A turbine heat dissipation device, a turbine device and a ventilator

Abstract

A turbine heat dissipation device, a turbine device and a ventilator. Among them, the turbine heat dissipation device includes a turbine box. The turbine box has an installation space for placing a turbine assembly, a flow guiding structure arranged in the installation space, and an air inlet communicated with the installation space to allow gas to enter the installation space. The flow guiding structure is configured to allow the gas to flow through the surface of the turbine assembly and then be introduced into the turbine assembly. The flow guiding structure can be used to construct an air flow channel in the turbine box. By changing the flow path of the gas, the contact area between the gas and the turbine assembly is increased, so that the gas can fully exchange heat with the turbine assembly during the flow process to take away part of the heat generated by the turbine assembly, thereby enhancing the heat dissipation effect of the turbine assembly and improving the heat dissipation efficiency.

Description

Technical Field

[0001] The present invention relates to the field of medical equipment, and in particular to a turbine heat sink, a turbine device and a ventilator. Background Art

[0002] As we all know, the turbine, as a key component of the ventilator, mainly plays the role of pressurizing the gas and delivering the gas of a certain pressure to the patient, or using the pressurized gas as a low-pressure gas source for the inhalation valve. Due to the long-term use of the turbine, it often causes the problem of heat dissipation difficulties, that is, during the long-term operation of the turbine, the heat generated by the high-speed turbine motor cannot be quickly dissipated, causing the internal temperature of the ventilator to continue to rise, which seriously affects the service life and working performance of the turbine and the ventilator. Summary of the invention

[0003] The main technical problem solved by the present invention is to provide a turbine heat dissipation device and a turbine device and a ventilator using the heat dissipation device to enhance the heat dissipation effect.

[0004] According to a first aspect, an embodiment provides a turbine heat dissipation device, including a turbine box, wherein the turbine box has:

[0005] Installation space for accommodating turbine components;

[0006] an air inlet, for gas to enter the installation space, the air inlet being in communication with the installation space; and

[0007] The flow guiding structure is arranged in the installation space, and is configured to allow the gas to flow through the surface of the turbine assembly and then be introduced into the turbine assembly to take away at least part of the heat generated by the turbine assembly.

[0008] In one embodiment, the flow guide structure is also configured to divide the installation space into a first chamber and a second chamber, the first chamber is used to accommodate the motor part of the turbine assembly, and the second chamber is used to accommodate the impeller part of the turbine assembly, and the air inlet is connected to the first chamber so that the gas can flow through the surface of the motor part of the turbine assembly and then be introduced into the impeller part of the turbine assembly.

[0009] In one embodiment, the flow guiding structure comprises:

[0010] A support member is disposed around the outer periphery of the turbine assembly in a circumferential direction, wherein a side of the support member facing the turbine assembly is used for sealingly connecting the turbine assembly, and a side of the support member facing away from the turbine assembly is fixed to an inner wall of the turbine box, so that the support member can support and fix the turbine assembly and separate the installation space into a first chamber and a second chamber; and

[0011] A diversion channel is used to connect the first chamber and the second chamber. The diversion channel penetrates through the support member. The air inlet is located on one side of the outer periphery of the turbine assembly, and the diversion channel is on a different side from the side adjacent to the turbine assembly of the air inlet.

[0012] In one embodiment, the support member includes:

[0013] A first support member is located on the outer periphery of the turbine assembly. The side of the first support member facing the turbine assembly is generally in a superior arc structure or a semi-circular arc structure to be able to contact and seal a part of the outer peripheral surface of the turbine assembly; and

[0014] A second support member is located on the outer periphery of the turbine assembly and is spaced opposite to the first support member. The side of the second support member facing the turbine assembly is generally in an inferior arc structure to be able to contact and seal another part of the outer peripheral surface of the turbine assembly;

[0015] When the turbine assembly is placed between the first support member and the second support member, the diversion channel is formed by being jointly surrounded by the adjacent first support member, second support member, the inner wall of the turbine box, and the turbine assembly.

[0016] In one embodiment, the diversion structure further includes a diversion structure. The diversion structure is arranged around the surface of the motor part of the turbine assembly in the circumferential direction to guide the gas to flow from the air inlet to the diversion channel in the circumferential direction.

