Turbine casing and aero-engine

Abstract

The utility model discloses a turbine casing and an aero-engine. The turbine casing comprises a casing body, a cooling cover and a groove. The cooling cover comprises an annular cover body, an air inlet and an air outlet. The air inlet and the air outlet are formed in the annular cover body at intervals. The annular cover body is arranged on the outer side of the circumferential side wall of the casing body in a sleeving mode. And an annular airflow channel is formed between the annular cover body and the circumferential side wall. The air inlet is used for inputting cold air. Cold air enters the annular airflow channel through the air inlet and is discharged out of the annular airflow channel through the air outlet. The cooling cover further comprises a mounting edge arranged at the axial end of the annular cover body. The mounting edge is attached to at least part of the circumferential side wall. The groove is formed in the edge of the mounting edge and is concave inwards in the axial direction of the mounting edge. The grooves can reduce thermal stress generated by deformation of the cooling cover in the circumferential direction, the risk that the cooling cover loses efficacy due to the stress concentration phenomenon caused by thermal deformation discordance in the working process is reduced, and then the reliability of the turbine case is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engines, and in particular to a turbine casing and an aircraft engine. Background Art

[0002] The turbine casing needs to withstand high temperatures and internal pressures, and transmit the axial force, torque, and vibration load of the engine. Therefore, in the casing design, attention should be paid to maintaining uniform deformation of the casing during operation, reducing thermal stress, and controlling casing deformation to ensure the matching clearance with the rotor. High-pressure turbine performance test pieces are usually designed in the low-temperature and low-pressure state after molding. However, when the test pieces are designed using molding parameters of medium temperature, medium pressure, or even high temperature and high pressure, the turbine casing will have stress concentration problems caused by uncoordinated thermal deformation.

[0003] It should be noted that the statements in this background technology section only provide background technology related to the present application and do not necessarily constitute prior art. Utility Model Content

[0004] The present application provides a turbine casing and an aircraft engine to improve the reliability of the turbine casing.

[0005] The first aspect of the present application provides a turbine casing, comprising a casing body, a cooling shroud and a groove. The cooling shroud comprises an annular shroud body, an air inlet and an exhaust port. The air inlet and the exhaust port are spaced apart on the annular shroud body. The annular shroud body is sleeved on the outer side of the circumferential side wall of the casing body, and an annular air flow channel is formed between the annular shroud body and the circumferential side wall. The air inlet is used to input cold air. The cold air enters the annular air flow channel through the air inlet and is discharged from the annular air flow channel through the exhaust port. The cooling shroud also includes a mounting edge arranged at the axial end of the annular shroud body. The mounting edge is in contact with at least a portion of the circumferential side wall. The groove is provided at the edge of the mounting edge and is concave in the axial direction of the mounting edge.

[0006] In some embodiments, the mounting edge includes a first mounting edge and a second mounting edge respectively disposed at two axial ends of the annular cover body. The first mounting edge and the second mounting edge are used to connect with the circumferential side wall, and a groove is disposed on the first mounting edge and / or the second mounting edge.

[0007] In some embodiments, a plurality of grooves are included, and the plurality of grooves are spaced apart in a circumferential direction of the annular cover body.

[0008] In some embodiments, the first mounting edge is disposed at one end close to the air inlet, the second mounting edge is disposed at one end close to the exhaust port, and the length of the first mounting edge in the axial direction is greater than the length of the second mounting edge in the axial direction.

[0009] In some embodiments, the groove includes a plurality of first rectangular grooves and a plurality of second rectangular grooves, the plurality of first rectangular grooves are circumferentially spaced apart on the first mounting edge, the plurality of second rectangular grooves are circumferentially spaced apart on the second mounting edge, and the inner length of the first rectangular groove is greater than the inner length of the second rectangular groove.

[0010] In some embodiments, the annular cover body includes a boss segment and an inclined segment connected in sequence. The first end of the boss segment is connected to the circumferential side wall. The second end of the boss segment is connected to the first end of the inclined segment. The second end of the inclined segment is connected to the circumferential side wall. From the first end of the boss segment to the second end of the inclined segment, the distance between the annular cover body and the circumferential side wall increases first and then decreases, and the distance is the largest at the second end of the boss segment.

[0011] In some embodiments, the spacing gradually decreases from the first end of the inclined segment to the second end of the inclined segment.

