Star layout for an aeroengine recuperator

Abstract

The present disclosure relates to the technical field of aero-engines, and particularly provides a star-shaped aero-engine recuperator, comprising: a shell and a core device, the front part of the shell is provided with a containing cavity; the core device is arranged in the containing cavity, the core device comprises a first flow dividing device, a second flow dividing device and a plurality of heat exchange devices, the plurality of heat exchange devices are arranged in a star shape, and the heat exchange devices are respectively connected with the first flow dividing device, the second flow dividing device and the shell; first airflow input from the turbine side of the engine enters the heat exchange devices through the first flow dividing device, second airflow input from the compressor side of the engine enters the heat exchange devices through the second flow dividing device, the second airflow exchanges heat with the first airflow in the heat exchange devices, and then the second airflow returns to the combustion chamber of the engine through the second flow dividing device, and the first airflow is exhausted through the shell. The present disclosure makes full use of the space at the tail of the engine, improves the heat exchange capacity of the heat exchange devices, and meets the installation requirements of the aero-engine recuperator.

Description

Technical Field

[0001] This disclosure relates to the field of aero-engine technology, and in particular to a star-shaped aero-engine regenerator. Background Technology

[0002] A regenerative cycle is an improved heat engine cycle that improves cycle efficiency by recovering and utilizing some of the heat in the heat engine cycle. Its core idea is to use part of the heat absorbed from the high-temperature heat source to preheat the working fluid, thereby reducing the heat demand during the heating process, reducing the adverse effects of the working fluid absorbing heat at lower temperatures on cycle efficiency, and improving the efficiency of the heat engine.

[0003] In gas turbines / aero engines, regenerative cycles often utilize compressor stage extraction or direct turbine exhaust to heat the cryogenic working fluid / fuel. Because the regenerator and auxiliary piping inevitably occupy a significant amount of space, the earliest regenerative cycles were implemented in gas turbines. Existing regenerator designs suffer from poor integration with the engine and low heat exchange compactness; therefore, the technological level of the regenerator directly determines the performance of regenerative cycle gas turbines / aero engines. Summary of the Invention

[0004] This disclosure is made in view of the above-mentioned problems. This disclosure provides a star-shaped configuration of an aero-engine regenerator.

[0005] According to one aspect of this disclosure, a star-shaped aero-engine regenerator is provided, comprising: a housing, with a receiving cavity at the front of the housing; a core device disposed in the receiving cavity, the core device including a first flow divider, a second flow divider, and multiple heat exchange devices arranged in a star shape, the heat exchange devices being respectively connected to the first flow divider, the second flow divider, and the housing; a first airflow input from the engine turbine side enters the heat exchange device through the first flow divider, and a second airflow input from the engine compressor side enters the heat exchange device through the second flow divider; the second airflow and the first airflow exchange heat in the heat exchange device, and then the second airflow returns to the engine combustion chamber through the second flow divider, while the first airflow is discharged through the housing.

[0006] Furthermore, according to one aspect of this disclosure, a star-shaped configuration of an aero-engine regenerator includes a fourth flow channel inside the casing and multiple fourth inlets surrounding the receiving cavity, the fourth inlets connecting the heat exchange device and the fourth flow channel.

[0007] A fourth outlet is provided at the rear of the casing, and the fourth outlet is connected to the fourth flow channel.

[0008] Furthermore, according to one aspect of this disclosure, a star-shaped configuration of an aero-engine regenerator includes a core assembly further comprising: The end cap assembly has its front part connected to the rear end of the engine and its rear part connected to the first and second flow dividers, respectively. The end cap device includes a first cylinder, a second cylinder, and a third cylinder arranged concentrically from the inside to the outside. The first cylinder has a first flow channel inside, which is connected to a first flow distribution device. A second flow channel is provided between the first cylinder and the second cylinder, and a third flow channel is provided between the second cylinder and the third cylinder. Both the second and third flow channels are connected to a heat exchange device.

[0009] Furthermore, according to one aspect of this disclosure, a star-shaped configuration of an aero-engine regenerator has a flange at the front of the end cap assembly, through which the tail end of the engine is connected. And / or, a plurality of first support ribs are provided between the first cylinder and the second cylinder.

