described in more detail.

[0031] Explanation of terms or terms used in this article.

[0032] Turbofan aircraft engine: A gas turbine device used to power aircraft, which is characterized by the fact that part of the engine thrust is generated by external air pressurized by the fan, and the other part is generated by the internal combustion gas produced by the engine's thermodynamic cycle.

[0033] Splitter Ring: In a turbofan aircraft engine, a stationary physical component that separates the external and internal airflows, usually downstream of and immediately adjacent to the fan blades.

[0034] See also Figures 1 to 3The embodiment of the present invention provides a diverter ring, comprising an outer ring 1 and an inner ring 2. The outer ring 1 is constructed in an annular shape. The inner ring 2 is constructed in an annular shape; the inner ring 2 is located inside the outer ring 1, and the inner ring 2 and the outer ring 1 form an annular flow channel 3. The wall of the inner ring 2 is provided with a circle of swirl flow channel 21 along its own circumference, so that the hot gas in the inner ring 2 enters the annular flow channel 3 through the swirl flow channel 21.

[0035] The outer ring 1 is a component located outside the diverter ring, and the wall of the outer ring 1 is single-layer.

[0036] The inner ring 2 is located inside the inner ring 2, and the outer wall of the inner ring 2 and the inner wall of the outer ring 1 form an annular flow channel 3. The annular flow channel 3 is subsequently used to accommodate hot air to achieve anti-icing and de-icing of the diverter ring.

[0037] See also Figures 1 to 3 In some embodiments, the inner ring 2 includes an outer wall 23 and an inner wall 24. The outer wall 23 is located on the inner side of the outer ring 1, and one end of the outer wall 23 is separated from the inner wall of the outer ring 1, and the other end of the outer wall 23 is in contact with the inner wall of the outer ring 1 to form an annular flow channel 3. The inner wall 24 is located on the inner side of the outer wall 23, and one end of the inner wall 24 is fixedly connected to one end of the outer wall 23, and the other end of the inner wall 24 is separated from the other end of the outer wall 23. Among them, the part between the outer wall 23 and the inner wall 24 is a gas collecting cavity 25. The gas in the gas collecting cavity 25 comes from the air system. The air system refers to an air flow path system in which a part of the air is drawn out from the mainstream to meet specific purposes in an aircraft engine, a gas turbine or an independent compressor. The drawn air can be used for cooling hot end components, anti-icing of air intake components, sealing, balancing axial forces, or providing various external systems and equipment.

[0038] The swirl flow channel 21 is a through hole that penetrates the wall of the inner ring 2. The number of swirl flow channels 21 and the flow area of ​​each swirl flow channel 21 are related to the required ice-melting heat. Each swirl flow channel 21 is arranged at intervals. Under the same flow area requirement, the swirl flow channel 21 can be set as a slender hole or a short and wide hole. The structure of each swirl flow channel 21 can be the same, or it can be set to different sizes according to the different circumferential ice-melting requirements of the diverter ring.

[0039] See also Figures 1 to 3 In some embodiments, the swirl flow channel 21 passes through the outer wall 23 of the inner ring 2, and the length direction of each swirl flow channel 21 is configured to be spiral. This can improve the flow direction of the gas entering the annular flow channel 3 through the swirl flow channel 21, thereby improving the heat exchange effect.

[0040] The diverter ring provided by the above technical solution has an inner ring 2 and an outer ring 1, and the inner ring 2 is provided with a swirl flow channel 21. The hot air in the inner ring 2 enters the annular flow channel 3 through the swirl flow channel 21, and this part of the fluid will produce circumferential motion, so that the anti-icing hot air advances in a spiral manner during anti-icing. Since the axial velocity of the hot air decreases after the circumferential flow, and the axial flow distance of the hot air is not shortened, the unit mass of hot air stays in the diverter ring for a longer time, so that the heat exchange between the hot air and the diverter ring is more sufficient, the heat exchange effect is improved, and the anti-icing heat exchange efficiency between the hot air and the diverter ring is improved, thereby saving the amount of anti-icing bleed air and / or reducing the temperature of the anti-icing bleed air. The reduction in the amount of bleed air can not only reduce the impact of the anti-icing system on the overall performance of the engine, but also reduce the size of the anti-icing system pipelines and valves, achieve engine weight reduction, and improve the economic indicators of the engine.