[0017] In one embodiment, the diversion structure includes:

[0018] A housing part is used to cover and contact the surface of the motor part of the turbine assembly; and

[0019] A plurality of diversion vanes are fixedly arranged around the outer peripheral surface of the housing part in the circumferential direction. The plurality of diversion vanes are arranged at intervals in the axial direction to form diversion grooves between two adjacent diversion vanes. The diversion grooves are used to guide the gas to flow from the air inlet to the diversion channel in the circumferential direction.

[0020] In one embodiment, a heat dissipation assembly is further included. The heat dissipation assembly includes:

[0021] A heat conducting member is located in the installation space. The heat conducting member is used to contact and connect the surface of the turbine assembly to absorb part of the heat generated by the turbine assembly; and

[0022] A heat dissipation member is located outside the installation space. The heat dissipation member is in contact connection with the heat conducting member to dissipate the heat absorbed by the heat conducting member.

[0023] In one embodiment, the heat conducting member includes:

[0024] A first contact end, used for contacting and connecting an end of the motor portion of the turbine assembly adjacent to the impeller portion or the impeller portion of the turbine assembly;

[0025] A second contact end, used for contacting and connecting an end of the motor part of the turbine assembly away from the impeller part, wherein the second contact end is connected to the heat sink; and

[0026] A heat-conducting connection portion is arranged around the outer circumference of the motor part of the turbine assembly, one end of the heat-conducting connection portion is fixed to the first contact end, and the other end is fixed to the second contact end. The heat-conducting connection portion has a heat dissipation port, and the heat dissipation port is used to expose the surface of the motor part of the turbine assembly to the installation space so that gas can flow through the surface of the motor part of the turbine assembly.

[0027] In one embodiment, the turbine box further has a drainage space and a drainage port;

[0028] The drainage port is connected to the drainage space and is used for air and / or oxygen to enter the drainage space;

[0029] The drainage space is connected to the installation space through the air inlet, so that air or oxygen enters the installation space through the air inlet; or the drainage space is used to mix air and oxygen so that the mixture of air and oxygen enters the installation space through the air inlet.

[0030] According to a second aspect, an embodiment provides a turbine device, comprising:

[0031] A heat dissipation device, which adopts the turbine heat dissipation device described in the first aspect; and

[0032] The turbine assembly is arranged in the installation space.

[0033] According to a third aspect, an embodiment provides a ventilator, comprising a housing and a turbine device disposed in the housing, wherein the turbine device is the turbine device described in the second aspect.

[0034] According to the turbine heat dissipation device of the above embodiment, the turbine box includes a turbine box having an installation space for placing a turbine assembly, a flow guide structure arranged in the installation space, and an air inlet connected to the installation space so that gas can enter the installation space, and the flow guide structure is configured to allow gas to flow through the surface of the turbine assembly before being introduced into the turbine assembly. The flow guide structure can be used to construct an air flow channel in the turbine box, and by changing the flow path of the gas, the contact area between the gas and the turbine assembly is increased, so that the gas can fully exchange heat with the turbine assembly during the flow process, so as to take away part of the heat generated by the turbine assembly, thereby enhancing the heat dissipation effect of the turbine assembly and improving the heat dissipation efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1Schematic diagram of the structural assembly of a turbine device for an embodiment.

[0036] Figure 2 It is Figure 1 Schematic diagram of the axial cross-sectional structure of the turbine device A-A direction in

[0037] Figure 3 It is Figure 1 Schematic diagram of the axial cross-sectional structure of the turbine device B-B direction in

[0038] Figure 4 It is Figure 1 Schematic diagram of the circumferential cross-sectional structure of the turbine device in

[0039] Figure 5 Schematic diagram of the gas flow path in a turbine device for an embodiment.

[0040] Figure 6 Schematic diagram of the internal structure of the turbine box in a turbine device for an embodiment.

[0041] Figure 7 Schematic diagram of the structural assembly of the turbine component and the heat dissipation component in a turbine device for an embodiment.

[0042] Figure 8 Exploded schematic diagram of the structural assembly of the turbine component and the heat dissipation component in a turbine device for an embodiment.