[0010] Furthermore, according to one aspect of this disclosure, a star-shaped configuration of an aircraft engine regenerator includes a head assembly that further comprises: The first cone is located at the axial position inside the first cylinder, with the tip of the first cone facing the first diversion device to guide the airflow. Multiple second support ribs are provided between the first cone and the first cylinder. And / or, the second diversion device further includes: The second cone is located at the axial position inside the first diverter, with its tip facing the end cap device, and is used to guide the airflow.

[0011] Furthermore, according to one aspect of this disclosure, a star-shaped configuration of an aero-engine regenerator includes a first flow divider comprising: a plurality of first pipe devices arranged in a star configuration, wherein the first pipe devices are respectively connected to a first flow channel and a heat exchange device. And / or, the second diversion device includes: a plurality of second pipe devices arranged in a star shape, the second pipe devices being respectively connected to a second flow channel, a third flow channel and a heat exchange device.

[0012] Furthermore, according to one aspect of this disclosure, in a star-shaped configuration of an aero-engine regenerator, the second duct of the second diversion device is oriented at an acute angle to the radial direction of the end cap, with the angle being between 30° and 60°.

[0013] Furthermore, according to one aspect of this disclosure, a star-shaped aero-engine regenerator has a heat exchange device in a crossflow configuration, comprising: The housing has a first inlet, a first outlet, a second inlet, and a second outlet on its side. The first inlet and the first outlet are positioned opposite each other. The first inlet is connected to a first flow channel, and the first outlet is connected to a fourth flow channel of the housing. The second inlet and the second outlet are positioned opposite each other. The second inlet is connected to a third flow channel, and the second outlet is connected to a second flow channel. Multiple heat exchange plates are disposed inside the shell. The gaps between the heat exchange plates are respectively connected to the first flow channel and the fourth flow channel, and respectively connected to the second flow channel and the third flow channel.

[0014] Furthermore, according to one aspect of this disclosure, in a star-shaped configuration of an aero-engine regenerator, the first inlet and the first outlet of the heat exchange device are arranged in an involute pattern.

[0015] Furthermore, according to one aspect of this disclosure, a star-shaped configuration of an aircraft engine regenerator includes, in addition to: The third cone is located in the fourth flow channel and at the axial position of the housing. The tip of the third cone faces the fourth outlet and is used to guide the airflow.

[0016] According to an embodiment of the present disclosure, a star-shaped aero-engine regenerator improves system integration and heat exchange compactness by integrating the heat exchange device and the flow distribution device. It makes full use of the space at the engine tail, so that the airflow input from the engine turbine side and the airflow input from the engine compressor side can fully exchange heat, thereby significantly improving the heat exchange capacity of the heat exchange device and meeting the installation requirements of aero-engine regenerators.

[0017] It should be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further illustration of the claimed technology. Attached Figure Description

[0018] The above and other objects, features, and advantages of this disclosure will become more apparent from the more detailed description of the embodiments thereof in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of this disclosure and form part of the specification. They are used together with the embodiments of this disclosure to explain the disclosure and do not constitute a limitation thereof. In the drawings, the same reference numerals generally represent the same components or steps.

[0019] Figure 1 This is a perspective view of an aero-engine regenerator according to an embodiment of the present disclosure; Figure 2 This is a perspective view of an aero-engine regenerator according to an embodiment of the present disclosure; Figure 3 This is a front view schematic diagram of an aircraft engine regenerator according to an embodiment of the present disclosure; Figure 4 for Figure 3 Schematic cross-section view along the middle AA; Figure 5 This is a perspective view of the housing according to an embodiment of the present disclosure; Figure 6 This is a perspective view of a core device according to an embodiment of the present disclosure; Figure 7 This is a perspective view of a core device according to an embodiment of the present disclosure; Figure 8 This is a rear view schematic diagram of a core device according to an embodiment of the present disclosure; Figure 9 This is a perspective view of a core device according to an embodiment of the present disclosure, excluding the heat exchange device; Figure 10 This is a perspective view of a heat exchange apparatus according to an embodiment of the present disclosure.

[0020] Explanation of reference numerals in the attached figures: The aircraft engine includes a regenerator 100, a casing 101, a housing 111, a fourth inlet 112, a fourth outlet 113, a third cone 114, a core assembly 102, a first cylinder 121, a second cylinder 122, a third cylinder 123, a first flow divider 124, a second flow divider 125, a heat exchanger 126, a second cone 127, a first cone 128, a head assembly 129, a shell 131, heat exchange fins 132, a first inlet 133, a first outlet 134, a second inlet 135, a second outlet 136, a first flow channel 141, a second flow channel 142, a third flow channel 143, a fourth flow channel 144, a flange 151, and a first support rib 152. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this disclosure more apparent, exemplary embodiments according to this disclosure will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this disclosure, and not all embodiments of this disclosure. It should be understood that this disclosure is not limited to the exemplary embodiments described herein.

