Double-wall flexible inner flow channel structure and aero-engine with same

Abstract

This application provides a double-walled flexible inner flow channel structure, comprising: an inner flow channel; a front support ring, which includes an upper mounting edge, a lower mounting edge, and a flexible support ring extending in an inverted "S" shape between the upper and lower mounting edges; and a heat insulation plate disposed between the inner flow channel and the front support ring. The front support ring is fixedly connected by connecting rivets passing through the front ends of the inner flow channel and the heat insulation plate, and by connecting rivets passing through the rear ends of the inner flow channel and the heat insulation plate, forming a double-layered heat insulation wall between the inner ring of the turbine bearing casing and the main flow channel. The inner flow channel and the heat insulation plate are respectively provided with an inner flow channel slot and a heat insulation plate slot in the circumferential direction. The circumferential position, size, and slot shape of the inner flow channel slot and the heat insulation plate slot match the turbine bearing casing support plate to achieve assembly with the rectifier support plate or the turbine bearing casing support plate. The double-walled flexible inner flow channel structure of this application can greatly improve the heat insulation effect of the inner flow channel on the inner ring of the turbine bearing casing and reduce the operating temperature of the inner ring.

Description

Technical Field

[0001] This application belongs to the field of aero-engines, and specifically relates to a double-walled flexible internal flow channel structure and an aero-engine having the same. Background Technology

[0002] The turbine bearing casing is a major load-bearing component of the engine, needing to support the load of the turbine rotor. Simultaneously, it is also subjected to thermal shock and radiation from the mains combustion gases, bearing significant temperature loads. Therefore, the reliability of the turbine bearing casing is a key issue that needs to be addressed and resolved during engine design.

[0003] like Figure 1 As shown, to improve the structural reliability of the turbine bearing casing and reduce its operating temperature, a common method is to incorporate thermal insulation design into the inner ring 11, outer ring 12, and support plate 13 of the turbine bearing casing 10. Specifically, a flow channel component 20, consisting of an inner flow channel 21, an outer flow channel 22, and a rectifier support plate 23, is designed between the turbine bearing casing and the main flow path gas. The inner flow channel 21 is used to reduce the thermal shock and thermal radiation of the main flow path gas on the inner ring 11 of the turbine bearing casing, thereby lowering the operating temperature of the inner ring.

[0004] However, due to the increasing demands on thrust and other key performance parameters in current aero engines, the gas temperature in the main flow path is rising, leading to increasingly severe temperature loads on the inner ring of the turbine bearing casing and placing higher demands on the thermal insulation design of the inner flow path. Existing single-walled inner flow path structures are no longer sufficient to meet the thermal insulation design requirements of the turbine bearing casing, impacting its structural reliability and lifespan. Summary of the Invention

[0005] The purpose of this application is to provide a double-walled flexible internal flow channel structure and an aero-engine having the same, in order to solve or mitigate at least one of the problems in the prior art.

[0006] The technical solution of this application is: a double-walled flexible internal flow channel structure, comprising:

[0007] internal flow channel;

[0008] A front support ring, the front support ring including an upper mounting edge, a lower mounting edge, and a flexible support ring extending in an inverted "S" shape between the upper mounting edge and the lower mounting edge;

[0009] A heat insulation plate is installed between the inner flow channel and the front support ring;

[0010] Among them, the front end of the connecting rivet passes through the inner flow channel and the heat insulation plate and is fixedly connected to the front support ring. The rear end of the connecting rivet passes through the inner flow channel and the heat insulation plate, so that a double-layer heat insulation wall is formed between the inner ring of the turbine bearing casing and the main flow channel.

[0011] The inner flow channel and the heat insulation plate are respectively provided with an inner flow channel slot and a heat insulation plate slot in the circumferential direction. The circumferential position, size and slot shape of the inner flow channel slot and the heat insulation plate slot are matched with the turbine bearing casing support plate to realize the assembly with the rectifier support plate or the turbine bearing casing support plate.

[0012] In a preferred embodiment of this application, the flexible support ring is a structure formed by the transition between a circular arc and a slope, and the axial flexibility of the flexible support ring is adjusted by adjusting the slope angle and the radius of the circular arc.

[0013] In a preferred embodiment of this application, the heat insulation board is a corrugated structure composed of multiple circular arc transitions.

[0014] In a preferred embodiment of this application, the arc of the heat insulation board has a uniform radius structure, and the radius of the arc is not less than 10 times the wall thickness of the heat insulation board.

[0015] In a preferred embodiment of this application, the radial height difference between the upper boundary and the lower boundary of the corrugated structure is not less than 5 mm.

[0016] In a preferred embodiment of this application, the upper and lower boundaries of the corrugated structure are located radially at the midpoint between the inner flow channel and the inner ring of the turbine bearing casing, and the radial distance between the upper and lower boundaries of the corrugated structure and the inner flow channel and the inner ring of the turbine bearing casing is not less than 4 mm.

