A rotary engine rotor structure and a rotary engine

Abstract

The application relates to a rotary engine rotor structure and a rotary engine, and relates to the technical field of engines. The rotary engine rotor structure comprises a first rotor, the outer periphery of the first rotor is provided with at least one convex part, the profile line of the convex part comprises a top arc segment and a first transition segment and a second transition segment connected to the two ends of the top arc segment respectively; the outer periphery of a second rotor is provided with at least one inner recess part matched with the convex part, the profile line of the inner recess part comprises a concave arc segment and a first matched transition segment and a second matched transition segment connected to the two ends of the concave arc segment respectively; wherein the radii of the top arc segment and the concave arc segment are equal, and the centers of the circles are located on the rotation center axis of the first rotor; in the process of relative rotation of the first rotor and the second rotor, when the top arc segment rotates through the concave arc segment, a dynamic seal is formed between the top arc segment and the concave arc segment; the inside of the first rotor is provided with a cooling medium channel. The rotary engine rotor structure has the characteristics of good sealing performance, heat dissipation and light weight.

Description

Technical Field

[0001] This application relates to the field of engine technology, specifically to a rotary engine rotor structure and a rotary engine. Background Technology

[0002] Currently, reciprocating piston-connecting rod engines have become the mainstream engine structure in the market due to their mature and reliable structure and design. In contrast, rotary engines utilize a rotating rotor in conjunction with a casing or other rotors to form a variable-volume sealed space, thereby achieving a four-stroke cycle. Theoretically, this avoids the inertial forces of piston reciprocating motion, enabling higher speeds and power densities, and simplifying the structure and reducing volume, making it a consistently hot topic in new engine structure research. However, engineering practice has revealed a series of key design bottlenecks in existing rotary engine rotors. Specifically: sealing the meshing parts between rotors is difficult, affecting engine thermal efficiency and emissions; the rotor directly contacts high-temperature combustion gases, and the large heat load affects its durability; the rotor's large weight leads to increased rotational inertia, requiring more robust structural support to overcome system impacts, but this increases the overall weight, size, and cost of the engine. Summary of the Invention

[0003] In view of the above, the purpose of this application is to provide a rotary engine rotor structure and a rotary engine to solve at least one of the above technical problems.

[0004] In a first aspect, this application provides a rotary engine rotor structure, comprising: a first rotor having at least one protrusion on its outer periphery, the protrusion having a profile including a top arc segment and a first transition segment and a second transition segment respectively connected to both ends of the top arc segment; a second rotor having at least one concave portion on its outer periphery that mates with the protrusion, the concave portion having a profile including a concave arc segment and a first mating transition segment and a second mating transition segment respectively connected to both ends of the concave arc segment; wherein the radii of the top arc segment and the concave arc segment are equal and their centers are both located on the rotational central axis of the first rotor; during the relative rotation of the first rotor and the second rotor, when the top arc segment rotates past the concave arc segment, a dynamic seal is formed between the top arc segment and the concave arc segment; and a cooling medium channel is provided inside the first rotor.

[0005] In conjunction with the first aspect, in some optional embodiments, the first and second mating transition sections are symmetrically arranged about the centerline of the concave portion and are both concave curves; during the rotation of the top arc segment through either the first or second mating transition section, the endpoint of the top arc segment adjacent to that mating transition section remains in contact with that mating transition section.

[0006] In conjunction with the first aspect, in some alternative embodiments, at least one of the first transition section and the second transition section is a convex curve; during the rotation of the protrusion through the concave portion, the transition section with the convex curve maintains contact with the endpoint of the adjacent mating transition section that connects to the outer periphery of the second rotor.

[0007] In conjunction with the first aspect, in some optional embodiments, the first rotor includes a rotor body and a rotor shaft connected to the rotor body, and the cooling medium channel includes a first cooling cavity located in the rotor body, a first inlet channel and a first outlet channel located in the rotor shaft, a first connecting channel connecting the first cooling cavity and the first inlet channel, and a second connecting channel connecting the first cooling cavity and the first outlet channel.

[0008] In conjunction with the first aspect, in some alternative embodiments, the inlet of the first inlet channel is located on the side of the rotor shaft, and the outlet of the first outlet channel is located on the end face or side of the rotor shaft.

[0009] In conjunction with the first aspect, in some alternative embodiments, the interior of the second rotor is provided with a cooling medium channel.

[0010] In conjunction with the first aspect, in some alternative embodiments, the interior of the first rotor and / or the second rotor is formed with multiple hollow areas separated by multiple support structures.