[0022] This disclosure provides a star-shaped aero-engine regenerator. By integrating the heat exchange device and the flow distribution device, the system integration and heat exchange compactness are improved. The space at the engine tail is fully utilized, allowing the airflow input from the engine turbine side to fully exchange heat with the airflow input from the engine compressor side, thereby significantly improving the heat exchange capacity of the heat exchange device and meeting the installation requirements of aero-engine regenerators.

[0023] The embodiments of this disclosure will now be described in detail with reference to the accompanying drawings.

[0024] like Figure 1 , Figure 2 , Figure 3 , Figure 4 As shown, this disclosure provides a star-shaped layout aero-engine regenerator 100, including: a housing 101 and a core device 102; The housing 101 is generally ring-shaped, and its cross-section can be regarded as a C-shaped structure. The front of the housing 101 is provided with a receiving cavity 111, which is the installation space for the core device 102. The core device 102 is the core component for airflow heat exchange. The core device 102 is disposed in the receiving cavity 111. The core device 102 includes a first flow divider 124, a second flow divider 125, and multiple heat exchangers 126. The multiple heat exchangers 126 are arranged in a star shape, for example, six heat exchangers 126 are arranged in a hexagonal star shape, and eight heat exchangers 126 are arranged in an octagonal star shape, which can make full use of the circumferential space. The heat exchangers 126 are respectively connected to the first flow divider 124, the second flow divider 125, and the casing 101. The first airflow input from the turbine side of the engine ( Figure 4 (As indicated by arrow F in the image) enters the heat exchanger 126 through the first diversion device 124, and the second airflow input from the engine compressor side ( Figure 4 (As indicated by arrow E in the diagram) The second airflow enters the heat exchanger 126 through the second diversion device 125. The second airflow exchanges heat with the first airflow in the heat exchanger 126. Afterward, the second airflow returns to the engine combustion chamber through the second diversion device 125, while the first airflow is discharged through the casing 101. Figure 4 (As indicated by arrow F in the image).

[0025] In this embodiment of the aircraft engine regenerator 100, the first flow divider 124, the second flow divider 125 and the heat exchanger 126 are integrated, resulting in high heat exchange compactness and significantly improved heat exchange capacity of the heat exchanger 126, thus meeting the installation requirements of the aircraft engine regenerator 100.

[0026] In some possible implementations, such as Figure 2 , Figure 4 , Figure 5 As shown, a fourth flow channel 144 is provided inside the housing 101, and multiple fourth inlets 112 are provided around the receiving cavity 111 in the housing 101. The fourth inlets 112 are connected to the heat exchange device 126 and the fourth flow channel 144. The rear of the housing 101 is provided with a fourth outlet 113, which is connected to the fourth flow channel 144.

[0027] After heat exchange, the first gas flow enters the fourth flow channel 144 through the fourth inlet 112 and is then discharged through the fourth outlet 113.

[0028] In some possible implementations, such as Figure 1 , Figure 3 , Figure 4As shown, the core device 102 also includes: a head device 129, the front part of which is connected to the tail end of the engine, and the rear part is connected to the first diversion device 124 and the second diversion device 125 respectively, and the first airflow and the second airflow both flow through the head device 129. like Figure 3 , Figure 4 As shown, the end cap device 129 includes a first cylinder 121, a second cylinder 122, and a third cylinder 123 arranged concentrically from the inside to the outside. The first cylinder 121 has a first flow channel 141 inside, which is connected to the first flow divider 124. A second flow channel 142 is provided between the first cylinder 121 and the second cylinder 122, and a third flow channel 143 is provided between the second cylinder 122 and the third cylinder 123. Both the second flow channel 142 and the third flow channel 143 are connected to the heat exchange device 126. The second flow channel 142 is the path for the first airflow to return to the engine combustion chamber, and the third flow channel 143 is the path for the first airflow to flow to the heat exchange device 126. Through this arrangement, the end cap device 129 forms an integrated intake and exhaust device.

[0029] The end cap device 129 can be integrally formed, for example, by 3D printing technology, or it can be manufactured separately and then welded together.