[0017] In a preferred embodiment of this application, the number of the inner flow channel slots and the heat insulation plate slots is the same as the number of the rectifier support plate or the turbine bearing casing support plate.

[0018] In a preferred embodiment of this application, the double-walled flexible inner flow channel structure further includes a reinforcing ring, which is disposed between the inner flow channel and the rear end of the heat insulation plate and is fixedly connected by connecting rivets.

[0019] On the other hand, this application provides an aero-engine that includes a double-walled flexible internal flow channel structure as described above.

[0020] Compared with the single-wall structure in the prior art, the double-wall flexible inner flow channel structure provided in this application can greatly improve the heat insulation effect of the inner flow channel on the inner ring of the turbine bearing casing, reduce the working temperature of the inner ring, improve the structural reliability and service life of the turbine bearing casing, improve the stiffness of the inner flow channel through reasonable connection design, ensure the surface control requirements, and realize the thermal deformation non-coordination during coordinated operation through two flexible connections, thereby improving the structural reliability. Attached Figure Description

[0021] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0022] Figure 1 This is a schematic diagram of the flow channel structure in the prior art.

[0023] Figure 2 This is a cross-sectional view of the double-walled flexible internal flow channel structure of this application.

[0024] Figure 3 This is a three-dimensional view of the double-walled flexible internal flow channel structure of this application.

[0025] Figure 4 This is a schematic diagram of the parameters of the flexible support ring in this application.

[0026] Figure 5 This is a schematic diagram of the parameters of the heat insulation panel in this application.

[0027] Figure Labels

[0028] 30-Double-wall flexible internal flow channel structure

[0029] 31-Front Support Ring

[0030] 311-Top mounting edge

[0031] 312-Flexible support ring

[0032] 313-Lower Installation Edge

[0033] 32-Inner flow channel

[0034] 321-Inner Flow Channel Slot

[0035] 33-Insulation Board

[0036] 331-Insulation panel groove

[0037] 34-Reinforcing Ring

[0038] 35-Connecting Rivet Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0040] To address the insufficient cooling effect of the inner ring of the turbine bearing casing in existing technologies, this application provides a double-walled flexible inner flow channel structure to improve the heat insulation effect of the inner flow channel, reduce the operating temperature of the inner ring, and at the same time, combined with the flexible structure, reduce the thermal incompatibility stress of the inner flow channel, thereby improving the structural reliability and service life of the turbine bearing casing.

[0041] like Figure 2 and Figure 3As shown, the double-walled flexible inner flow channel structure 30 provided in this application is mainly composed of a front support ring 31, an inner flow channel 32, a heat insulation plate 33, and connecting rivets 35.

[0042] The front support ring 31 is a complete ring structure, comprising an upper mounting edge 311, a lower mounting edge 313, and a flexible support ring 312 extending in an inverted "S" shape between the upper and lower mounting edges 311 and 313. The upper mounting edge 311 is connected to the inner flow channel 32 and the heat insulation plate 33 via connecting rivets 35. The lower mounting edge 313 is used to assemble the inner flow channel structure onto the turbine bearing casing (not shown). The flexible support ring 312 enhances radial rigidity, providing reliable radial support for the inner flow channel 32 and the heat insulation plate 33. The flexible support ring 312 features a flexible axial connection design, which can release internal stress caused by thermal deformation incompatibility between the upper and lower mounting edges 311 and 313, improving the reliability of the inner flow channel structure.

[0043] like Figure 4 As shown, the flexible support ring 312 is a transition structure between an arc and a slope. The axial flexibility of the flexible support ring 312 can be adjusted by adjusting the slope angle α and the arc radius Ra. For example, the axial flexibility can be increased by reducing the slope angle α and increasing the arc radius Ra.

[0044] The inner flow channel 32 and the heat insulation plate 33 are arranged along the airflow direction. The front and rear ends of the inner flow channel 32 and the heat insulation plate 33 are fixedly connected by connecting rivets 35, so that a double-layer heat insulation wall is formed between the inner ring of the turbine bearing casing and the main flow channel. Compared with the single-layer wall structure of the prior art, the thermal radiation effect of the main flow channel gas can be greatly reduced.

[0045] In a preferred embodiment of this application, the heat insulation plate 33 has a corrugated structure. The corrugated structure can coordinate the thermal deformation difference between the heat insulation plate 33 and the inner flow channel 32 under working conditions, and reduce thermal incompatibility stress.

[0046] like Figure 5 As shown, the corrugated structure is a multi-arc transition structure, where each arc has a uniform radius (arc radius Rb is not less than 10 times the wall thickness b). The radial height difference between the upper boundary M1 and the lower boundary M2 of the corrugated structure is not less than 5mm to facilitate forming and meet deformation requirements. The upper and lower boundaries M1 and M2 of the corrugated structure are radially located at the midpoint between the inner flow channel 32 and the inner ring of the turbine bearing casing. Furthermore, the radial distances between the upper and lower boundaries M1 and M2 of the corrugated structure and the inner flow channel and the inner ring of the turbine bearing casing are not less than 4mm, respectively, to avoid interference due to processing and operational deformation.

