Aeroengine and splitter ring therefor

Abstract

This disclosure provides an aero-engine and its flow splitter ring. The flow splitter ring includes: a ring body having an air collection chamber adapted to its own shape, an air inlet provided on the rear wall of the ring body, and an air outlet provided on the front wall of the ring body. The air collection chamber is configured to introduce heated airflow required for heating the ring body through the air inlet and to discharge the heated airflow after heat exchange through the air outlet; and a first partition portion disposed within the air collection chamber and corresponding to the position of the air inlet. The first partition portion divides the air collection chamber into a first sub-cavity and a second sub-cavity disposed along the circumference of the ring body, so that the heated airflow can be split into two flows at the position of the air inlet. The aero-engine and its flow splitter ring of this disclosure improve the anti-icing effect of the flow splitter ring by optimizing the anti-icing structure.

Description

Technical Field

[0001] This disclosure relates to the field of aero engines, and in particular to an aero engine and its shunt ring. Background Technology

[0002] In cold weather, the surface of the splitter ring of an aircraft engine is prone to icing. Icing alters the original aerodynamic shape of the splitter ring, potentially causing the engine to deviate from its designed operating state. Icing can also cause uneven circumferential blockage of the intake passages, potentially leading to intake distortion or surge. If the icing is severe, detached ice fragments may be sucked into the engine cavity and collide with the high-speed rotating engine blades, causing structural damage. Current splitter ring anti-icing primarily uses hot gas, but the anti-icing structure itself needs further optimization, and its effectiveness needs improvement. Summary of the Invention

[0003] The purpose of this disclosure is to provide an aero-engine and its shunting ring to optimize the anti-icing structure and improve the anti-icing effect of the shunting ring.

[0004] The first aspect of this disclosure provides a flow splitter ring for an aircraft engine, comprising:

[0005] An annular body has a gas collecting cavity adapted to its own shape. An air inlet is provided on the rear wall of the annular body, and an air outlet is provided on the front wall of the annular body. The gas collecting cavity is configured to introduce a heating airflow required for heating the annular body through the air inlet, and to discharge the heat-exchanged heating airflow through the air outlet.

[0006] A first partition is disposed within the gas collecting chamber and corresponds to the position of the air inlet. The first partition divides the gas collecting chamber into a first sub-chamber and a second sub-chamber arranged circumferentially along the ring body, so that the heated airflow can be split into two streams at the position of the air inlet.

[0007] According to some embodiments of this disclosure, a second partition is included, with two second partitions respectively disposed within the first cavity and the second cavity, the two second partitions dividing the first cavity and the second cavity into two sub-cavities disposed along the axial direction of the ring body.

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

[0009] According to some embodiments of this disclosure, along the circumference of the ring body, the sum of the flow areas of each of the vents located at the upstream end is less than the sum of the flow areas of each of the vents located at the downstream end per unit area.

[0010] According to some embodiments of this disclosure, in the radial cross-section of the ring body, the second partition is straight, or the second partition is arc-shaped protruding toward the front wall of the ring body.

[0011] According to some embodiments of this disclosure, the second partition is connected to the first partition and extends circumferentially along the ring body, and the central angle of the first cavity and the central angle of the second cavity are respectively greater than the central angle of the corresponding second partition.

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

[0013] According to some embodiments of this disclosure, a third partition is included along the circumference of the ring body, the third partition being spaced apart from the first partition, and the first cavity and the second cavity being separated by the third partition at their downstream ends.

[0014] According to some embodiments of this disclosure, along the circumference of the ring body, the sum of the flow areas of each of the air outlets located at the upstream end is less than the sum of the flow areas of each of the air outlets located at the downstream end per unit area.

[0015] A second aspect of this disclosure provides an aircraft engine including the shunt ring described in the first aspect of this disclosure.

[0016] When the airflow of the aero-engine disclosed herein is in operation, the heated airflow can be directly introduced into the air collection chamber inside the ring body through the air inlet. Under the action of the first partition, the airflow is divided into two paths along the circumference of the ring body in the first and second partition chambers and exchanges heat with the airflow. This can heat the airflow and prevent external water vapor from freezing on the surface of the airflow. The airflow after heat exchange can be discharged through the air outlet and merge into the mainstream of the aero-engine.

[0017] Based on the above structure, the heated airflow can directly enter the air collecting chamber through the air inlet and exchange heat with the flow divider ring, without the need to install an air supply pipeline in the air collecting chamber. This helps to optimize the anti-icing structure of the flow divider ring from the perspectives of simplifying the air supply pipeline, reducing additional heat dissipation, and reducing weight.