[0030] In some possible implementations, such as Figure 1 , Figure 3 As shown, a flange 151 is provided at the front of the end cap device 129, which is connected to the tail end of the engine. The flange 151 is specifically located at the end of the third cylinder 123, and is connected to the tail end of the engine at the outermost side of the end cap device 129, which can ensure the leakage-free flow of the first airflow and the second airflow.

[0031] In some possible implementations, such as Figure 1 , Figure 3 , Figure 4 As shown, a plurality of first support ribs 152 are provided between the first cylinder 121 and the second cylinder 122. By providing the first support ribs 152, the structural strength of the end cap device 129 can be guaranteed.

[0032] In some possible implementations, such as Figure 4 As shown, the end cap device 129 further includes: a first cone 128, which is located at the axial position inside the first cylinder 121. The tip of the first cone 128 faces the first diverter 124 and is used to guide the airflow, gather the first airflow into the first flow channel 141, and reduce turbulence. A plurality of second support ribs are provided between the first cone 128 and the first cylinder 121. By providing the second support ribs, the structural strength of the end cap device 129 can be guaranteed.

[0033] In some possible implementations, such as Figure 2 , Figure 4 As shown, the second diversion device 125 further includes a second cone 127, which is located at the axial position inside the first diversion device 124. The tip of the second cone 127 faces the end cap device 129 and is used to guide the airflow, disperse the first airflow to multiple heat exchange devices 126, and reduce turbulence.

[0034] In some possible implementations, such as Figure 7 , Figure 8 , Figure 9 As shown, the first diversion device 124 includes a plurality of first pipe devices, the number of which is equal to the number of heat exchange devices 126. The plurality of first pipe devices are arranged in a star-shaped configuration, for example, six first pipe devices in a hexagonal star configuration or eight first pipe devices in an octagonal star configuration. The first pipe devices are respectively connected to the first flow channel 141 and the heat exchange device 126, and the first airflow flows into the heat exchange device 126 through the first pipe devices. The first diversion device 124 can be integrally formed, for example, by 3D printing technology, or it can be manufactured in parts and then welded together.

[0035] In some possible implementations, such as Figure 6 , Figure 7 , Figure 8 As shown, the second diversion device 125 includes: a plurality of second pipe devices, the number of which is equal to the number of heat exchange devices 126. The plurality of second pipe devices are arranged in a star shape, for example, six second pipe devices are arranged in a hexagonal star shape, and eight second pipe devices are arranged in an octagonal star shape. The second pipe devices are respectively connected to the second flow channel 142, the third flow channel 143 and the heat exchange device 126.

[0036] The second piping device includes two adjacent pipes, one of which connects the second flow channel 142 and the heat exchanger 126, and the other pipe connects the third flow channel 143 and the heat exchanger 126, bypassing the outside of the heat exchanger 126 before connecting to it. The second diversion device 125 can be integrally formed, for example by 3D printing technology, or it can be manufactured in parts and then welded together.

[0037] In some possible implementations, such as Figure 3 , Figure 6 As shown, the orientation of the second pipe assembly of the second diversion device 125 is set at an acute angle to the radial direction of the end cap assembly 129, that is... Figure 3 In this case, α has an angle between 30° and 60°, for example, it can be 44°, which can make full use of the circumferential space and facilitate the flow of air.

[0038] In some possible implementations, such as Figure 4 , Figure 7, Figure 10 As shown, the heat exchanger 126 has a crossflow configuration and can use typical indirect-flow structures such as plate-fin type, printed circuit board type, or single-surface type. Figure 10 As shown, the heat exchange device 126 includes: a housing 131 and a plurality of heat exchange plates 132; The casing 131 is approximately cubic in shape. A first inlet 133, a first outlet 134, a second inlet 135, and a second outlet 136 are provided on the side of the casing 131. The first inlet 133 and the first outlet 134 are positioned opposite each other. The first inlet 133 connects to the first flow channel 141, specifically connecting to the first pipe device of the first diverter 124. The first outlet 134 connects to the fourth flow channel 144 of the casing 101, specifically connecting to the fourth inlet 112 of the casing 101. The second inlet 135 and the second outlet 136 are positioned opposite each other. The second inlet 135 connects to the third flow channel 143, specifically connecting to the second pipe device of the second diverter 125. The second outlet 136 connects to the second flow channel 142, specifically connecting to the second pipe device of the second diverter 125. The pipe connecting to the second inlet 135 in the second pipe device bypasses the outside of the heat exchanger 126 before connecting to the second inlet 135.