[0043] In the figure:

[0044] 100, turbine component; 110, motor part; 120, impeller part; 121, air inlet end; 122, air outlet end;

[0045] 200, turbine box; 210, top shell; 220, base; 230, installation space; 230a, first chamber; 230b, second chamber; 240, air inlet; 250, air outlet; 260, drainage space; 261, deflector; 270, drainage port; 271, gas purification device;

[0046] 300, flow guiding structure; 310, support member; 310a, first support member; 310b, second support member; 320, flow guiding channel; 330, housing part; 340, flow guiding vane; 350, drainage groove;

[0047] 400, heat dissipation component; 410, heat conducting member; 411, first contact end; 412, second contact end; 413, heat conducting connection part; 414, heat dissipation port; 420, heat dissipation member; 421, heat sink group; 422, heat dissipation fan; 430, wire harness through hole. Detailed implementation manner

[0048] The present invention will be further described in detail below in conjunction with the specific embodiments and the accompanying drawings. Similar elements in different embodiments are denoted by related similar element numbers. In the following embodiments, many detailed descriptions are provided to enable a better understanding of the present application. However, those skilled in the art can easily recognize that some of the features can be omitted in different situations, or can be replaced by other elements, materials, or methods. In some cases, some operations related to the present application are not shown or described in the specification to avoid overwhelming the core part of the present application with excessive descriptions. For those skilled in the art, it is not necessary to describe these related operations in detail, and they can fully understand the related operations based on the descriptions in the specification and the general technical knowledge in the art.

[0049] In addition, the features, operations, or characteristics described in the specification can be combined in any suitable manner to form various embodiments. At the same time, the steps or actions in the method description can also be reordered or adjusted in a manner obvious to those skilled in the art. Therefore, the various sequences in the specification and the drawings are only for clearly describing a certain embodiment and do not mean that they are the necessary sequences, unless it is stated that a certain sequence must be followed.

[0050] The serial numbers assigned to the components herein, such as "first", "second", etc., are only used to distinguish the described objects and do not have any sequential or technical meanings. The terms "connection" and "coupling" used in the present application, unless otherwise specified, both include direct and indirect connections (couplings).

[0051] The term "axial direction" used herein refers to the direction of the axis of the turbine device or the turbine assembly; generally, since the turbine motor is one of the core components of the turbine device or the turbine assembly, based on the structural configuration and operating principle of the turbine motor itself, the axis of the turbine motor can be used to represent the overall axis of the turbine device or the turbine assembly; therefore, the "axial direction" can also specifically refer to the direction of the axis of the turbine motor or the axial direction of the turbine motor.

[0052] The term "circumferential direction" used herein refers to the direction around the axis of the turbine device or the turbine assembly, which can be abbreviated as the circumferential direction; generally, it can also specifically refer to the circumferential direction of the turbine motor.

[0053] Please refer to Figures 1 to 8 , an embodiment provides a turbine device that can be used in medical equipment to control gases, such as controlling gas pressurization, transportation, etc.; the turbine device includes a turbine assembly 100 and a turbine heat dissipation device (which can also be abbreviated as the heat dissipation device), which will be described separately below.

[0054] Please refer to Figures 2 to 5 and Figure 7and Figure 8 The turbine assembly 100 is mainly used as a power element of a turbine device and includes a motor part 110 and an impeller part 120. Among them, the impeller part 120 is axially installed at the power output end of the motor part 110, and the impeller part 120 has an air inlet end 121 and an air outlet end 122. The motor part 110 is used to drive the impeller part 120 to rotate at a high speed, so that gas can be sucked into the impeller part 120 from the air inlet end 121 under the rotation effect of the impeller part 120, and after being converted into the required high-pressure gas, it is discharged from the impeller part 120 through the air outlet end 122 for use. In one embodiment, the contour shape of the impeller part 120 can adopt a volute structure in the prior art, so that the air inlet end 121 is axially distributed at one end of the impeller part 120 away from the motor part 110, and the air outlet end 122 is circumferentially distributed on one side of the impeller part 120 (it can also be understood that the air outlet end 122 is tangentially distributed on the periphery of the impeller part 120); of course, the impeller part 120 is not limited to the volute structure.