[0012] In some embodiments, the air inlet is arranged on the boss section, and the air outlet is arranged on the inclined section.

[0013] In some embodiments, the boss section includes a first extension portion and a second extension portion arranged at an angle. The first end of the first extension portion is connected to the circumferential side wall. The second end of the first extension portion is connected to the first end of the second extension portion. The second end of the second extension portion is connected to the first end of the inclined section. The extension direction of the second extension portion is parallel to the axis of the casing body. The air inlet is arranged on the second extension portion.

[0014] In some embodiments, an air intake connector is further included. One end of the air intake connector is used to connect to a cold air pipeline. The other end of the air intake connector is connected to an air inlet to guide cold air from the cold air pipeline to the air inlet. The axis of the air intake connector is perpendicular to the axis of the casing body.

[0015] In some embodiments, an exhaust connector is further included. One end of the exhaust connector is used to connect an exhaust pipeline. The other end of the exhaust connector is connected to the exhaust port to guide cold air from the exhaust port to the exhaust pipeline. The axis of the exhaust connector is perpendicular to the axis of the casing body.

[0016] In some embodiments, the cooling shroud includes a plurality of air inlets which are spaced apart in the circumferential direction of the annular shroud body, and / or the cooling shroud includes a plurality of exhaust ports which are spaced apart in the circumferential direction of the annular shroud body.

[0017] A second aspect of the present application provides an aircraft engine, comprising the turbine casing as described above.

[0018] Based on the technical solution provided in the present application, the turbine casing includes a casing body, a cooling hood and a groove. The cooling hood includes an annular hood body, an air inlet and an exhaust port. The air inlet and the exhaust port are arranged on the annular hood body at intervals. The annular hood body is sleeved on the outer side of the circumferential side wall of the casing body. An annular air flow channel is formed between the annular hood body and the circumferential side wall. The air inlet is used to input cold air. The cold air enters the annular air flow channel through the air inlet and is discharged from the annular air flow channel through the exhaust port. The cooling hood also includes a mounting edge arranged at the axial end of the annular hood body. The mounting edge is at least partially fitted with the circumferential side wall. The groove is provided at the edge of the mounting edge and is concave in the axial direction of the mounting edge. The groove can reduce the thermal stress generated by the circumferential deformation of the cooling hood, optimize the distribution of the thermal stress of the cooling hood, reduce the risk of failure of the cooling hood due to stress concentration caused by uncoordinated thermal deformation during operation, increase the service life of the cooling hood, and thereby improve the reliability of the turbine casing.

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

[0020] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0021] Figure 1 Schematic diagram of a turbine casing according to some embodiments of the present application.

[0022] Figure 2 This is a cross-sectional view of a turbine casing according to some embodiments of the present application.

[0023] Figure 3 A top view of a partial area of ​​a turbine casing according to some embodiments of the present application. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present application and its application or use. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0025] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the application. Meanwhile, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to actual proportional relationships. The technology, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but in appropriate cases, the technology, methods and equipment should be considered as a part of the specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, and therefore, once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0026] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" may include both "above" and "below". The device may also be positioned in other different ways, and the spatially relative descriptions used here are interpreted accordingly.

[0027] refer to Figure 1 and Figure 2 The present application provides a turbine casing, comprising a casing body 1, a cooling hood 2 and a groove 3. The cooling hood 2 comprises an annular hood body 21, an air inlet 22 and an exhaust port 23. The air inlet 22 and the exhaust port 23 are arranged on the annular hood body 21 at intervals. The annular hood body 21 is sleeved on the outer side of the circumferential side wall of the casing body 1. An annular airflow channel A is formed between the annular hood body 21 and the circumferential side wall. The air inlet 22 is used to input cold air. The cold air enters the annular airflow channel A through the air inlet 22 and is discharged from the annular airflow channel A through the exhaust port 23. The cooling hood 2 also includes a mounting edge arranged at the axial end of the annular hood body 21. The mounting edge is in contact with at least a portion of the circumferential side wall. The groove 3 is opened at the edge of the mounting edge and is concave in the axial direction of the mounting edge.

[0028] The cold air enters the annular air flow channel A through the air inlet 22 and flows toward the exhaust port 23 . During the flow, the cold air exchanges heat with the circumferential side wall of the casing body 1 in the entire circumferential direction of the casing body 1 , and takes out the heat, thereby cooling the casing body 1 and reducing the thermal stress of the casing body 1 .