[0039] Multiple heat exchange plates 132 are arranged in parallel and are disposed inside the housing 131. The gaps between the heat exchange plates 132 are respectively connected to the first flow channel 141 and the fourth flow channel 144, and respectively connected to the second flow channel 142 and the third flow channel 143.

[0040] The first flow channel 141 is connected to the fourth flow channel 144 through the gaps between the heat exchange fins 132, and the second flow channel 142 is connected to the third flow channel 143. However, the gaps between the heat exchange fins 132 are not connected, so the first airflow and the second airflow will not mix. The first airflow and the second airflow can flow layer by layer between the multiple heat exchange fins 132. The connection between the heat exchange device 126 and the first flow splitter 124 and the second flow splitter 125 can be fixed by welding.

[0041] In some possible implementations, such as Figure 6 , Figure 7 , Figure 8 As shown, the first inlet 133 and the first outlet 134 of the heat exchange device 126 are arranged in an involute pattern, which can make full use of the circumferential space and facilitate the flow of air.

[0042] Because the first outlet 134 is connected to the fourth inlet 112 of the housing 101, and the outer wall of the receiving cavity 111 is circular, the heat exchange device 126 is also designed to be arc-shaped at the first outlet 134.

[0043] In some possible implementations, such as Figure 2 , Figure 4 , Figure 5 As shown, the housing 101 also includes a third cone 114, which is disposed in the fourth flow channel 144 and located at the axial position of the housing 101. The tip of the third cone 114 faces the fourth outlet 113 and is used to guide the airflow, output the first airflow to the fourth flow channel 144, and reduce the occurrence of turbulence.

[0044] The above description, with reference to the accompanying drawings, describes a star-shaped configuration of an aircraft engine regenerator according to an embodiment of the present disclosure, which has the following advantages: By integrating the heat exchanger and the flow splitter, the system integration and heat exchange compactness are improved. The space at the engine tail is fully utilized, allowing the airflow input from the engine turbine side to fully exchange heat with the airflow input from the engine compressor side. This significantly improves the heat exchange capacity of the heat exchanger and meets the installation requirements of the aero-engine regenerator.

[0045] The basic principles of this disclosure have been described above with reference to specific embodiments. However, it should be noted that the advantages, benefits, and effects mentioned in this disclosure are merely examples and not limitations, and should not be considered as essential features of each embodiment of this disclosure. Furthermore, the specific details disclosed above are for illustrative and facilitative purposes only, and are not limitations. These details do not limit the scope of this disclosure to the necessity of employing the aforementioned specific details for implementation.

[0046] The block diagrams of devices, apparatuses, devices, and systems disclosed herein are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, devices, and systems can be connected, arranged, and configured in any manner. Words such as “comprising,” “including,” “having,” etc., are open-ended terms meaning “including but not limited to,” and are used interchangeably with them. The terms “or” and “and” as used herein refer to the terms “and / or,” and are used interchangeably with them unless the context clearly indicates otherwise. The term “such as” as used herein refers to the phrase “such as but not limited to,” and is used interchangeably with it.

[0047] Additionally, as used herein, the "or" used in a list of items beginning with "at least one" indicates a separate list, such that a list of, for example, "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not imply that the described example is preferred or better than other examples.

[0048] It should also be noted that in the systems and methods of this disclosure, the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions to this disclosure.

[0049] Various changes, substitutions, and modifications can be made to the technology described herein without departing from the teachings defined by the appended claims. Furthermore, the scope of the claims of this disclosure is not limited to the specific aspects of the processes, machines, manufactures, events, means, methods, and actions described above. Currently existing or later-developed processes, machines, manufactures, events, means, methods, or actions that perform substantially the same function or achieve substantially the same result as the corresponding aspects described herein can be utilized. Therefore, the appended claims include such processes, machines, manufactures, events, means, methods, or actions within their scope.

[0050] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use this disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of this disclosure. Therefore, this disclosure is not intended to be limited to the aspects shown herein, but rather to be carried out within the widest scope consistent with the principles and novel features disclosed herein.

[0051] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of this disclosure to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations therein.