[0011] In conjunction with the first aspect, in some alternative embodiments, multiple support structures are distributed circumferentially along the rotor, with each support structure extending tangentially along an arbitrary circle centered on the rotor's center.

[0012] In conjunction with the first aspect, in some alternative embodiments, the interior of the first rotor and / or the second rotor is further provided with a counterweight for balancing the center of gravity.

[0013] Secondly, this application provides a rotary engine, including the rotary engine rotor structure in any of the embodiments of the first aspect described above.

[0014] Based on the above technical solutions, the rotary engine rotor structure and rotary engine provided in this application, by designing the profiles of the protrusion of the first rotor and the concave part of the second rotor, ensure that during the relative rotation of the two rotors, the top arc segment of the protrusion and the concave arc segment of the concave part form a dynamic seal, effectively solving the problem of difficult sealing at the rotor meshing point, thereby improving the thermal efficiency and emissions of the rotary engine; the cooling medium channel set inside the rotor can effectively cool the high-temperature area, significantly reducing the adverse effects of heat load on rotor durability, avoiding rotor thermal deformation and failure, and the cooling medium channel also reduces the weight of the rotor, which is conducive to the lightweighting of the rotor and rotary engine. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of a rotary engine rotor structure provided in an embodiment of this application.

[0017] Figure 2 This is a partially enlarged schematic diagram of a rotary engine rotor structure provided in an embodiment of this application.

[0018] Figure 3 This is a schematic diagram of the meshing process between a first rotor and a second rotor, provided as an embodiment of this application.

[0019] Figure 4 This is a schematic diagram of another meshing process between a first rotor and a second rotor provided in an embodiment of this application.

[0020] Figure 5 This is a schematic diagram of the structure of a first rotor and its cooling medium channel provided in an embodiment of this application.

[0021] Figure 6 This is a schematic diagram of the structure in which the cooling medium passage of the housing is connected to the first rotor, as provided in an embodiment of this application.

[0022] Figure 7 This is a schematic diagram of the internal structure of a first rotor provided in an embodiment of this application.

[0023] Figure 8 This is a schematic diagram of the force distribution on a support structure within a first rotor, provided as an embodiment of this application.

[0024] Reference numerals: 10, First rotor; 11, Protrusion; 12, Rotor body; 13, Rotor shaft; 14, Cooling medium channel; 141, First cooling chamber; 142, First inlet channel; 1421, Inlet; 143, First outlet channel; 1431, Outlet; 144, First connecting channel; 145, Second connecting channel; 15, Support structure; 16, Hollowed-out area; 17, Counterweight; 20, Second rotor; 21, Recessed portion; 30, Outer shell; 31, Air inlet; 32, Exhaust port; 33, Cooling medium supply passage. Detailed Implementation

[0025] The specific embodiments of this application will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely a part of the embodiments of this application, and not all of them. Based on the description of this application, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this application.

[0026] In the description of this application, unless otherwise expressly specified and limited, the terms "connection," "setup," "installation," etc., should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0027] The terms “upper,” “lower,” “left,” “right,” “front,” “back,” “center,” “top,” “bottom,” “inner,” “outer,” “vertical,” “horizontal,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product is in use. They are used only for the convenience of description and simplification, and 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. Therefore, they should not be construed as limitations on this application.

[0028] The terms “first,” “second,” “third,” etc., are used only to distinguish elements with similar properties, and do not indicate or imply relative importance or a specific order, unless otherwise explicitly stated or limited.

[0029] The terms “comprising,” “including,” “having,” or any other variations thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase “comprising one…” does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0030] The term "multiple" means two or more (including two).

[0031] The term "and / or" describes the relationship between related objects, indicating that there can be three relationships. For example, A and / or B can represent three cases: A exists alone, A and B exist simultaneously, and B exists alone.

[0032] The terms "an embodiment," "as an example," and "in one implementation" refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which may be included in at least one embodiment or example of this application. These illustrative expressions do not necessarily refer to the same embodiment, nor are they independent or alternative embodiments mutually exclusive with other embodiments. Where there is no conflict, the embodiments and features described in these embodiments can be combined in a suitable manner.

[0033] This application provides a rotary engine rotor structure, which aims to solve the problems of difficult meshing and sealing, high heat load, and large self-weight of existing rotary engine rotors.

