Aero-engine and shunt ring thereof

Abstract

The invention provides an aero-engine and a shunt ring thereof. The flow dividing ring comprises a ring body, the ring body is provided with a gas collecting cavity adaptive to the shape of the ring body, a gas inlet is formed in the rear wall of the ring body, a gas outlet is formed in the front wall of the ring body, and the gas collecting cavity is configured to introduce heating gas flow needed for heating the ring body through the gas inlet and discharge the heating gas flow after heat exchange through the gas outlet; and the first separation part is arranged in the gas collection cavity and corresponds to the position of the gas inlet, and the gas collection cavity is divided into a first sub-cavity and a second sub-cavity which are arranged in the circumferential direction of the ring body by the first separation part, so that the heating gas flow can be divided into two paths to flow at the position of the gas inlet. According to the aero-engine and the shunt ring thereof, the anti-icing effect of the shunt ring can be improved by optimizing the anti-icing structure.

Description

Technical Field

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

[0002] The surface of the diverter ring of an aircraft engine is prone to ice formation when encountering low temperature weather. Ice on the diverter ring will change its original aerodynamic shape and easily cause the engine to deviate from the designed working state. Ice on the diverter ring will also cause uneven blockage of the intake flow duct along the circumference, which may cause intake distortion or surge. If the ice on the diverter ring is severe, the detached ice may be sucked into the engine and collide with the high-speed rotating engine blades, causing structural damage to the engine. The current diverter ring mainly uses hot air anti-icing, but the anti-icing structure itself needs to be optimized, and the anti-icing effect needs to be improved. Summary of the invention

[0003] The purpose of the present disclosure is to provide an aircraft engine and a splitter ring thereof, so as to optimize the anti-icing structure and improve the anti-icing effect of the splitter ring.

[0004] A first aspect of the present disclosure provides a splitter ring of an aircraft engine, comprising:

[0005] A ring body having an air collecting cavity adapted to its own shape, wherein the rear wall of the ring body is provided with an air inlet, and the front wall of the ring body is provided with an air outlet, and the air collecting cavity is configured to introduce a heated airflow required for heating the ring body through the air inlet, and discharge the heated airflow after heat exchange through the air outlet; and

[0006] A first partition is disposed in the air collecting chamber and corresponds to the position of the air inlet. The first partition divides the air collecting chamber into a first sub-chamber and a second sub-chamber disposed along the circumference of the ring body, so that the heated airflow can be divided into two flows at the position of the air inlet.

[0007] According to some embodiments of the present disclosure, a second partition is included, and two second partitions are respectively arranged in the first sub-chamber and the second sub-chamber, and the two second partitions respectively divide the first sub-chamber and the second sub-chamber into two sub-chambers arranged along the axial direction of the ring body.

[0008] According to some embodiments of the present disclosure, the second partition is provided with a vent hole, and the vent hole connects the two sub-cavities.

[0009] According to some embodiments of the present disclosure, along the circumference of the ring body, on a unit area basis, the sum of the flow areas of the ventilation holes located at the upstream end is smaller than the sum of the flow areas of the ventilation holes located at the downstream end.

[0010] According to some embodiments of the present disclosure, on a radial cross section of the ring body, the second partition is in a straight line shape, or the second partition is in an arc shape that protrudes toward the front wall of the ring body.

[0011] According to some embodiments of the present disclosure, the second partition is connected to the first partition and extends along the circumference of the ring body, and the central angle of the first sub-cavity and the central angle of the second sub-cavity are respectively larger than the central angle of the corresponding second partition.

[0012] According to some embodiments of the present disclosure, along the circumference of the ring body, the flow areas of the first sub-chamber and the second sub-chamber gradually decrease from the upstream end to the downstream end.

[0013] According to some embodiments of the present disclosure, a third partition is included. Along the circumference of the ring body, the third partition is spaced apart from the first partition, and the first sub-chamber and the second sub-chamber are separated by the third partition at the downstream end.

[0014] According to some embodiments of the present disclosure, along the circumference of the ring body, on a unit area basis, the sum of the flow areas of the air outlets located at the upstream end is smaller than the sum of the flow areas of the air outlets located at the downstream end.

[0015] A second aspect of the present disclosure provides an aircraft engine, comprising the splitter ring described in the first aspect of the present disclosure.