Claims

1. A star-shaped aero-engine regenerator, characterized in that, include: The housing (101) has a receiving cavity (111) at its front. The core device (102) is disposed in the receiving cavity (111). The core device (102) includes a first flow divider (124), a second flow divider (125), and a plurality of heat exchangers (126). The plurality of heat exchangers (126) are arranged in a star shape. The heat exchangers (126) are respectively connected to the first flow divider (124), the second flow divider (125), and the housing (101). The first airflow input from the turbine side of the engine enters the heat exchange device (126) through the first splitting device (124), and the second airflow input from the compressor side of the engine enters the heat exchange device (126) through the second splitting device (125). The second airflow and the first airflow exchange heat in the heat exchange device (126), and then the second airflow returns to the engine combustion chamber through the second splitting device (125). The first airflow is discharged through the casing (101). The core device (102) further includes: The end cap device (129) is connected to the tail end of the engine at the front and to the first flow divider device (124) and the second flow divider device (125) at the rear. The end cap device (129) includes a first cylinder (121), a second cylinder (122), and a third cylinder (123) arranged concentrically from the inside to the outside. The first cylinder (121) has a first flow channel (141) inside, which is connected to the first flow divider (124). A second flow channel (142) is provided between the first cylinder (121) and the second cylinder (122), and a third flow channel (143) is provided between the second cylinder (122) and the third cylinder (123). Both the second flow channel (142) and the third flow channel (143) are connected to the heat exchange device (126). The first diversion device (124) includes: Multiple first pipe devices are arranged in a star shape, and the first pipe devices are respectively connected to the first flow channel (141) and the heat exchange device (126). And / or, the second diversion device (125) includes: a plurality of second pipe devices arranged in a star shape, the second pipe devices respectively connecting the second flow channel (142), the third flow channel (143) and the heat exchange device (126).

2. The star-shaped aero-engine regenerator according to claim 1, characterized in that, The housing (101) has a fourth flow channel (144) inside, and the housing (101) has a plurality of fourth inlets (112) around the receiving cavity (111). The fourth inlets (112) connect the heat exchange device (126) and the fourth flow channel (144). The rear of the housing (101) is provided with a fourth outlet (113), which is connected to the fourth flow channel (144).

3. The star-shaped aero-engine regenerator according to claim 2, characterized in that, The front part of the end cap device (129) is provided with a flange (151), through which the rear end of the engine is connected; And / or, a plurality of first support ribs (152) are provided between the first cylinder (121) and the second cylinder (122).

4. The star-shaped aero-engine regenerator according to claim 2, characterized in that, The end cap device (129) further includes: The first cone (128) is located at the axial position inside the first cylinder (121), with the tip of the first cone (128) facing the first diverting device (124) to guide the airflow. A plurality of second support ribs are provided between the first cone (128) and the first cylinder (121). And / or, the first shunt device (124) further includes: The second cone (127) is located at the axial position inside the first diverter (124), with the tip of the second cone (127) facing the end cap (129) to guide the airflow.

5. The star-shaped aero-engine regenerator according to claim 2, characterized in that, The orientation of the second pipe device of the second diversion device (125) is set at an acute angle to the radial direction of the end cap device (129), with an angle between 30° and 60°.

6. The star-shaped aero-engine regenerator according to claim 2, characterized in that, The heat exchange device (126) is a crossflow configuration, including: The housing (131) has a first inlet (133), a first outlet (134), a second inlet (135), and a second outlet (136) on its side. The first inlet (133) and the first outlet (134) are arranged opposite to each other. The first inlet (133) is connected to the first flow channel (141), and the first outlet (134) is connected to the fourth flow channel (144) of the housing (101). The second inlet (135) and the second outlet (136) are arranged opposite to each other. The second inlet (135) is connected to the third flow channel (143), and the second outlet (136) is connected to the second flow channel (142). Multiple heat exchange plates (132) are disposed inside the housing (131). The gaps between the heat exchange plates (132) are respectively connected to the first flow channel (141) and the fourth flow channel (144), and respectively connected to the second flow channel (142) and the third flow channel (143).

7. The star-shaped aero-engine regenerator according to claim 6, characterized in that, The first inlet (133) and the first outlet (134) of the heat exchange device (126) are arranged in an involute pattern.

8. The aero-engine regenerator with a star-shaped layout according to any one of claims 2-7, characterized in that, The housing (101) also includes: The third cone (114) is disposed in the fourth flow channel (144) and located at the axial position of the housing (101), with the tip of the third cone (114) facing the fourth outlet (113) to guide the airflow.

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