Radial backflow type transition section structure of turbine engine and turbine engine
By designing a radial recirculation transition section structure in the turbine engine, the flow path matching problem was solved, achieving uniform airflow distribution, reducing flow losses, and improving turbine efficiency and output power.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-01-13
- Publication Date
- 2026-04-10
AI Technical Summary
In the prior art, the transition section structure of the turbine engine cannot effectively match the flow path between the rotor and the turbine, resulting in uneven flow, reduced efficiency and increased flow losses.
A radial recirculation transition section structure is designed, including a centrifugal section, an axial section, and a centripetal section. Through a segmented progressive expansion structure, the airflow undergoes radial inflow, axial transition, and reverse radial outflow within the transition section, ensuring that the airflow is evenly distributed before entering the turbine and avoiding flow separation and vibration.
It achieves a precise connection between the wave rotor and the turbine, reduces flow losses, provides uniform intake conditions, and improves the turbine's operating efficiency and output power.
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Figure CN121828008A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of turbine engine technology, and in particular to a radial return flow transition section structure for a turbine engine and a turbine engine. Background Technology
[0002] The turbine engine is a core component of an aircraft. With the introduction of pressurized combustion technology, the isobaric endothermic cycle is transformed into a near-isochoric endothermic cycle, significantly improving cycle thermal efficiency. The wave rotor is a highly efficient energy conversion device that uses unsteady waves to transfer and convert energy, possessing advantages such as self-cooling, stable intake and exhaust, high efficiency, and fast dynamic response. The wave rotor is located upstream of the turbine. However, the wave rotor outlet is not a full-ring exhaust; it is in a partial exhaust state. The downstream turbine, on the other hand, has a full-ring intake.
[0003] To achieve flow path matching between the wave rotor and turbine, related technologies incorporate a transition section between the wave rotor outlet and turbine inlet, effectively converting the turbine inlet into a partial intake. This matches the turbine intake state with the wave rotor outlet state. However, this leads to uneven flow within the turbine, reducing turbine efficiency and output power. Based on this, another approach involves designing the transition section as a full annular structure. While this ensures sufficient turbine intake area, it results in a flow path mismatch between the wave rotor outlet and the transition section inlet. Sudden structural expansion can also cause large-scale flow separation, leading to significant flow losses. Summary of the Invention
[0004] To solve the above-mentioned technical problems, or at least partially solve them, embodiments of this application provide a radial recirculation transition section structure for a turbine engine and a turbine engine, which can both match the exhaust at the rotor outlet with the turbine's full-ring intake and effectively suppress flow losses.
[0005] In a first aspect, embodiments of this application provide a radial recirculation transition section structure for a turbine engine, the transition section structure being connected between the turbine rotor and the turbine of the turbine engine; The transition section structure includes a body, which has an airflow channel, and the airflow channel includes a centrifugal section, an axial section and a centripetal section connected in sequence. The centrifugal section extends radially away from the axis of the body. The inlet of the airflow channel is located at one end of the centrifugal section near the axis. The inlet is an arc-shaped inlet that matches the outlet of the wave rotor. The circumferential opening angle of the centrifugal section gradually increases along its extension direction. The axial segment extends along the axial direction of the body from the end of the centrifugal segment away from the axis, and the circumferential opening angle of the axial segment remains unchanged or gradually increases along the extension direction of the axial segment. The centripetal segment is an annular segment extending radially toward the axis of the body from the end of the axial segment away from the centrifugal segment. The end of the centripetal segment near the axis forms the outlet of the airflow channel, and the outlet is an annular outlet centered on the axis of the body and adapted to the air intake end of the turbine. The circumferential opening angle of the centripetal segment gradually increases along the extension direction of the centripetal segment.
[0006] Optionally, along the extension direction of the centrifugal segment, the circumferential expansion ratio of the circumferential opening angle of the centrifugal segment ranges from 2.5 to 3. And / or, the axial width of the centrifugal segment remains unchanged along the extension direction of the centrifugal segment.