[0016] When the diverter ring of the aircraft engine provided by the present invention is working, the heated airflow can be directly introduced into the air collecting cavity inside the ring body through the air inlet, and under the action of the first partition part, it is divided into two flows in the first cavity and the second cavity along the circumference of the ring body and exchanges heat with the diverter ring, thereby heating the diverter ring and preventing external water vapor from freezing on the surface of the diverter ring. The airflow after heat exchange can be discharged through the air outlet and merged into the mainstream of the aircraft engine.

[0017] Based on the above structure, the heated airflow can directly enter the air collecting cavity through the air inlet and exchange heat with the diverter ring. There is no need to set up an air supply pipeline in the air collecting cavity, which is beneficial for optimizing the diverter ring anti-icing structure from the perspective of simplifying the air supply pipeline, reducing additional heat dissipation and reducing weight.

[0018] The aircraft engine provided by the present disclosure has the advantages of the aforementioned splitter ring.

[0019] Other features and advantages of the present disclosure will become apparent from the following detailed description of exemplary embodiments of the present disclosure with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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:

[0021] Figure 1 It is a schematic diagram of the structure of an aircraft engine according to some embodiments of the present disclosure.

[0022] Figure 2 The figure is a schematic diagram of the heated air flow path of the diverter ring according to some embodiments of the present disclosure, wherein the diverter ring is expanded in the circumferential direction.

[0023] Figure 3 It is a schematic diagram of the radial cross-sectional structure of the diverter ring of some embodiments of the present disclosure, wherein the cutting position does not pass through the air inlet.

[0024] Figure 4 Schematic diagram of the radial cross-sectional structure of the diverter ring according to other embodiments of the present disclosure, wherein the cutting position does not pass through the air inlet.

[0025] Figures 1 to 4 In the figure, each reference numeral represents:

[0026] 1. flow dividing ring; 10. ring body; 101. gas collecting chamber; 102. air inlet; 103. air outlet; 104. first sub-chamber; 104a. first sub-chamber of the first sub-chamber; 104b. second sub-chamber of the first sub-chamber; 105. second sub-chamber; 105a. first sub-chamber of the second sub-chamber; 105b. second sub-chamber of the second sub-chamber; 11. first partition; 12. second partition; 121. vent; 13. third partition; B. rear wall; F. front wall;

[0027] 2. Air bleed pipe;

[0028] 3. Connotation of Tao;

[0029] 4. External duct; 5. Fan;

[0030] 6. High pressure compressor. DETAILED DESCRIPTION

[0031] 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.

[0032] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present disclosure. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, these technologies, methods and equipment should be considered as a part of the 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 reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0033] 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.

[0034] 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.

[0035] An embodiment of the present disclosure provides an aircraft engine and a splitter ring thereof.

[0036] The aircraft engine provided by the embodiment of the present disclosure includes the diverter ring provided by the embodiment of the present disclosure, and has the advantages of the diverter ring. Figures 1 to 4 The splitter ring provided in the embodiment of the present disclosure is described.

[0037] The flow dividing ring includes a ring body 10 and a first partition 11. The ring body 10 has a gas collecting cavity 101 adapted to its own shape, the rear wall B of the ring body 10 is provided with an air inlet 102, and the front wall F of the ring body 10 is provided with an air outlet 103. The gas collecting cavity 101 is configured to introduce the heating airflow required for heating the ring body 10 through the air inlet 102, and discharge the heated airflow after heat exchange through the air outlet 103. The first partition 11 is arranged in the gas collecting cavity 101 and corresponds to the position of the air inlet 102. The first partition 11 divides the gas collecting cavity 101 into a first sub-cavity 104 and a second sub-cavity 105 arranged along the circumference of the ring body 10, so that the heated airflow can be divided into two flows at the position of the air inlet 102.

[0038] Optionally, refer to Figure 1 The aircraft engine includes a flow divider ring 1, an air bleed pipe 2, an inner duct 3, an outer duct 4, a fan 5 and a high-pressure compressor 6. The air inlet end of the air bleed pipe 2 is connected to the high-pressure compressor 6, and the air outlet end of the air bleed pipe 2 is connected to the air inlet 102 of the flow divider ring 1. The heated air flow can be high-temperature and high-pressure gas provided by the high-pressure compressor.