[0029] The groove 3 can reduce the thermal stress generated by the circumferential deformation of the cooling hood 2, optimize the distribution of the thermal stress of the cooling hood 2, reduce the risk of failure of the cooling hood 2 due to stress concentration caused by uncoordinated thermal deformation during operation, increase the service life of the cooling hood 2, and thereby improve the reliability of the turbine casing.

[0030] refer to Figure 2 In some embodiments, the mounting edge includes a first mounting edge 21a and a second mounting edge 21b respectively arranged at two axial ends of the annular cover body 21. The first mounting edge 21a and the second mounting edge 21b are used to connect with the circumferential side wall. A groove 3 is arranged on the first mounting edge 21a and / or the second mounting edge 21b. Mounting edges are arranged at both axial ends of the annular cover body 21, and the mounting edges at both ends are in contact with the circumferential side wall, which can improve the stability of the connection between the cooling cover 2 and the circumferential side wall, and can improve the air tightness of the annular airflow channel A, reduce the risk of accidental leakage of cold air after entering the air inlet 22, and thereby ensure the cooling ability of the cold air on the casing body 1.

[0031] refer to Figure 1 In some embodiments, the turbine casing includes a plurality of grooves 3. The plurality of grooves 3 are arranged at intervals in the circumferential direction of the annular cover body 21. Specifically, the plurality of grooves 3 are provided on the first mounting edge 21a and the second mounting edge 21b, so as to further optimize the distribution of thermal stress and improve the service life of the cooling cover 2.

[0032] refer to Figure 1 and 2 In some embodiments, the first mounting edge 21a is disposed at one end close to the air inlet 22, the second mounting edge 21b is disposed at one end close to the exhaust port 23, and the length of the first mounting edge 21a in the axial direction is greater than the length of the second mounting edge 21b in the axial direction. Specifically, the stress at the position close to the air inlet 22 of the cooling cover 2 is greater than that at the position close to the exhaust port 23, so the size of the first mounting edge 21a in the axial direction is designed to be larger, so that the stress distribution can be more uniform, thereby increasing the service life of the cooling cover 2.

[0033] Further, refer to Figure 1In some embodiments, the groove 3 includes a plurality of first rectangular grooves 31 and a plurality of second rectangular grooves 32. The plurality of first rectangular grooves 31 are circumferentially spaced apart on the first mounting edge 21a. The plurality of second rectangular grooves 32 are circumferentially spaced apart on the second mounting edge 21b. The concave length of the first rectangular groove 31 is greater than the concave length of the second rectangular groove 32. Since the axial length of the first mounting edge 21a is longer than that of the second mounting edge 21b, the concave length of the first rectangular groove 31 is made longer than that of the second rectangular groove 32, thereby improving the ability of the first rectangular groove 31 to reduce the thermal stress generated by the circumferential deformation of the cooling cover 2.

[0034] refer to Figure 2 In some embodiments, the annular cover body 21 includes a boss segment 211 and an inclined segment 212 connected in sequence. The first end of the boss segment 211 is connected to the circumferential side wall. The second end of the boss segment 211 is connected to the first end of the inclined segment 212. The second end of the inclined segment 212 is connected to the circumferential side wall. From the first end of the boss segment 211 to the second end of the inclined segment 212. The distance between the annular cover body 21 and the circumferential side wall increases first and then decreases. The distance is the largest at the second end of the boss segment 211.

[0035] Specifically, the first end of the boss section 211 constitutes a first mounting edge 21 a , and the second end of the inclined section 212 constitutes a second mounting edge 21 b . The boss section 211 can be used to release the axial stress on the cooling cover 2 .

[0036] In order to further release the axial stress of the cooling cover 2, refer to Figure 2 In some embodiments, the air inlet 22 is disposed on the boss section 211 , and the air outlet 23 is disposed on the inclined section 212 .