[0007] Optionally, in the extension direction of the axial segment, the circumferential expansion ratio of the circumferential opening angle of the axial segment ranges from 1 to 1.05.
[0008] Optionally, along the extension direction of the centripetal segment, the circumferential expansion ratio of the circumferential opening angle of the centripetal segment ranges from 1.2 to 1.5. And / or, the axial width of the centripetal segment remains unchanged along the extension direction of the centripetal segment.
[0009] Optionally, the axial width of the centrifugal section is greater than the axial width of the centripetal section.
[0010] Optionally, the area of the outlet is smaller than the area of the import.
[0011] Optionally, the centrifugal section, axial section, and centripetal section are all surface-symmetrical structures.
[0012] Optionally, the ratio of the circumferential opening angle of the outlet to the circumferential opening angle of the inlet is in the range of 3 to 4.
[0013] Optionally, the body includes at least two circulating units, which are arranged sequentially along the circumference of the axis. Each of the aforementioned circulation units includes a sub-centrifugal segment, a sub-axial segment, and a sub-centripetal segment connected in sequence; the sub-centrifugal segment extends radially away from the axis of the body, the sub-axial segment extends axially from the end of the sub-centrifugal segment away from the axis of the body, and the sub-centripetal segment extends from the end of the sub-axial segment away from the sub-centrifugal segment towards the axis of the body. Each of the centrifugal segments of the circulation unit has an inlet, and the end of each centripetal segment near the axis is formed into an arc-shaped sub-outlet. The arc-shaped sub-outlets of all the centripetal segments are sequentially assembled along the circumference of the axis to form the outlet.
[0014] Secondly, embodiments of this application provide a turbine engine, including a wave rotor, a turbine, and a transition section structure of the turbine engine as described above.
[0015] The radial return flow transition section structure and turbine engine provided in this application are characterized by the following: the transition section structure includes a body, and the airflow passage of the body includes a centrifugal section, an axial section, and a centripetal section connected in sequence. The centrifugal section extends radially away from the axis of the body, and the inlet of the airflow passage is located at the end of the centrifugal section near the axis. The inlet is an arc-shaped inlet adapted to the exhaust end of the wave rotor, and the circumferential opening angle of the centrifugal section gradually increases. The axial section extends axially from the end of the centrifugal section away from the axis along the axis of the body. The circumferential opening angle of the axial section remains unchanged or gradually increases. The centripetal section is an annular section extending radially towards the axis of the body. The end of the centripetal section near the axis forms the outlet of the airflow passage. The outlet is an annular outlet adapted to the turbine intake end, and the circumferential opening angle of the centripetal section gradually increases. In other words, the inlet of the transition section structure is adapted to the outlet of the wave rotor, and the outlet of the transition section structure is adapted to the full-ring inlet of the turbine. The airflow channel guides the working gas to complete a 180° flow deflection, radial inflow, axial transition, and reverse radial outflow. In the initial centrifugal section of the flow, the airflow can initially expand circumferentially, preparing for the subsequent large-scale expansion and avoiding sudden expansion. In the axial section where the airflow turns, the circumferential opening angle is maintained or gradually increased to provide a stable turning channel for the airflow and reduce the disturbance caused by the change in flow direction. In the centripetal section at the end of the flow, the airflow continues to expand moderately, so that the airflow can be more evenly distributed circumferentially before entering the turbine. This achieves a precise connection and flow path connection between the transition section structure and the upstream wave rotor and downstream turbine, and avoids flow separation caused by structural abrupt changes to a certain extent. Through this segmented and progressive expansion structure, the flow separation and vibration caused by sudden expansion of the working gas are effectively suppressed, and a smooth transition from partial intake of the wave rotor to full-ring intake of the turbine is achieved. While achieving flow path matching, the flow loss is greatly reduced, and uniform intake conditions are provided for the turbine. Attached Figure Description
[0016] Figure 1 This is a schematic diagram of the radial recirculation transition section structure of a turbine engine according to an embodiment of this application; Figure 2 for Figure 1 A cross-sectional schematic diagram; Figure 3 This is a schematic cross-sectional view of the sub-centrifuge section according to an embodiment of this application; Figure 4 This is a schematic cross-sectional view of the axial segment described in one embodiment of this application; Figure 5 This is a schematic cross-sectional view of the sub-centripetal segment according to an embodiment of this application.