[0034] like Figure 1 As shown, the rotary engine rotor structure includes a first rotor 10 and a second rotor 20. The first rotor 10 has at least one protrusion 11 on its outer periphery, and the second rotor 20 has at least one concave portion 21 on its outer periphery that meshes with the protrusion 11. In this embodiment, the first rotor 10 has a protrusion 11 on its outer periphery, and the second rotor 20 has a concave portion 21 on its outer periphery. During operation, the first rotor 10 and the second rotor 20 rotate in opposite directions at the same speed within the outer casing 30 of the rotary engine. Under the combined action of the protrusion 11 and the concave portion 21, two continuously changing cavities are formed between the two sides of the protrusion 11 and the outer casing 30. One cavity connects to the air inlet 31 on the outer casing 30, and the volume of this cavity continuously increases to draw in air or a mixture of air and fuel from the outside, or to accommodate the expanded gas after ignition; the other cavity connects to the exhaust port 32 on the outer casing 30, and the volume of this cavity continuously decreases to compress the air or mixture of air and fuel, or to discharge exhaust gas. Among them, the mating part of the protrusion 11 and the concave part 21, as well as the contact part of the protrusion 11 and the inner wall surface of the outer shell 30, are the main boundaries that constitute the two cavities. Their shapes are complex and have high sealing requirements. Therefore, the profile design of the protrusion 11 and the concave part 21 is crucial.

[0035] It should be noted that in other embodiments, the number of protrusions 11 on the outer periphery of the first rotor 10 can be two, three, or even more, and the number of recesses 21 on the second rotor 20 corresponds to the number of protrusions 11. When multiple protrusions 11 and multiple recesses 21 are provided, multi-stroke staggered operation can be achieved, further improving the power density and operational stability of the rotary engine.

[0036] Regarding the profile design of the protrusion 11 and the concave portion 21, as an example, such as Figure 2As shown, the profile of the protrusion 11 includes a top arc segment BC and a first transition segment AB and a second transition segment CD connected to the two ends of the top arc segment BC. The radius of the rotor body 12 of the first rotor 10 is R, the height of the protrusion 11 relative to the rotor body 12 is L, and the top arc segment BC is a circular arc with a radius of R+L, centered at the rotation center of the first rotor 10 (i.e., concentric with the first rotor 10). During the rotation of the first rotor 10, due to the arc design of the top arc segment BC with a certain width, when the top arc segment BC passes through the inner wall surface of the outer casing 30, its contact with the inner wall surface of the outer casing 30 changes from traditional edge contact to surface contact. This surface contact effectively improves the sealing performance between the protrusion 11 and the inner wall surface of the outer casing 30, preventing gas leakage and providing a good dynamic sealing effect.

[0037] Furthermore, the profile of the concave portion 21 includes a concave arc segment NO and a first mating transition segment MN and a second mating transition segment OP respectively connected to the two ends of the concave arc segment NO. The concave arc segment NO is a circular arc with a radius of R+L, centered at the rotation center of the first rotor 10. During the relative rotation of the first rotor 10 and the second rotor 20, since both the top arc segment BC and the concave arc segment NO are equal-diameter circular arcs with a certain width, a narrow parallel channel is formed between the top arc segment BC and the concave arc segment NO when the top arc segment BC rotates past the concave arc segment NO. This narrow parallel channel constitutes a highly efficient surface seal during the relative rotation of the two rotors. Whether in the intake, compression, power, or exhaust strokes, this structure continuously utilizes the throttling resistance of the fluid to prevent gas leakage, thereby comprehensively ensuring the volumetric efficiency and thermal efficiency of the rotary engine throughout its entire operating process.

[0038] To further optimize the sealing effect when the protrusion 11 and the concave portion 21 engage, the following design was adopted for the profiles of the protrusion 11 and the concave portion 21: Both the first mating transition segment MN and the second mating transition segment OP are designed as concave curves and are symmetrically arranged about the centerline of the concave portion 21. The first mating transition segment MN and the second mating transition segment OP are also configured such that, during the rotation of the top arc segment BC through any mating transition segment (referring to the first mating transition segment MN or the second mating transition segment OP), the endpoint of the top arc segment BC adjacent to that mating transition segment remains in contact with that mating transition segment. As an example, such as... Figure 3 As shown, taking the first rotor 10 rotating counterclockwise and the second rotor 20 rotating clockwise as an example, during the rotation of the top arc segment BC through the second mating transition segment OP, the end point C of the top arc segment BC remains in contact with the second mating transition segment OP. During the rotation of the top arc segment BC through the first mating transition segment MN, the end point B of the top arc segment BC remains in contact with the first mating transition segment MN. This can enhance the sealing effect when the protrusion 11 and the concave part 21 mesh.