[0047] The inner flow channel 32 and the heat insulation plate 33 are respectively provided with multiple inner flow channel slots 321 and heat insulation plate slots 331 in the circumferential direction. The circumferential position, size and slot shape of the inner flow channel slots 321 and heat insulation plate slots 331 are matched with the turbine bearing casing support plate to realize the assembly with the rectifier support plate or the turbine bearing casing support plate. The number of inner flow channel slots 321 and heat insulation plate slots 331 is the same as the number of rectifier support plates or turbine bearing casing support plates.

[0048] In some embodiments of this application, the inner flow channel slot 321 and the heat insulation plate slot 331 are machined from the rear end of the inner flow channel 32 and the heat insulation plate 33 towards the front end, respectively. This machining method reduces the structural strength of the inner flow channel 32 and the heat insulation plate 33. To address this, a reinforcing ring 34 is provided in this application. The rear ends of the inner flow channel 32 and the heat insulation plate 33 are fixedly connected by connecting rivets 35 passing through the inner flow channel 32, the heat insulation plate 33, and the reinforcing ring 34, thereby improving the rigidity of the inner flow channel structure, which is beneficial for maintaining the accuracy of the flow channel profile, improving the vibration characteristics of the inner flow channel structure, and improving the reliability of the inner flow channel assembly.

[0049] Compared with the single-wall structure in the prior art, the double-wall flexible inner flow channel structure provided in this application can greatly improve the heat insulation effect of the inner flow channel on the inner ring of the turbine bearing casing, reduce the working temperature of the inner ring, improve the structural reliability and service life of the turbine bearing casing, improve the stiffness of the inner flow channel through reasonable connection design, ensure the surface control requirements, and realize the thermal deformation non-coordination during coordinated operation through two flexible connections, thereby improving the structural reliability.

[0050] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A double-walled flexible internal flow channel structure, characterized in that, include: Internal flow channel (32); The front support ring (31) includes an upper mounting edge (311), a lower mounting edge (313), and a flexible support ring (312) extending in an inverted "S" shape between the upper mounting edge (311) and the lower mounting edge (313). A heat insulation plate (33) is installed between the inner flow channel (32) and the front support ring (31); Among them, the front end of the inner flow channel (32) and the heat insulation plate (33) is fixedly connected to the front support ring (31) by connecting rivets (35) passing through the inner flow channel (32) and the heat insulation plate (33), and the rear end of the inner flow channel (32) and the heat insulation plate (33) is connected by connecting rivets (35) passing through the inner flow channel (32) and the heat insulation plate (33), so that a double-layer heat insulation wall is formed between the inner ring of the turbine bearing casing and the main flow channel. The inner flow channel (32) and the heat insulation plate (33) are respectively provided with an inner flow channel slot (321) and a heat insulation plate slot (331) in the circumferential direction. The circumferential position, size and slot shape of the inner flow channel slot (321) and the heat insulation plate slot (331) are matched with the turbine bearing casing support plate to realize the assembly with the rectifier support plate or the turbine bearing casing support plate.

2. The double-walled flexible internal flow channel structure as described in claim 1, characterized in that, The flexible support ring (312) is a structure formed by the transition between a circular arc and a slope. The axial flexibility of the flexible support ring (312) can be adjusted by adjusting the slope angle and the radius of the circular arc.

3. The double-walled flexible internal flow channel structure as described in claim 1, characterized in that, The heat insulation board (33) is a corrugated structure composed of multiple circular arc transitions.

4. The double-walled flexible internal flow channel structure as described in claim 3, characterized in that, The arc of the heat insulation board (33) is a structure with equal radius, and the radius of the arc is not less than 10 times the wall thickness of the heat insulation board.

5. The double-walled flexible internal flow channel structure as described in claim 3, characterized in that, The radial height difference between the upper boundary and the lower boundary of the corrugated structure is not less than 5 mm.

6. The double-walled flexible internal flow channel structure as described in claim 5, characterized in that, The upper and lower boundaries of the corrugated structure are located radially at the midpoint between the inner flow channel and the inner ring of the turbine bearing casing, and the radial distance between the upper and lower boundaries of the corrugated structure and the inner flow channel and the inner ring of the turbine bearing casing is not less than 4 mm.

7. The double-walled flexible internal flow channel structure as described in claim 1, characterized in that, The number of the inner flow channel slots (321) and the heat insulation plate slots (331) is the same as the number of the rectifier support plate or the turbine bearing casing support plate.

8. The double-walled flexible internal flow channel structure as described in claim 1, characterized in that, The double-walled flexible inner flow channel structure also includes a reinforcing ring (34), which is disposed between the rear end of the inner flow channel (32) and the heat insulation plate (33) and is fixedly connected by connecting rivets.

9. An aircraft engine, characterized in that, The aero-engine includes a double-walled flexible internal flow channel structure as described in any one of claims 1 to 8.

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