[0041] See also Figures 1 to 3 In some embodiments, a direct current channel 22 is provided at the leading edge of the inner ring 2 , and the direct current channel 22 penetrates the wall of the inner ring 2 and is in fluid communication with the annular flow channel 3 .

[0042] After the direct flow channel 22 is set, the hot gas in the gas collecting cavity 25 is divided into two parts. One part of the hot gas S1 is transported to the annular flow channel 3 of the diverter ring through the swirl flow channel 21 and forms a circumferential flow, and the other part of the hot gas S2 impacts the front edge of the diverter ring through the direct flow channel 22 at the front edge of the diverter ring to heat the front edge area. The two anti-icing hot gases are mixed near the front edge and enter the downstream flow path together to be used for anti-icing on the inner surface of the diverter ring.

[0043] For different types of diverter rings, the total flow areas of the swirl flow channel 21 and the straight flow channel 22 can be different, and the flow areas of the swirl flow channel 21 and the straight flow channel 22 can be adjusted, so that the anti-icing flow can be distributed on demand. Among them, the total flow area of ​​the swirl flow channel 21 should make the hot gas flow passing through not less than the anti-icing critical design flow outside the diverter ring, and the effective total flow area of ​​the straight flow channel 22 should make the hot gas flow passing through not less than the anti-icing critical design flow at the leading edge of the diverter ring.

[0044] In the above technical solution, since the hot gas directly flows out of the straight channel 22 when the leading edge of the diverter ring impacts, no other impact structure is needed, which reduces the heat transfer resistance between the hot gas and the outer surface of the diverter ring in the traditional solution. In addition, by adjusting the flow channel area of ​​the swirl channel 21 and the straight channel 22, the hot gas flow rate can be distributed on demand, thereby further optimizing the amount of anti-icing hot gas, achieving efficient use of anti-icing hot gas, and improving the heat exchange efficiency by distributing and using the anti-icing hot gas. In addition, the technical solution of the embodiment of the present invention can reduce the flow rate of high-pressure bleed air, or directly bleed air from a relatively low-pressure position of the engine, thereby ultimately achieving the purpose of reducing the bleed air flow (pressure) and temperature and improving the operating state of the engine under anti-icing conditions.

[0045] See also Figure 1 In some embodiments, the inner wall of the outer ring 1 is provided with an inner recess 11, and the inner recess 11 corresponds to the direct current channel 22, so that the fluid flowing out through the direct current channel 22 impacts into the inner recess 11, and finally the impact airflow flowing out through the direct current channel 22 generates a vortex in the inner recess 11 to enhance heat exchange.

[0046] See also Figure 3 In some embodiments, a plurality of straight flow channels 22 are provided along the circumference of the inner ring 2. The straight flow channels 22 have a relatively small flow area, a relatively strong impact force, and a good heat exchange effect.

[0047] See also Figure 3 In some embodiments, the flow divider ring further includes a support member 4, which is disposed between the outer side wall 23 and the inner side wall 24; one end of the support member 4 abuts against the other end of the inner side wall 24, and the other end of the support member 4 abuts against the other end of the outer side wall 23, so that the other end of the outer side wall 23 abuts against the inner wall of the outer ring 1. The support member 4 can be specifically fixed to other fixed components of the aircraft engine by a cantilever.

[0048] See also Figure 3 In some embodiments, the support member 4 is constructed in a strip shape, and multiple support members 4 are provided along the radial direction of the diverter ring. The support member 4 is provided between the inner wall 24 and the outer wall 23 of the inner ring 2 of the diverter ring to improve the rigidity of the inner ring 2 of the diverter ring and ensure the aerodynamic shape and sealing effect of the diverter ring.