[0039] At least one of the first transition section AB and the second transition section CD is designed as a convex curve and configured such that, as the protrusion 11 rotates through the concave portion 21, the transition section designed as a convex curve maintains contact with the endpoint of the adjacent mating transition section that connects to the outer periphery of the second rotor 20. As an example, such as... Figure 3 As shown, taking the first rotor 10 rotating counterclockwise and the second rotor 20 rotating clockwise as an example, the first transition section AB is a straight line and the second transition section CD is an outwardly convex curve. During the process of the protrusion 11 rotating through the concave part 21, the second transition section CD and the end point P of the second mating transition section OP remain in contact, which can enhance the sealing effect when the protrusion 11 and the concave part 21 mesh.

[0040] As another example, such as Figure 4 As shown, both the first transition section AB and the second transition section CD are convex curves and symmetrically arranged about the centerline of the top arc section BC. During the rotation of the protrusion 11 through the concave portion 21, the first transition section AB maintains contact with the endpoint M of the first mating transition section MN, and the second transition section CD maintains contact with the endpoint P of the second mating transition section OP. This not only enhances the sealing effect when the protrusion 11 and the concave portion 21 engage, but also, as the protrusion 11 rotates through the concave portion 21, the first transition section AB gradually approaches and eventually completely fits against the first mating transition section MN. This allows the gradually decreasing volume cavity space between the protrusion 11 and the concave portion 21 to be cleared without leakage, achieving zero-volume compression. This design can be used to completely compress gas into another cavity during compression, improving compression efficiency, and also to clear residual exhaust gas from a gradually increasing cavity before ignition, ensuring combustion quality.

[0041] In practical design, the first transition segment AB and the second transition segment CD, which are designed as convex curves, and the first mating transition segment MN and the second mating transition segment OP, which are designed as concave curves, can be constructed using formulas.

[0042] As an example, the first mate transition segment MN and the second mate transition segment OP can be constructed using equation (1): (1) in, , The curve coordinates of the second mating transition section OP are represented; D is the radius of the top arc segment BC (or the concave arc segment NO); r is the radius of the first rotor 10 (or the second rotor 20); Indicates the current parameter angle; The terminator is the termination angle; t is a parameter variable, t∈[0,1].

[0043] The first transition segment AB and the second transition segment CD, designed as convex curves, can be constructed using equation (2): (2) in, , The curve coordinates of the second transition segment CD are represented; D is the radius of the top arc segment BC (or the concave arc segment NO); r is the radius of the first rotor 10 (or the second rotor 20); , Indicates the coordinates of the intersection point of the second transition segment CD and the second mating transition segment OP; Indicates the current parameter angle; Indicates the starting angle; This represents the angular span; t is a parameter variable, t∈[0,1].

[0044] The above formula ensures the continuity of the curve and the smoothness of higher-order derivatives, thereby reducing meshing impact and vibration of the rotor at high speed.

[0045] To address the issue of high rotor heat load, the first rotor 10 is equipped with a cooling medium channel 14 to cool the concentrated heat load area on the first rotor 10 using a cooling medium (such as oil); the second rotor 20 can be equipped with a cooling medium channel as needed.

[0046] Regarding the structure of the cooling medium channel 14 inside the first rotor 10, as follows: Figure 5As shown, the first rotor 10 includes a rotor body 12 and a rotor shaft 13 connected to the rotor body 12. The cooling medium channel 14 includes a first cooling chamber 141 located in the rotor body 12, a first inlet channel 142 and a first outlet channel 143 located in the rotor shaft 13, a first connecting channel 144 connecting the first cooling chamber 141 and the first inlet channel 142, and a second connecting channel 145 connecting the first cooling chamber 141 and the first outlet channel 143. The first cooling chamber 141 is machined or pre-cast into the rotor body 12. Its arrangement position can be modified according to the actual heat load concentration area on the first rotor 10, or its arrangement shape can be modified according to the required flow rate and heat dissipation. The first cooling chamber 141 shown in the figure corresponds to the area of ​​the protrusion 11 of the first rotor 10 and the cavity connected to the air inlet 31. The first inlet channel 142 and the first outlet channel 143 can both be arranged in the rotor shaft 13 by machining holes along the axial direction. The first connecting channel 144 and the second connecting channel 145 can also be arranged in the rotor body 12 by machining holes, and respectively connect the first cooling chamber 141 with the first inlet channel 142 and the first cooling chamber 141 with the first outlet channel 143. The openings of the first inlet channel 142, the first outlet channel 143, the first connecting channel 144 and the second connecting channel 145 on the rotor shaft 13 can be sealed as needed using steel balls, cup-shaped plugs or welding.