[0017] Explanation of reference numerals in the attached figures: 100. Transition section structure; 1. Body; 10. Axis; 11. Airflow channel; 111. Inlet; 112. Outlet; 12. Centrifugal section; 121. Sub-centrifugal section; 13. Axial section; 131. Sub-axial section; 14. Centripetal section; 141. Sub-centripetal section; 1411. Arc-shaped sub-outlet; 15. Circulation unit. Detailed Implementation
[0018] The present application will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the application and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present application, not the entire structure.
[0019] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to". The concepts of "first," "second," etc., used in this application are only used to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies. It should be noted that the modifications "a" or "a plurality of" used in this application are illustrative rather than restrictive, and those skilled in the art should understand that, unless explicitly stated in the context, they should be understood as "one or more".
[0020] Reference Figures 1 to 5 As shown, this application embodiment provides a radial return transition section structure 100 for a turbine engine, the turbine engine including a wave rotor and a turbine, the transition section structure 100 being connected between the wave rotor and the turbine of the turbine engine.
[0021] The transition section structure 100 includes a body 1, which has an airflow channel 11. The airflow channel 11 includes a centrifugal section 12, an axial section 13, and a centripetal section 14 connected in sequence.
[0022] The centrifugal section 12 extends radially along the body 1 towards the axis 10 away from the body 1. The inlet 111 of the airflow channel 11 is located at one end of the centrifugal section 12 near the axis 10, and the inlet 111 is an arc-shaped inlet adapted to the outlet end of the wave rotor. Figures 1 to 3 As shown, the circumferential opening angle of the centrifugal segment 12 gradually increases along the extension direction of the centrifugal segment 12.
[0023] The axial segment 13 extends along the axial direction of the body 1 from the end of the centrifugal segment 12 away from the axis 10. In the direction of extension of the axial segment 13, the circumferential opening angle of the axial segment 13 remains unchanged or gradually increases.
[0024] The centripetal segment 14 is an annular segment extending radially from the end of the axial segment 13 away from the centrifugal segment 12 towards the axis 10. The end of the centripetal segment 14 near the axis 10 forms the outlet 112 of the airflow passage 11, and the outlet 112 is an annular outlet centered on the axis 10 of the body 1 and adapted to the turbine's inlet. Figure 1 and Figure 5 As shown, the circumferential opening angle of the centripetal segment 14 gradually increases along the extension direction of the centripetal segment 14.
[0025] In other words, the inlet 111 of the airflow passage 11 (the inlet of the centrifugal section 12) is matched and connected to the outlet end of the upstream wave rotor, and the outlet 112 of the airflow passage 11 (the outlet of the centripetal section 14) is matched and connected to the inlet end of the downstream turbine. The inlet of the axial section 13 is connected to the outlet of the centrifugal section 12, and the inlet of the centripetal section 14 is connected to the outlet of the axial section 13.
[0026] Figure 1 and Figure 2 The direction indicated by the dashed arrow is the flow direction of the gaseous working medium. Specifically, the gas discharged from the outlet end of the wave rotor enters the airflow channel 11 of the transition section structure 100 through the arc-shaped inlet 111. The gas entering from the inlet 111 flows along the extension direction of the centrifugal section 12 (radial direction of the body 1) in a direction away from the axis 10 of the body 1. As the circumferential opening angle of the centrifugal section 12 gradually increases, the airflow undergoes initial circumferential expansion within the centrifugal section 12, and then turns backward from the outlet end of the centrifugal section 12 (i.e., the end of the centrifugal section 12 away from the axis 10). Entering the axial section 13, the airflow flows along the extension direction of the axial section 13 (the axial direction of the body 1). When the airflow flows in the axial section 13, it can maintain or slightly increase the circumferential dimension. Then, it turns from the outlet end of the axial section 13 (i.e. the end of the axial section 13 away from the centrifugal section 12) and enters the centripetal section 14. It flows along the extension direction of the centripetal section 14 (the radial direction of the body 1) towards the direction close to the axis 10. The airflow continues to gradually expand in the centripetal section 14 and finally flows out from the annular outlet 112 of the airflow channel 11, and then enters the turbine from the inlet end of the downstream turbine.