[0039] When the diverter ring of the aircraft engine provided by the embodiment of the present disclosure is working, the heated airflow can be directly introduced into the air collecting cavity inside the ring body through the air inlet, and under the action of the first partition, it is divided into two flows in the first sub-cavity and the second sub-cavity along the circumference of the ring body and exchanges heat with the diverter ring, thereby heating the diverter ring and preventing external water vapor from freezing on the surface of the diverter ring. The airflow after heat exchange can be discharged through the air outlet and merged into the mainstream of the aircraft engine.

[0040] Based on the above structure, the heated airflow can directly enter the air collecting cavity through the air inlet, flow along the circumference of the ring body and exchange heat with the diverter ring. There is no need to set air supply pipelines such as distribution pipes extending along the circumference of the diverter ring and diverter pipes connecting the distribution pipes and the air collecting cavity on the outside of the diverter ring. This is beneficial for optimizing the diverter ring anti-icing structure from the perspectives of simplifying the air supply pipelines, reducing additional heat dissipation and reducing weight.

[0041] Figure 2 Schematic diagram of the heating air flow path of the diverter ring in some embodiments of the present disclosure, wherein along the circumference of the ring body 10, the diverter ring gradually expands from the middle to both sides at the position of the air inlet 102, Figure 2 In the figure, the left-right direction is the circumferential direction of the ring body 10, the up-down direction is the axial direction of the ring body 10, and the arrow direction indicates the flow direction of the heated airflow. In the present disclosure, the descriptions of "upstream end" and "downstream end" are all based on the flow direction of the heated airflow.

[0042] Combine the following Figure 2 The structure and working principle of the diverter ring of some embodiments of the present disclosure are further explained.

[0043] In some embodiments, reference Figures 2 to 4 The diverter ring includes a second partition 12, and two second partitions 12 are respectively arranged in the first sub-chamber 104 and the second sub-chamber 105. The two second partitions 12 respectively divide the first sub-chamber 104 and the second sub-chamber 105 into two sub-chambers arranged along the axial direction of the ring body 10.

[0044] refer to Figure 2 A second partition 12 arranged in the first sub-chamber 104 divides the first sub-chamber 104 into a first sub-chamber 104a located on the side close to the rear wall B and a second sub-chamber 104b located on the side close to the front wall F. A second partition 12 arranged in the second sub-chamber 105 divides the second sub-chamber 105 into a first sub-chamber 105a located on the side close to the rear wall B and a second sub-chamber 105b located on the side close to the front wall F.

[0045] For the flow dividing ring in the above embodiment, the second partition has a blocking effect in the axial direction of the ring body, which can prevent the heated airflow entering the gas collecting cavity from directly rushing to the front wall of the ring body, and can change the flow direction of the heated airflow from the axial direction to the circumferential direction, thereby weakening the heat exchange near the air inlet of the gas collecting cavity to prevent overheating there. In addition, due to the provision of the second partition, it is not necessary to further provide a distribution pipeline for the heated airflow inside the gas collecting cavity, which is conducive to simplifying the gas supply pipeline.

[0046] In some embodiments, the second partition 12 is provided with a vent hole 121 , and the vent hole 121 connects the two sub-cavities.

[0047] By arranging air holes on the second partition, after the heated airflow enters the air collecting chamber from the air inlet, most of it is blocked by the second partition in the first sub-chamber corresponding to the first sub-chamber or the second sub-chamber, and a small part can enter the second sub-chamber corresponding to the first sub-chamber or the second sub-chamber through the air holes, which is beneficial for making the temperature of the second sub-chamber at the upstream end within a suitable range, so as to improve the anti-icing effect at the corresponding position.

[0048] In some embodiments, along the circumference of the ring body 10 , on a unit area basis, the sum of the flow areas of the vents 121 located at the upstream end is smaller than the sum of the flow areas of the vents 121 located at the downstream end.

[0049] Adjusting the sum of the flow areas of the vent holes per unit area can be achieved by adjusting the aperture of the vent holes or the density of the vent holes. Optionally, along the circumference of the ring body 10, the sum of the flow areas of the vent holes 121 per unit area gradually increases.

[0050] For the diverter ring of the above-mentioned embodiment, as the heated air flow flows and exchanges heat in the ring body, the temperature of the heated air flow gradually decreases, but the flow rate of the heated air flow from the first sub-chamber to the second sub-chamber can be increased accordingly, and in the process of the heated air flow from the first sub-chamber to the second sub-chamber, the throttling and deceleration effect of the vent on the heated air flow is relatively small, which is conducive to enhancing the heat exchange at the downstream end, so that the heat exchange at different positions of the diverter ring is more uniform.