[0047] Furthermore, such as Figure 6 As shown, the inlet 1421 of the first inlet channel 142 can be located on the side of the rotor shaft 13 to connect with the corresponding semi-circular or annular cooling medium supply passage 33 on the outer casing 30. When the rotor shaft 13 rotates, the inlet 1421 of the first inlet channel 142 can be intermittently or continuously connected with the cooling medium supply passage 33 on the outer casing 30 to introduce the cooling medium. The outlet 1431 of the first outlet channel 143 can be located at any position on the rotor shaft 13, either on the end face and / or side of the rotor shaft 13, which facilitates the arrangement of the cooling medium return channel to accommodate different overall machine design requirements.

[0048] Regarding the cooling medium channel inside the second rotor 20, since both the first rotor 10 and the second rotor 20 are independently rotating components, if the second rotor 20 is configured with a cooling medium channel, an independent cooling medium channel must also be used. Its specific structure can be designed with reference to the cooling medium channel 14 inside the first rotor 10 described above. Specifically, the second rotor 20 also includes a rotor body and a rotor shaft. Its internal cooling medium channel includes a second cooling chamber located within the rotor body, a second inlet channel and a second outlet channel located within the rotor shaft, a third connecting channel connecting the second cooling chamber and the second inlet channel, and a fourth connecting channel connecting the second cooling chamber and the second outlet channel. In terms of the medium passage layout, the inlet of the second inlet channel is located on the side of the rotor shaft of the second rotor 20, used to connect to another annular or semi-annular cooling medium supply passage specially provided on the outer casing 30, so as to realize the dynamic introduction of cooling medium during the rotation of the second rotor 20; the outlet of the second outlet channel is located on the end face or side of the rotor shaft of the second rotor 20, to facilitate the arrangement of the cooling medium return channel. The aforementioned second cooling chamber and connecting channels can also be formed by machining or pre-casting, and the process holes can be sealed as needed using steel balls, cup-shaped plugs, or welding. This independent structural design ensures that the first rotor 10 and the second rotor 20 can obtain stable and reliable cooling without interfering with each other when rotating independently.

[0049] To address the issue of the large self-weight of the rotor, the interior of the first rotor 10 is formed with multiple hollow areas 16 separated by multiple support structures 15. While retaining the necessary wall thickness, the self-weight and inertia of the first rotor 10 are reduced to the maximum extent by the internal hollowing, thereby reducing the strength requirements of the support structure 15 and helping to reduce the overall size and cost. The interior of the second rotor 20 can be equipped with support structures and hollow areas as needed.

[0050] Regarding the arrangement of the support structure 15, taking the support structure 15 inside the first rotor 10 as an example, the support structure inside the second rotor 20 can be designed with reference to this. Specifically, as follows... Figure 7 As shown, multiple support structures 15 are distributed circumferentially along the first rotor 10, and each support structure 15 extends tangentially along any circle centered on the center of the first rotor 10. Since the first rotor 10 is always subjected to force on one side of the protrusion 11 during operation, if a traditional radial support (i.e., the support structure 15 passes through the rotation center) is used, the high-pressure thrust will generate significant bending stress on the support structure 15, easily leading to the breakage of the first rotor 10. Therefore, the support structure 15 is designed to be arranged tangentially along the center of the first rotor 10 (i.e., not passing through the rotation center axis of the first rotor 10), which can convert the torsional moment on the first rotor 10 into compressive stress in the support direction rather than bending stress. Figure 8As shown, the force F acting on the protrusion 11 can be decomposed into a radial component F1 and a tangential component F2. The tangentially arranged support structure 15 effectively counteracts the shearing and bending effects of the tangential component F2, significantly improving the rotor's resistance to deformation and structural strength. In practical design, the magnitude of the tangential component F2 can be adjusted by changing the diameter of the circle tangent to the support structure 15 to adapt to different operating conditions. Furthermore, at least a portion of the cooling medium channel 14, such as the first connecting channel 144 and / or the second connecting channel 145, can be housed within the support structure 15. Moreover, the support structure 15 with connecting channels can be thickened as needed, while the thickness of the remaining support structures 15 can remain unchanged, thus minimizing the weight and inertia of the first rotor 10.