[0027] The radial recirculation transition section structure 100 of the turbine engine provided in this embodiment, through the above-described configuration, allows the inlet 111 of the transition section structure 100 to be adapted to the outlet end of the wave rotor, and the outlet 112 of the transition section structure 100 to be adapted to the full-ring inlet end of the turbine. The airflow channel 11 guides the gas working fluid to complete a 180° flow deflection, radial inflow, axial transition, and reverse radial outflow. In the initial centrifugal section 12, the airflow begins to expand circumferentially, preparing for subsequent large-scale expansion and avoiding a sudden one-time expansion. In the axial section 13 where the airflow turns, the circumferential opening angle is maintained or gradually increased to provide a stable airflow. The diversion channel reduces disturbances caused by changes in flow direction; the centripetal section 14 at the end of the flow continues to expand moderately, allowing the airflow to be more evenly distributed circumferentially before entering the turbine. This achieves precise connection and flow path connection between the transition section structure 100 and the upstream wave rotor and downstream turbine, and to a certain extent avoids flow separation caused by abrupt structural changes. Through this segmented and progressive expansion structure, the flow separation and vibration caused by the sudden expansion of the working gas are effectively suppressed, and a smooth transition from partial air intake of the wave rotor to full-circumference air intake of the turbine is achieved. While achieving flow path matching, the flow loss is greatly reduced, providing uniform air intake conditions for the turbine.
[0028] In some embodiments, the circumferential expansion ratio of the circumferential opening angle of the centrifugal segment 12 in the extension direction of the centrifugal segment 12 (i.e., in the radial direction of the body 1 and in the direction away from the axis 10 of the body 1) ranges from 2.5 to 3.
[0029] It is understandable that the circumferential expansion ratio of the circumferential opening angle of the centrifugal section 12 can be specifically: the ratio between the opening angle of the outlet end of the centrifugal section 12 (i.e. the end of the centrifugal section 12 away from the axis 10) in the circumferential direction of the centrifugal section 12 and the opening angle of the inlet 111 in the circumferential direction of the centrifugal section 12.
[0030] Reference Figure 1 and Figure 3 As shown, the circumferential opening angle at the outlet end of centrifugal section 12 is significantly larger than the circumferential opening angle at the inlet end (inlet 111) of centrifugal section 12.
[0031] For example, the circumferential expansion ratio of the circumferential opening angle of the centrifugal segment 12 can be 2.5, 2.6, 2.7, 2.8, 2.9, or 3.
[0032] By setting the circumferential expansion ratio of the circumferential opening angle of the centrifugal section 12 within the above range, the initial circumferential opening expansion of the centrifugal section 12 is achieved, laying the foundation for the full-circumferential expansion of the subsequent centripetal section 14. Moreover, within the above range, flow separation caused by excessive expansion can be effectively avoided, and the gas flow state of the centrifugal section 12 can be better controlled.
[0033] Reference Figure 2As shown, in some embodiments, along the extension direction of the centrifugal segment 12 (e.g.) Figure 2 (In the direction from bottom to top), the axial width H of the centrifugal section 12 (the width of the centrifugal section 12 along the axial direction of the body) remains unchanged.
[0034] In other words, the axial width H of the centrifugal segment 12 is equal at different positions in its extension direction.
[0035] This configuration effectively ensures the axial stability of the working fluid flow cross section within the centrifugal section 12, avoids sudden changes in flow velocity caused by width variations, further suppresses flow separation, improves flow smoothness, and further reduces flow loss.
[0036] In some embodiments, in the extending direction along the axial segment 13 (e.g. Figure 2 In the direction from left to right, the circumferential expansion ratio of the circumferential opening angle of the axial segment 13 ranges from 1 to 1.05.