[0018] The aero-engine disclosed herein has the advantages of the aforementioned flow divider ring.

[0019] Other features and advantages of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0020] The accompanying drawings, which are included to provide a further understanding of this disclosure and form part of this application, illustrate exemplary embodiments of this disclosure and are used to explain this disclosure, but do not constitute an undue limitation of this disclosure. In the drawings:

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

[0022] Figure 2 This is a schematic diagram of the heating airflow path of a flow divider ring according to some embodiments of the present disclosure, wherein the flow divider ring is deployed circumferentially.

[0023] Figure 3 This is a radial cross-sectional view of a splitter ring according to some embodiments of the present disclosure, wherein the cut does not pass through the air inlet.

[0024] Figure 4 This is a radial cross-sectional view of the splitter ring according to some other embodiments of the present disclosure, wherein the cut does not pass through the air inlet.

[0025] Figures 1 to 4 In the figures, the labels represent:

[0026] 1. Diverter ring; 10. Ring body; 101. Gas collection 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 hole; 13. Third partition; B. Rear wall; F. Front wall;

[0027] 2. Air evacuation pipeline;

[0028] 3. The inner meaning of Tao;

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

[0030] 6. High-pressure air compressor. Detailed Implementation

[0031] The technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this disclosure, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this disclosure or its application or use. All other embodiments obtained by those skilled in the art based on the embodiments of this disclosure without creative effort are within the scope of protection of this disclosure.

[0032] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of this disclosure. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0033] In the description of this disclosure, it should be understood that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this disclosure.

[0034] In the description of this disclosure, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings and is only for the convenience of describing this disclosure and simplifying the description. Unless otherwise stated, these directional terms 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 should not be construed as a limitation on the scope of protection of this disclosure; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0035] Embodiments of this disclosure provide an aero-engine and a flow divider ring thereof.

[0036] The aero-engine provided in the embodiments of this disclosure includes the flow divider ring provided in the embodiments of this disclosure and has the advantages of the flow divider ring. Reference is made below. Figures 1 to 4 The shunt ring provided in the embodiments of this disclosure is described.

[0037] The flow divider ring includes a ring body 10 and a first dividing portion 11. The ring body 10 has a gas collecting cavity 101 adapted to its own shape. An air inlet 102 is provided on the rear wall B of the ring body 10, and an air outlet 103 is provided on the front wall F of the ring body 10. 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 to discharge the heat-exchanged heating airflow through the air outlet 103. The first dividing portion 11 is provided in the gas collecting cavity 101 and corresponds to the position of the air inlet 102. The first dividing portion 11 divides the gas collecting cavity 101 into a first compartment 104 and a second compartment 105 arranged circumferentially along the ring body 10, so that the heating airflow can be split into two flows at the position of the air inlet 102.

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

[0039] When the airflow of the aero-engine provided in the embodiments of this disclosure is in operation, the heated airflow can be directly introduced into the air collection chamber inside the ring body through the air inlet. Under the action of the first partition, the airflow is divided into two paths along the circumference of the ring body in the first and second partition chambers and exchanges heat with the airflow ring. This can heat the airflow ring and prevent external water vapor from freezing on the surface of the airflow ring. The airflow after heat exchange can be discharged through the air outlet and merge into the mainstream of the aero-engine.

[0040] Based on the above structure, the heated airflow can directly enter the gas collection chamber through the air inlet, flow along the circumference of the ring and exchange heat with the distribution ring. There is no need to set up distribution pipes extending along the circumference of the distribution ring, or distribution pipes connecting the distribution pipes and the gas collection chamber on the outside of the distribution ring. This helps to optimize the anti-icing structure of the distribution ring from the perspectives of simplifying the gas supply pipeline, reducing additional heat dissipation and reducing weight.

[0041] Figure 2 This is a schematic diagram of the heating airflow path of the flow divider ring according to some embodiments of the present disclosure, wherein, along the circumference of the ring body 10, the flow divider ring gradually expands from the middle to both sides at the air inlet 102. Figure 2 In the diagram, the left-right direction represents the circumference of the annular body 10, the up-down direction represents the axial direction of the annular body 10, and the arrow direction indicates the flow direction of the heating gas flow. In this disclosure, the descriptions of "upstream end" and "downstream end" are based on the flow direction of the heating gas flow.