[0051] In some embodiments, reference Figure 3 In the radial cross section of the ring body 10 , the second partition 12 is in a straight line shape.

[0052] Optionally, on the radial cross section of the ring body 10 , the second partition 12 is arranged radially along the diverter ring, and two ends of the second partition 12 are respectively connected to the radial inner circumferential surface of the gas collecting cavity 101 and the radial outer circumferential surface of the gas collecting cavity 101 .

[0053] In other embodiments, reference Figure 4 In the radial cross section of the ring body 10 , the second partition 12 is in the shape of an arc that protrudes toward the front wall F of the ring body 10 .

[0054] Compared with the straight second partition, the arc-shaped second partition protruding toward the front wall can reduce the contact area between the heated airflow and the inner wall of the first sub-cavity corresponding to the first sub-cavity or the second sub-cavity. This arrangement can not only reduce the heat dissipation of the heated airflow in the corresponding first sub-cavity, play a heat preservation effect, so that the heated airflow can still maintain a high temperature during the process of flowing to the downstream end, thereby reducing the upstream and downstream temperature difference, making the temperature distribution around the ring body more uniform, but also prevent the corresponding position of the inner wall of the first sub-cavity from overheating.

[0055] Moreover, for the arc-shaped second partition, more positions are available for opening vents, and the setting of the vents is more flexible. The vents can be set not only toward the front wall of the ring body, but also toward the circumferential surface radially inside or outside the air collecting cavity. Based on the vents in different directions, the flow direction of the heating airflow in the air collecting cavity can be further optimized.

[0056] Optionally, in the radial cross section of the ring body 10, the second partition 12 is U-shaped, and both ends of the second partition 12 are connected to the rear wall B. In this way, direct heat exchange between the heated airflow and the wall located on the radial inner or outer side of the gas collecting cavity can be avoided, further improving the heat preservation effect of the heated airflow in the first sub-cavity.

[0057] It can be seen that the arc-shaped second partition can improve the utilization efficiency of the heated airflow and reduce the usage of the heated airflow.

[0058] In some embodiments, the second partition 12 is connected to the first partition 11 and extends along the circumference of the ring body 10 , and the central angle of the first sub-cavity 104 and the central angle of the second sub-cavity 105 are respectively larger than the central angle of the corresponding second partition 12 .

[0059] In the diverter ring of the above embodiment, the first sub-chamber and the second sub-chamber corresponding to the first sub-chamber or the second sub-chamber are separated by a second partition at the upstream end, and the first sub-chamber and the second sub-chamber can be connected through the vent hole; and the first sub-chamber and the second sub-chamber corresponding to the first sub-chamber or the second sub-chamber are directly connected at the downstream end, and the heated airflows in the first sub-chamber and the second sub-chamber merge into one.

[0060] In some embodiments, along the circumference of the ring body 10 , the flow areas of the first sub-chamber 104 and the second sub-chamber 105 gradually decrease from the upstream end to the downstream end.

[0061] Optionally, refer to Figure 2 Along the circumference of the ring body 10 , the dimensions of the first sub-chamber 104 and the second sub-chamber 105 along the axial direction of the ring body 10 gradually decrease from the upstream end to the downstream end.

[0062] For the diverter ring in the above-mentioned embodiment, as the heated airflow flows and exchanges heat in the ring body, the temperature of the heated airflow gradually decreases, but the flow rate of the heated airflow entering the second sub-chamber from the first sub-chamber can be increased accordingly as the flow area of ​​the first sub-chamber and the second sub-chamber decreases, which is beneficial to enhance the heat exchange at the downstream end, so that the heat exchange at different positions of the diverter ring is more uniform.

[0063] In some embodiments, reference Figure 2 The flow dividing ring includes a third partition 13 , which is spaced apart from the first partition 11 along the circumference of the ring body 10 , and the first sub-chamber 104 and the second sub-chamber 105 are separated by the third partition 13 at the downstream end.