[0037] It is understandable that the circumferential expansion ratio of the circumferential opening angle of the axial segment 13 can be specifically: the ratio between the opening angle of the outlet end of the axial segment 13 (i.e., the end of the axial segment 13 away from the centrifugal segment 12) in the circumferential direction of the axial segment 13 and the opening angle of the inlet end of the axial segment 13 (i.e., the end connected to the outlet end of the centrifugal segment 12) in the circumferential direction of the axial segment 13.
[0038] Combination Figure 1 and Figure 4 As shown, the circumferential opening angle at the outlet end of the axial segment 13 is basically consistent with the circumferential opening angle at the inlet end of the axial segment 13.
[0039] That is, when the circumferential opening angle of the outlet end of the axial segment 13 is the same as the circumferential opening angle of the inlet end of the axial segment 13, the circumferential expansion ratio of the circumferential opening angle of the axial segment 13 is 1.
[0040] When the circumferential opening angle at the outlet end of the axial segment 13 is greater than the circumferential opening angle at the inlet end of the axial segment 13, the circumferential expansion ratio of the circumferential opening angle of the axial segment 13 is greater than 1.
[0041] For example, the circumferential expansion ratio of the circumferential opening angle of the axial segment 13 can be 1, 1.01, 1.02, 1.03, 1.04, or 1.05.
[0042] By keeping the circumferential opening angle of the axial section 13 essentially unchanged or slightly increased, abrupt changes in flow parameters within the axial section 13 are avoided, thereby further maintaining the uniformity of the working fluid flow, providing a smooth transition for the expansion of the centrifugal section 12 and the centripetal section 14, reducing flow disturbances at the flow channel turning point, and further suppressing flow separation.
[0043] In some embodiments, the circumferential expansion ratio of the circumferential opening angle of the centripetal segment 14 in the extension direction of the centripetal segment 14 (i.e., in the radial direction of the body 1 and toward the axis 10 close to the body 1) ranges from 1.2 to 1.5.
[0044] It is understandable that the circumferential expansion ratio of the circumferential opening angle of the centripetal segment 14 can be specifically: the ratio between the opening angle of the outlet end of the centripetal segment 14 (i.e., the outlet 112 of the airflow channel 11) in the circumferential direction of the centripetal segment 14 and the opening angle of the inlet end of the centripetal segment 14 (i.e., the end of the centripetal segment 14 away from the axis 10) in the circumferential direction of the centripetal segment 14.
[0045] Reference Figure 1 and Figure 5 As shown, the circumferential opening angle at the outlet end of the centripetal section 14 is significantly larger than the circumferential opening angle at the inlet end of the centripetal section 14.
[0046] For example, the circumferential expansion ratio of the circumferential opening angle of the centripetal segment 14 can be 1.2, 1.3, 1.35, 1.4, or 1.5.
[0047] By setting the circumferential expansion ratio of the opening angle of the centripetal section 14 within the above range, it is possible to better adapt to the turbine's full-ring intake requirements, improve the uniformity of the flow field at the outlet 112, and avoid uneven intake caused by insufficient expansion or flow separation caused by excessive expansion.
[0048] In some embodiments, along the extension direction of the centripetal segment 14 (e.g. Figure 2 In the direction from top to bottom, the axial width h of the centripetal segment 14 (the width of the centripetal segment 14 along the axial direction of the body) remains unchanged.
[0049] In other words, the axial width h of the centripetal segment 14 is equal at different positions in its extension direction.
[0050] This configuration ensures the axial stability of the working fluid flow within the centripetal section 14, guides the working fluid to converge smoothly along the counter-radial direction, avoids eddies caused by width changes, and further reduces flow losses.
[0051] Reference Figure 2 As shown, in some embodiments, the axial width H of the centrifugal section 12 is greater than the axial width h of the centripetal section 14.
[0052] This configuration creates a gradual change in cross-section, with a wider centrifugal section 12 and a narrower centripetal section 14. This guides the working fluid to gradually contract within the centripetal section 14, increasing the flow velocity of the working fluid within the centripetal section 14 and thus ensuring the turbine's intake efficiency.