[0042] The following is combined with Figure 2 The structure and working principle of the shunt ring in some embodiments of this disclosure are further explained.

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

[0044] refer to Figure 2 A second partition 12 disposed within the first cavity 104 divides the first cavity 104 into a first sub-cavity 104a located near the rear wall B and a second sub-cavity 104b located near the front wall F. A second partition 12 disposed within the second cavity 105 divides the second cavity 105 into a first sub-cavity 105a located near the rear wall B and a second sub-cavity 105b located near the front wall F.

[0045] In the above embodiment of the flow divider ring, 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 chamber from directly impacting the front wall of the ring body, and can also change the flow direction of the heated airflow from axial to circumferential, thereby weakening the heat exchange near the air inlet of the gas collecting chamber and preventing overheating at this point. Furthermore, due to the setting of the second partition, there is no need to further set up a heating airflow distribution pipeline inside the gas collecting chamber, which helps to simplify the gas supply pipeline.

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

[0047] By providing vent holes on the second partition, after the heated airflow enters the air collecting chamber through the air inlet, most of it is blocked by the second partition into the first sub-cavity corresponding to the first or second sub-cavity. A small portion can enter the second sub-cavity corresponding to the first or second sub-cavity through the vent holes, which helps to keep the temperature of the second sub-cavity at the upstream end within a suitable range, thereby improving the anti-icing effect at the corresponding location.

[0048] In some embodiments, along the circumference of the ring 10, the sum of the flow areas of each vent 121 located at the upstream end is less than the sum of the flow areas of each vent 121 located at the downstream end per unit area.

[0049] The sum of the flow areas of each vent per unit area can be adjusted by adjusting the vent diameter or the density of the vents. Optionally, along the circumference of the annulus 10, the sum of the flow areas of each vent 121 per unit area gradually increases.

[0050] For the flow divider ring in the above embodiment, as the heating gas flows and exchanges heat in the ring, the temperature of the heating gas gradually decreases. However, the flow rate of the heating gas entering the second sub-cavity from the first sub-cavity can be increased accordingly. Furthermore, during the process of the heating gas entering the second sub-cavity from the first sub-cavity, the throttling and deceleration effect of the vent on the heating gas is small, which is conducive to enhancing the heat exchange at the downstream end, so that the heat exchange at different positions of the flow divider ring is more uniform.

[0051] In some embodiments, reference Figure 3 On the radial section of the ring 10, the second partition 12 is straight.

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

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

[0054] Compared to a straight second partition, an arc-shaped second partition protruding towards the front wall reduces the contact area between the heated airflow and the inner wall of the corresponding first sub-cavity of the first or second partition. This design not only reduces heat loss from the heated airflow in the corresponding first sub-cavity, thus providing insulation and maintaining a higher temperature as the heated airflow flows downstream, thereby reducing the upstream-downstream temperature difference and making the circumferential temperature distribution of the annulus more uniform, but also prevents overheating at the corresponding location on the inner wall of the first sub-cavity.

[0055] Furthermore, for the arc-shaped second partition, there are more positions available for opening vents, and the setting of vents is more flexible. Vents can not only be set towards the front wall of the ring, but also towards the circumferential surface of the radial inner or outer side of the gas collecting cavity. Based on the different orientations of the vents, the flow direction of the heating airflow in the gas collecting cavity can be further optimized.

[0056] Optionally, in the radial cross-section of the ring 10, the second partition 12 is U-shaped, and both ends of the second partition 12 are connected to the rear wall B. This avoids direct heat exchange between the heated airflow and the wall surface located radially inside or outside the gas collecting cavity, further improving the heat preservation effect of the heated airflow in the first sub-cavity.

[0057] Therefore, the aforementioned arc-shaped second partition can improve the utilization efficiency of the heating airflow and reduce the amount of heating airflow used.

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

[0059] In the flow splitting ring of the above embodiment, the first sub-cavity and the second sub-cavity corresponding to the first or second splitting cavity are separated by the second partition at the upstream end, and the first and second sub-cavities can be connected through the vent hole; while the first and second sub-cavities corresponding to the first or second splitting cavity are directly connected at the downstream end, and the heating airflow in the first and second sub-cavities merges into one stream.

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

[0062] For the flow divider ring in the above embodiment, as the heating gas flows and exchanges heat in the ring, the temperature of the heating gas gradually decreases. However, the flow velocity of the heating gas entering the second sub-cavity from the first sub-cavity can increase accordingly as the flow area of ​​the first and second sub-cavities decreases, which is beneficial to enhance the heat exchange at the downstream end and make the heat exchange at different positions of the flow divider ring more uniform.