[0037] refer to Figure 2 and Figure 3 In some embodiments, the boss section 211 includes a first extension portion 2111 and a second extension portion 2112 that are arranged at an angle. The first end of the first extension portion 2111 is connected to the circumferential side wall. The second end of the first extension portion 2111 is connected to the first end of the second extension portion 2112. The second end of the second extension portion 2112 is connected to the first end of the inclined section 212. The extension direction of the second extension portion 2112 is parallel to the axis of the casing body 1. The air inlet 22 is arranged on the second extension portion 2112. In this embodiment, the first end of the first extension portion 2111 extends in the axial direction and constitutes a first mounting edge 21a, and the first extension portion 2111 extends in a direction away from the circumferential side wall, so that the distance between the second extension portion 2112 and the circumferential side wall becomes larger, thereby forming a boss to better release the axial stress of the cooling cover 2.

[0038] refer to Figure 2In some embodiments, the spacing gradually decreases from the first end of the inclined section 212 to the second end of the inclined section 212. The flow area of ​​the annular airflow channel A gradually decreases from the first end of the inclined section 212 to the second end of the inclined section 212, so that the flow rate of the cold air near the exhaust port 23 can be increased, and the cold air is guided to be discharged through the exhaust port 23, so that the flow of the cold air in the annular airflow channel A is smoother, and the cooling effect is improved.

[0039] refer to Figure 1 In some embodiments, an air intake connector 4 is further included. One end of the air intake connector 4 is used to connect a cold air pipeline. The other end of the air intake connector 4 is connected to the air inlet 22 to guide the cold air from the cold air pipeline to the air inlet 22. The axis of the air intake connector 4 is perpendicular to the axis of the casing body 1. Specifically, since the air inlet 22 is arranged on the second extension portion 2112, the air intake connector 4 is arranged in this way so that the cold air can enter the air inlet 22 vertically, thereby increasing the amount of cold air entering the annular air flow channel A through the air inlet 22 per unit time, thereby improving the cold air circulation efficiency and the cooling effect. In addition, such an arrangement can also allow the exhaust connector 5 to extend in the radial direction of the casing body 1, thereby saving space and simplifying the structure.

[0040] refer to Figure 1 In some embodiments, an exhaust connector 5 is further included. One end of the exhaust connector 5 is used to connect the exhaust pipeline. The other end of the exhaust connector 5 is connected to the exhaust port 23 to guide the cold air from the exhaust port 23 to the exhaust pipeline. The axis of the exhaust connector 5 is perpendicular to the axis of the casing body 1. Extending the exhaust connector 5 in the radial direction of the casing body 1 can save space and simplify the structure.

[0041] refer to Figure 1 In some embodiments, the cooling cover 2 includes a plurality of air inlets 22 , which are spaced apart in the circumferential direction of the annular cover body 21 , and / or the cooling cover 2 includes a plurality of exhaust ports 23 , which are spaced apart in the circumferential direction of the annular cover body 21 .

[0042] Specifically, the turbine casing includes a plurality of air intake connectors 4 and a plurality of exhaust connectors 5, and the plurality of air intake connectors 4 and the plurality of exhaust connectors 5 are respectively connected to a plurality of air intake ports 22 and a plurality of exhaust ports 23, so that the amount of cold air circulation can be increased and the cooling effect can be improved.

[0043] In some embodiments, the brake body 1 includes a main body 11, an air intake side mounting edge 12, and an exhaust side mounting edge 13. The main body 11 has a streamlined profile, and the air intake side mounting edge 12 and the exhaust side mounting edge 13 are arranged on the side wall of the main body 11 and extend radially outward, and the air intake side mounting edge 12 and the exhaust side mounting edge 13 are respectively close to the axial ends of the main body 11. The air intake side mounting edge 12 and the exhaust side mounting edge 13 are respectively used to connect pipelines at the axial ends of the brake body 1, so that gas can flow inside the casing body 1.

[0044] The present application also provides an aircraft engine, comprising the turbine case as described above.

[0045] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present application rather than to limit it. Although the present application has been described in detail with reference to the preferred embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the present application can still be modified or some technical features can be replaced by equivalents without departing from the spirit of the technical solution of the present application, which should be included in the scope of the technical solution for protection in the present application.

Claims

1. A turbine casing, characterized in that: include: Receiver body (1); A cooling cover (2), comprising an annular cover body (21), an air inlet (22) and an exhaust port (23), wherein the air inlet (22) and the exhaust port (23) are arranged on the annular cover body (21) at intervals, the annular cover body (21) is sleeved on the outer side of the circumferential side wall of the casing body (1), and an annular air flow channel (A) is formed between the annular cover body (21) and the circumferential side wall, the air inlet (22) is used to input cold air, the cold air enters the annular air flow channel (A) through the air inlet (22) and is discharged from the annular air flow channel (A) through the exhaust port (23), the cooling cover (2) further comprising a mounting edge arranged at an axial end of the annular cover body (21), the mounting edge being in contact with at least a portion of the circumferential side wall; and A groove (3), wherein the groove (3) is provided at the edge of the mounting edge and is concave inwardly along the axial direction of the mounting edge.