[0053] In some embodiments, the area of the outlet 112 is smaller than the area of the inlet 111.
[0054] By making the flow area of outlet 112 smaller than that of inlet 111, a flow condition with slightly accelerated flow at outlet 112 is created, which is beneficial to improving the kinetic energy and anti-separation capability of the airflow at the turbine inlet.
[0055] Continue to refer to Figures 1 to 5 As shown, in some embodiments, the centrifugal section 12, the axial section 13, and the centripetal section 14 are all surface-symmetrical structures.
[0056] This configuration can, to a certain extent, ensure the consistency of parameters such as velocity and pressure of the working fluid on both sides of the flow channel, avoid the generation of flow deviation and eddies, further suppress flow separation, reduce flow losses, and provide stable and uniform intake conditions for the turbine.
[0057] In some embodiments, the ratio of the circumferential opening angle of the outlet 112 to the circumferential opening angle of the inlet 111 ranges from 3 to 4.
[0058] The segmented expansion achieves the transition from small opening angle partial air intake to 360° full annular air intake, avoiding large-scale flow separation caused by sudden expansion full annular transition section. As shown above, while meeting the requirements of large expansion ratio, it effectively suppresses flow loss.
[0059] Combination Figures 1 to 5 As shown, in some embodiments, the body 1 includes at least two loop units 15, which are arranged sequentially along the circumference of the axis 10.
[0060] Each circulation unit 15 includes a sub-centrifugal segment 121, a sub-axial segment 131, and a sub-centripetal segment 141 connected in sequence. The sub-centrifugal segment 121 extends radially away from the axis 10 of the body 1, the sub-axial segment 131 extends axially from the end of the sub-centrifugal segment 121 away from the axis 10 of the body 1, and the sub-centripetal segment 141 extends from the end of the sub-axial segment 131 away from the sub-centrifugal segment 121 towards the axis 10.
[0061] Each centrifugal segment 121 of each circulation unit 15 has an inlet 111, and the end of each centripetal segment 141 near the axis 10 is formed as an arc-shaped sub-outlet 1411. The arc-shaped sub-outlets 1411 of all the centripetal segments 141 are sequentially assembled along the circumference of the axis 10 to form an outlet 112.
[0062] This improves the compatibility between the transition section structure 100 and the multi-channel exhaust structure of the wave rotor. By splicing multiple arc-shaped sub-outlets 1411 circumferentially to form a total annular outlet 112, the continuity and uniformity of the turbine inlet's full-annular intake are ensured.
[0063] Reference Figure 1As shown, for example, there are two circulation units 15, which are symmetrically arranged. The centrifugal segment 12 includes two sub-centrifugal segments 121, and the circumferential opening angle of each sub-centrifugal segment 121 gradually increases. The axial segment 13 includes two sub-axial segments 131, and the circumferential opening angle of each sub-axial segment 131 remains unchanged or gradually increases. The centripetal segment 14 includes two sub-centripetal segments 141, and the circumferential opening angle of each sub-centripetal segment 141 gradually increases.
[0064] This configuration improves the uniformity of airflow distribution, thereby further suppressing flow separation and reducing flow losses.
[0065] Of course, in other implementations, the cyclic unit 15 can also be three, four or more, depending on the specific structure of the wave rotor, etc.
[0066] This application also provides a turbine engine, which can be used, for example, in an aircraft.
[0067] The turbine engine includes a wave rotor, a turbine, a transition section structure 100, and a tail nozzle. The transition section structure 100 is connected between the wave rotor and the turbine, and the tail nozzle is located at the exhaust end of the turbine.
[0068] The high-temperature, high-pressure gas discharged from the wave rotor enters through the inlet 111 of the transition section structure 100, flows along the airflow channel 11, and flows out through the outlet 112 of the airflow channel 11 to the turbine, driving the turbine to rotate and causing the gas to be ejected through the tail nozzle, thereby providing thrust for the aircraft to fly.