[0064] Optionally, the third partition 13 and the first partition 11 are arranged opposite to each other along the circumference of the ring body 10, and the first sub-cavity 104 and the second sub-cavity 105 are arranged symmetrically. Optionally, along the circumference of the ring body 10, the second partition 12 is connected to the first partition 11 at the upstream end, and is spaced apart from the third partition 13 at the downstream end.

[0065] By setting the third partition, the first chamber and the second chamber are not connected to each other at the downstream end, which can prevent the heated airflows in the first chamber and the second chamber from colliding with each other at the downstream end to cause pressure loss and reduce the adverse effect on the anti-icing effect.

[0066] In some embodiments, along the circumference of the ring body 10 , per unit area, the sum of the flow areas of the gas outlets 103 at the upstream end is smaller than the sum of the flow areas of the gas outlets 103 at the downstream end.

[0067] Adjusting the sum of the flow areas of each outlet per unit area can be achieved by adjusting the diameter of the outlet or the distribution density of the outlet. Optionally, along the circumference of the ring body 10, the sum of the flow areas of each outlet 103 per unit area gradually increases.

[0068] For the diverter ring in the above-mentioned embodiment, as the heated airflow flows and exchanges heat in the ring body, the temperature of the heated airflow gradually decreases, but the flow rate of the heated airflow flowing out of the air collecting chamber can be increased accordingly, which is beneficial to enhance the heat exchange at the downstream end, so that the heat exchange at different positions of the diverter ring is more uniform.

[0069] 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 splitter ring of an aircraft engine, characterized in that: include: A ring body (10) having a gas collecting cavity (101) adapted to its own shape, a rear wall (B) of the ring body (10) being provided with an air inlet (102), a front wall (F) of the ring body (10) being provided with an air outlet (103), the gas collecting cavity (101) being configured to introduce a heating airflow required for heating the ring body (10) through the air inlet (102), and to discharge the heating airflow after heat exchange through the air outlet (103); and A first partition (11) is arranged in the air collecting chamber (101) and corresponds to the position of the air inlet (102). The first partition (11) divides the air collecting chamber (101) into a first sub-chamber (104) and a second sub-chamber (105) arranged along the circumference of the ring body (10), so that the heated airflow can be divided into two flows at the position of the air inlet (102).

2. The flow divider ring according to claim 1, characterized in that: It comprises a second partition (12), wherein two second partitions (12) are respectively arranged in the first sub-chamber (104) and the second sub-chamber (105), and the two second partitions (12) respectively divide the first sub-chamber (104) and the second sub-chamber (105) into two sub-chambers arranged along the axial direction of the ring body (10).

3. The flow divider ring according to claim 2, characterized in that: The second partition (12) is provided with a vent hole (121), and the vent hole (121) communicates with the two sub-cavities.

4. The flow divider ring according to claim 3, characterized in that: Along the circumference of the ring body (10), on a unit area basis, the sum of the flow areas of the ventilation holes (121) located at the upstream end is smaller than the sum of the flow areas of the ventilation holes (121) located at the downstream end.

5. The flow divider ring according to claim 2, characterized in that: In a radial cross section of the ring body (10), the second partition (12) is in a straight line shape, or the second partition (12) is in an arc shape protruding toward the front wall (F) of the ring body (10).

6. The flow divider ring according to claim 2, characterized in that: The second partition (12) is connected to the first partition (11) and extends along the circumference of the ring body (10), and the central angle of the first sub-cavity (104) and the central angle of the second sub-cavity (105) are respectively greater than the central angle of the corresponding second partition (12).

7. The flow divider ring according to any one of claims 1 to 6, characterized in that: Along the circumference of the ring body (10), the flow areas of the first sub-chamber (104) and the second sub-chamber (105) gradually decrease from the upstream end to the downstream end.

8. The flow divider ring according to any one of claims 1 to 6, characterized in that: The invention comprises a third partition (13), wherein the third partition (13) is spaced apart from the first partition (11) along the circumference of the ring body (10), and the first sub-chamber (104) and the second sub-chamber (105) are separated by the third partition (13) at the downstream end.

9. The flow divider ring according to any one of claims 1 to 6, characterized in that: Along the circumference of the ring body (10), on a unit area basis, the sum of the flow areas of the gas outlets (103) located at the upstream end is smaller than the sum of the flow areas of the gas outlets (103) located at the downstream end.

10. An aircraft engine, characterized in that: Comprising the splitter ring according to any one of claims 1 to 9.

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