2. The turbine casing according to claim 1, characterized in that: The mounting edge comprises a first mounting edge (21a) and a second mounting edge (21b) respectively arranged at two axial ends of the annular cover body (21); the first mounting edge (21a) and the second mounting edge (21b) are used to be connected to the circumferential side wall; the first mounting edge (21a) and / or the second mounting edge (21b) are provided with the groove (3).

3. The turbine casing according to claim 2, characterized in that: It comprises a plurality of grooves (3), wherein the plurality of grooves (3) are arranged at intervals in the circumferential direction of the annular cover body (21).

4. The turbine casing according to claim 2, characterized in that: The first mounting edge (21a) is arranged at one end close to the air inlet (22), and the second mounting edge (21b) is arranged at one end close to the air outlet (23), and the length of the first mounting edge (21a) in the axial direction is greater than the length of the second mounting edge (21b) in the axial direction.

5. The turbine casing according to claim 4, characterized in that: The groove (3) comprises a plurality of first rectangular grooves (31) and a plurality of second rectangular grooves (32); the plurality of first rectangular grooves (31) are circumferentially spaced apart on the first mounting edge (21a); ​​the plurality of second rectangular grooves (32) are circumferentially spaced apart on the second mounting edge (21b); and the inner concave length of the first rectangular groove (31) is greater than the inner concave length of the second rectangular groove (32).

6. The turbine casing according to claim 1, characterized in that: The annular cover body (21) comprises a boss section (211) and an inclined section (212) connected in sequence, the first end of the boss section (211) is connected to the circumferential side wall, the second end of the boss section (211) is connected to the first end of the inclined section (212), and the second end of the inclined section (212) is connected to the circumferential side wall, and from the first end of the boss section (211) to the second end of the inclined section (212), the distance between the annular cover body (21) and the circumferential side wall first increases and then decreases, and the distance is the largest at the second end of the boss section (211).

7. The turbine casing according to claim 6, characterized in that: The spacing gradually decreases from the first end of the inclined section (212) to the second end of the inclined section (212).

8. The turbine casing according to claim 6, characterized in that: The air inlet (22) is arranged on the boss section (211), and the air outlet (23) is arranged on the inclined section (212).

9. The turbine casing according to claim 8, characterized in that: The boss section (211) comprises a first extension portion (2111) and a second extension portion (2112) which are arranged at an angle, wherein the first end of the first extension portion (2111) is connected to the circumferential side wall, the second end of the first extension portion (2111) is connected to the first end of the second extension portion (2112), the second end of the second extension portion (2112) is connected to the first end of the inclined section (212), the extension direction of the second extension portion (2112) is parallel to the axis of the casing body (1), and the air inlet (22) is arranged on the second extension portion (2112).

10. The turbine casing according to claim 8, characterized in that: It also includes an air intake connector (4), one end of which is used to connect to a cold air pipeline, and the other end of which is connected to the air inlet (22) to guide the cold air from the cold air pipeline to the air inlet (22), and the axis of the air intake connector (4) is perpendicular to the axis of the casing body (1).

11. The turbine casing according to claim 8, characterized in that: It also includes an exhaust connector (5), one end of which is used to connect to an exhaust pipeline, and the other end of which is in communication with the exhaust port (23) so as to guide cold air from the exhaust port (23) to the exhaust pipeline, and the axis of the exhaust connector (5) is perpendicular to the axis of the casing body (1).

12. The turbine casing according to any one of claims 1 to 11, characterized in that: The cooling hood (2) comprises a plurality of air inlets (22), and the plurality of air inlets (22) are arranged at intervals in the circumferential direction of the annular hood body (21); and / or the cooling hood (2) comprises a plurality of exhaust ports (23), and the plurality of exhaust ports (23) are arranged at intervals in the circumferential direction of the annular hood body (21).

13. An aircraft engine, characterized in that: Comprising a turbine casing as claimed in any one of claims 1 to 12.

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