[0069] The transition segment structure 100 in this embodiment has the same specific structure and implementation principle as the transition segment structure 100 provided in the above embodiments, and can bring the same or similar technical effects. It will not be described in detail here, but can be referred to the description of the above embodiments.
[0070] The above description is merely an embodiment of this application and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of disclosure in this application is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features with similar functions disclosed in this application.
Claims
1. A radial recirculation transition section structure for a turbine engine, characterized in that, The transition section structure connects the wave rotor and the turbine of the turbine engine; The transition section structure includes a body, which has an airflow channel, and the airflow channel includes a centrifugal section, an axial section and a centripetal section connected in sequence. The centrifugal section extends radially away from the axis of the body. The inlet of the airflow channel is located at one end of the centrifugal section near the axis. The inlet is an arc-shaped inlet that matches the outlet of the wave rotor. The circumferential opening angle of the centrifugal section gradually increases along its extension direction. The axial segment extends along the axial direction of the body from the end of the centrifugal segment away from the axis, and the circumferential opening angle of the axial segment remains unchanged or gradually increases along the extension direction of the axial segment. The centripetal segment is an annular segment extending radially toward the axis of the body from the end of the axial segment away from the centrifugal segment. The end of the centripetal segment near the axis forms the outlet of the airflow channel, and the outlet is an annular outlet centered on the axis of the body and adapted to the air intake end of the turbine. The circumferential opening angle of the centripetal segment gradually increases along the extension direction of the centripetal segment.
2. The radial return flow transition section structure of the turbine engine according to claim 1, characterized in that, Along the extension direction of the centrifugal segment, the circumferential expansion ratio of the circumferential opening angle of the centrifugal segment ranges from 2.5 to 3. And / or, the axial width of the centrifugal segment remains unchanged along the extension direction of the centrifugal segment.
3. The radial return flow transition section structure of the turbine engine according to claim 1, characterized in that, Along the extension direction of the axial segment, the circumferential expansion ratio of the circumferential opening angle of the axial segment ranges from 1 to 1.
05.
4. The radial return flow transition section structure of the turbine engine according to claim 1, characterized in that, Along the extending direction of the centripetal segment, the circumferential expansion ratio of the circumferential opening angle of the centripetal segment ranges from 1.2 to 1.5; And / or, the axial width of the centripetal segment remains unchanged along the extension direction of the centripetal segment.
5. The radial return flow transition section structure of the turbine engine according to any one of claims 1 to 4, characterized in that, The axial width of the centrifugal section is greater than the axial width of the centripetal section.
6. The radial return flow transition section structure of the turbine engine according to claim 5, characterized in that, The area of the export is smaller than the area of the import.
7. The radial return flow transition section structure of the turbine engine according to any one of claims 1 to 4, characterized in that, The centrifugal section, axial section, and centripetal section are all surface-symmetrical structures.
8. The radial return flow transition section structure of the turbine engine according to any one of claims 1 to 4, characterized in that, The ratio of the circumferential opening angle of the outlet to the circumferential opening angle of the inlet is in the range of 3 to 4.
9. The radial return flow transition section structure of the turbine engine according to any one of claims 1 to 4, characterized in that, The body includes at least two circulating units, which are arranged sequentially along the circumference of the axis. Each of the aforementioned circulation units includes a sub-centrifugal segment, a sub-axial segment, and a sub-centripetal segment connected in sequence; the sub-centrifugal segment extends radially away from the axis of the body, the sub-axial segment extends axially from the end of the sub-centrifugal segment away from the axis of the body, and the sub-centripetal segment extends from the end of the sub-axial segment away from the sub-centrifugal segment towards the axis of the body. Each of the centrifugal segments of the circulation unit has an inlet, and the end of each centripetal segment near the axis is formed into an arc-shaped sub-outlet. The arc-shaped sub-outlets of all the centripetal segments are sequentially assembled along the circumference of the axis to form the outlet.
10. A turbine engine, characterized in that, It includes a wave rotor, a turbine, and a transition section structure of a turbine engine as described in any one of claims 1 to 9.