[0063] In some embodiments, reference Figure 2 The diversion ring includes a third partition 13 along the circumference of the ring body 10. The third partition 13 is spaced apart from the first partition 11. The first partition 104 and the second partition 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 each other along the circumference of the ring body 10, and the first cavity 104 and the second cavity 105 are symmetrically arranged. Optionally, along the circumference of the ring body 10, the second partition 12 is connected to the first partition 11 at its upstream end, and is spaced apart from the third partition 13 at its downstream end.

[0065] By setting a third partition, the first and second chambers are not connected to each other at the downstream end, which can prevent the heated airflow in the first and second chambers from colliding with each other at the downstream end and causing pressure loss, thus reducing the adverse effect on the anti-icing effect.

[0066] In some embodiments, along the circumference of the ring 10, the sum of the flow areas of each air outlet 103 located at the upstream end is less than the sum of the flow areas of each air outlet 103 located at the downstream end per unit area.

[0067] The sum of the flow areas of each air outlet per unit area can be adjusted by adjusting the diameter of the air outlet or the distribution density of the air outlet. Optionally, along the circumference of the annulus 10, the sum of the flow areas of each air outlet 103 per unit area gradually increases.

[0068] For the flow divider ring in the above embodiment, as the heating gas flows and exchanges heat in the ring, the temperature of the heating gas gradually decreases, but the flow rate of the heating gas flowing out of the gas 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 flow divider ring is more uniform.

[0069] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this disclosure and not to limit them; although this disclosure has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of this disclosure or equivalent substitutions can be made to some technical features, all of which should be covered within the scope of the technical solutions claimed in this disclosure.

Claims

1. A flow splitter ring for an aero-engine, characterized in that, include: The ring (10) has a gas collecting cavity (101) adapted to its own shape. The rear wall (B) of the ring (10) is provided with an air inlet (102), and the front wall (F) of the ring (10) is provided with an air outlet (103). The gas collecting cavity (101) is configured to introduce the heating airflow required to heat the ring (10) through the air inlet (102) and discharge the heat-exchanged heating airflow through the air outlet (103). A first partition (11) is disposed within the gas collecting chamber (101) and corresponds to the position of the air inlet (102). The first partition (11) divides the gas collecting chamber (101) into a first sub-chamber (104) and a second sub-chamber (105) arranged circumferentially along the annulus (10), so that the heated airflow can be split into two streams at the position of the air inlet (102); and The second partition (12) is disposed in the first cavity (104) and the second cavity (105) respectively. The two second partitions (12) divide the first cavity (104) and the second cavity (105) into two sub-cavities disposed along the axial direction of the ring body (10).

2. The shunt ring according to claim 1, characterized in that, The second partition (12) is provided with a vent (121), which connects the two sub-cavities.

3. The shunt ring according to claim 2, characterized in that, Along the circumference of the ring (10), the sum of the flow areas of each of the vents (121) located at the upstream end per unit area is less than the sum of the flow areas of each of the vents (121) located at the downstream end.

4. The shunt ring according to claim 1, characterized in that, On the radial cross section of the ring (10), the second partition (12) is straight, or the second partition (12) is arc-shaped and protrudes toward the front wall (F) of the ring (10).

5. The shunt ring according to claim 1, characterized in that, The second partition (12) is connected to the first partition (11) and extends circumferentially along the ring (10). The central angle of the first cavity (104) and the central angle of the second cavity (105) are respectively greater than the central angle of the corresponding second partition (12).

6. The shunt ring according to any one of claims 1 to 5, characterized in that, Along the circumference of the ring (10), the flow area of ​​the first cavity (104) and the second cavity (105) gradually decreases from the upstream end to the downstream end.

7. The shunt ring according to any one of claims 1 to 5, characterized in that, Includes a third partition (13) along the circumference of the ring body (10), the third partition (13) is spaced apart from the first partition (11), and the first cavity (104) and the second cavity (105) are separated by the third partition (13) at the downstream end.

8. The shunt ring according to any one of claims 1 to 5, characterized in that, Along the circumference of the ring (10), the sum of the flow areas of each of the air outlets (103) located at the upstream end per unit area is less than the sum of the flow areas of each of the air outlets (103) located at the downstream end.

9. An aircraft engine, characterized in that, Includes the shunt ring according to any one of claims 1 to 8.

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