[0051] Due to the use of an internally asymmetrical hollow structure and a tangentially arranged support structure 15, coupled with the presence of a cooling chamber 141, the mass distribution of the first rotor 10 after machining deviates from its rotation center. To address the dynamic balance problem during high-speed rotation, such as... Figure 8 As shown, the first rotor 10 also has a counterweight 17 inside for balancing the center of gravity. This counterweight 17 is preferably located at the edge of the hollowed-out area on the side approximately symmetrical to the side containing the protrusion 11. In actual manufacturing, after the rough and fine machining of the first rotor 10 is completed, the imbalance of the first rotor 10 can be precisely controlled by testing on a dynamic balancing machine and removing or adding counterweights at preset positions. This ensures that it rotates smoothly even at rated speeds of tens of thousands of revolutions per minute, suppressing overall machine vibration.

[0052] Based on the aforementioned rotary engine rotor structure, this application also provides a rotary engine, which includes the rotary engine rotor structure of any of the above embodiments. Thanks to the conjugate profile design of the radial cross-section, the surface contact sealing design, the efficient internal cooling medium channel layout, and the lightweight structure of the tangential biomimetic support, this rotary engine fundamentally overcomes the end-face and radial sealing problems of traditional rotary engines, significantly reducing the risk of rotor thermal deformation and thermal stress failure, while achieving extremely low rotational inertia. Therefore, this rotary engine achieves improved thermal efficiency, extended service life, and reduced overall weight, thereby significantly enhancing the overall performance and market competitiveness of the machine.

[0053] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any person skilled in the art can easily conceive of various variations or substitutions within the technical scope disclosed in this application, and these should all be included within the scope of protection of this application.

Claims

1. A rotary engine rotor structure, characterized by, include: The first rotor has at least one protrusion on its outer periphery. The profile of the protrusion includes a top arc segment and a first transition segment and a second transition segment respectively connected to the two ends of the top arc segment. The second rotor has at least one concave portion on its outer periphery that mates with the protrusion. The profile of the concave portion includes a concave arc segment and a first mating transition segment and a second mating transition segment respectively connected to the two ends of the concave arc segment. The top arc segment and the concave arc segment have equal radii and their centers are both located on the rotation center axis of the first rotor; during the relative rotation of the first rotor and the second rotor, when the top arc segment rotates past the concave arc segment, a dynamic seal is formed between the top arc segment and the concave arc segment; the first rotor has a cooling medium channel inside.

2. The rotary engine rotor structure according to claim 1, characterized in that, The first and second mating transition sections are symmetrically arranged about the centerline of the concave portion and are both concave curves; during the rotation of the top arc segment through either the first or the second mating transition section, the endpoint of the top arc segment adjacent to the mating transition section remains in contact with the mating transition section.

3. The rotary engine rotor structure according to claim 2, characterized in that, At least one of the first transition section and the second transition section is a convex curve; during the rotation of the protrusion through the concave portion, the transition section with the convex curve maintains contact with the endpoint of the adjacent mating transition section that connects to the outer periphery of the second rotor.

4. The rotary engine rotor structure according to claim 1, characterized in that, The first rotor includes a rotor body and a rotor shaft connected to the rotor body. The cooling medium channel includes a first cooling cavity located in the rotor body, a first inlet channel and a first outlet channel located in the rotor shaft, a first connecting channel connecting the first cooling cavity and the first inlet channel, and a second connecting channel connecting the first cooling cavity and the first outlet channel.

5. The rotary engine rotor structure according to claim 4, characterized in that, The inlet of the first inlet channel is located on the side of the rotor shaft, and the outlet of the first outlet channel is located on the end face or side of the rotor shaft.

6. The rotary engine rotor structure according to claim 1, characterized in that, The second rotor has a cooling medium channel inside.

7. The rotary engine rotor structure according to claim 1, characterized in that, The interior of the first rotor and / or the second rotor has multiple hollow areas separated by multiple support structures.

8. The rotary engine rotor structure according to claim 7, characterized in that, Multiple support structures are distributed circumferentially along the rotor, and each support structure extends tangentially along any circle centered on the rotor.

9. The rotary engine rotor structure according to claim 7 or 8, characterized in that, The first rotor and / or the second rotor are further provided with a counterweight for balancing the center of gravity.

10. A rotary engine, characterized in that, Includes the rotary engine rotor structure as described in any one of claims 1-9.

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