[0049] See also Figure 1 In some embodiments, the diverter ring further includes a seal 5, which is disposed between the other end of the outer side wall 23 and the inner wall of the outer ring 1. The seal 5 is, for example, a metal sealing ring to meet the high temperature working conditions of the diverter ring.

[0050] See also Figure 1 In some embodiments, one end of the outer ring 1 is configured to be bent so that the end of the outer ring 1 and the outer side wall 23 of the inner ring 2 form an air outlet. The air outlet can be a hole, a slit or other structures.

[0051] A seal 5 is used at one end of the annular channel to prevent hot air leakage, and the other end is connected to the main air flow path of the engine through an air outlet to achieve anti-icing hot air exhaust.

[0052] An embodiment of the present invention further provides an aircraft engine, comprising a splitter ring provided by any technical solution of the present invention.

[0053] In the description of the present invention, it is necessary to understand that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the protection content of the present invention.

[0054] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein, but these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A diverter ring, characterized in that: include: An outer ring (1) is constructed in a ring shape; as well as The inner ring (2) is constructed in an annular shape; the inner ring (2) is located inside the outer ring (1), and the inner ring (2) and the outer ring (1) form an annular flow channel (3); the wall of the inner ring (2) is provided with a circle of swirl flow channels (21) along its circumference, so that hot air in the inner ring (2) enters the annular flow channel (3) via the swirl flow channels (21); The inner ring (2) comprises: an outer wall (23) located on the inner side of the outer ring (1), with one end of the outer wall (23) separated from the inner wall of the outer ring (1) and the other end of the outer wall (23) in contact with the inner wall of the outer ring (1), so as to form the annular flow channel (3); and an inner wall (24) located on the inner side of the outer wall (23), one end of the inner wall (24) being fixedly connected to one end of the outer wall (23), and the other end of the inner wall (24) being separated from the other end of the outer wall (23); Wherein, the portion between the outer wall (23) and the inner wall (24) is a gas collecting cavity (25).

2. The flow divider ring according to claim 1, characterized in that: A straight flow channel (22) is provided at the front edge of the inner ring (2), and the straight flow channel (22) penetrates the wall of the inner ring (2) and is fluidically connected to the annular flow channel (3).

3. The flow divider ring according to claim 2, characterized in that: An inner wall of the outer ring (1) is provided with an inner recess (11), and the inner recess (11) corresponds to the direct flow channel (22), so that the fluid flowing out through the direct flow channel (22) enters the inner recess (11).

4. The flow divider ring according to claim 2, characterized in that: A plurality of the direct flow channels (22) are arranged along the circumference of the inner ring (2).

5. The flow divider ring according to claim 1, characterized in that: Also includes: A support member (4) disposed between the outer side wall (23) and the inner side wall (24); One end of the support member (4) abuts against the other end of the inner wall (24), and the other end of the support member (4) abuts against the other end of the outer wall (23), so that the other end of the outer wall (23) abuts against the inner wall of the outer ring (1).

6. The flow divider ring according to claim 5, characterized in that: The support member (4) is constructed in a strip shape, and a plurality of the support members (4) are arranged along the radial direction of the diverter ring.

7. The flow divider ring according to claim 1, characterized in that: Also includes: A sealing member (5) is arranged between the other end of the outer side wall (23) and the inner wall of the outer ring (1).

8. The flow divider ring according to claim 1, characterized in that: One end of the outer ring (1) is configured to be bent so that an end portion of the one end of the outer ring (1) and an outer side wall (23) of the inner ring (2) form an air outlet.

9. The flow divider ring according to claim 1, characterized in that: The swirl flow channel (21) passes through the outer wall (23) of the inner ring (2), and the length direction of each swirl flow channel (21) is constructed in a spiral shape.

10. An aircraft engine, characterized in that: It comprises the diverter ring described in any one of claims 1 to 9.

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