[0055] Please refer to Figures 1 to 8 For the turbine heat dissipation device; on the one hand, it is used to house the turbine assembly 100 to form a protective structure around the turbine assembly 100, thereby facilitating the overall application and assembly of the turbine device; on the other hand, it plays a role in gas diversion, so that when the gas flows through the surface of the turbine assembly 100, it can take away part of the heat generated by the turbine assembly 100, realize the heat dissipation of the turbine assembly 100, and can finally be introduced into the turbine assembly 100 (specifically the impeller part 120) from the air inlet end 121 and discharged from the turbine assembly 100 through the air outlet end 122.

[0056] In one embodiment, please refer to Figures 1 to 7, the turbine heat dissipation device includes a turbine box 200. The turbine box 200 can adopt a box body or a shell structure formed by relatively assembling and fixing two parts, such as relatively assembling and forming by arranging a top shell 210 and a base 220 in an up-and-down or left-and-right arrangement, so that an installation space 230 with a certain volume can be formed in the turbine box 200, and the turbine assembly 100 is placed in the installation space 230; an air inlet 240 and an air outlet 250 are provided on the box wall of the turbine box 200; wherein, the air inlet 240 communicates with the installation space 230 so that external gas can enter the installation space 230 through the air inlet 240, and the air outlet 250 communicates with the air outlet end 122 so that the gas pressurized by the turbine assembly 100 can be discharged; at the same time, a flow guiding structure 300 is provided in the turbine box 200 (i.e., in the installation space 230), which is configured to guide (or allow, or restrict) the gas entering the installation space 230 to first flow through the surface of the turbine assembly 100, and then enter the area corresponding to the air inlet end 121 and be introduced into the impeller part 121, and finally be discharged based on the connection relationship between the air outlet end 122 and the air outlet 250; during the process of gas flow, especially during the process of flowing through the surface of the turbine assembly 100, the gas can absorb and take away part of the heat generated by the turbine assembly 100.

[0057] The flow guiding structure 300 can be configured into a suitable structural form based on factors such as the outer contour structure of the turbine assembly 100, the internal structural structure of the turbine box 200, the structural combination form between the turbine box 200 and the turbine assembly 100, and the range or area when the gas needs to flow through the surface of the turbine assembly 100.

[0058] In one embodiment, please refer to Figures 2 to 7, the flow guiding structure 300 includes a support member 310 and a flow guiding channel 320; wherein, the support member 310 is arranged around the turbine assembly 100 in the circumferential direction, such as around one end of the motor part 110 adjacent to the impeller part 120 or the part where the motor part 110 is connected and transitioned with the impeller part 120; the side of the support member 310 facing the turbine assembly 100 is sealingly connected to the contour surface of the turbine assembly 100, and the side facing away from the turbine assembly 100 is fixed to the inner wall of the turbine box 200; for example, the support member 310 can be a single component independent of the turbine box 200 and be fixed to the inner wall of the turbine box 200 by means of locking, clamping, etc.; another example is that the support member 310 adopts a structure integrally formed with the turbine box 200 and extends from the inner wall of the turbine box 200 towards the turbine assembly 100. The support member 310 can adopt a plate-like structure that is generally annular as a whole, or can be composed of several components assembled and spliced together and is generally annular as a whole; for example, the corresponding positions of the top shell 210 and the base 220 extend towards the turbine assembly 100 respectively to form a raised structure protruding from the inner wall of the turbine box 200. After the top shell 210 and the base 220 are assembled oppositely, the overall structure of the support member 310 can be formed by using the corresponding relationship between the raised structures.

[0059] The installation space 230 can be roughly divided or separated into a first chamber 230a and a second chamber 230b arranged in sequence along the axial direction by using the support member 310; wherein, the motor part 110 is accommodated by using the first chamber 230, and the impeller part 120 is accommodated by using the second chamber 230b; and the flow guiding channel 320 is arranged through the support member 310 along the axial direction, thereby connecting the first chamber 230a and the second chamber 230b; meanwhile, the air outlet 250 can be arranged in the second chamber 230b, and the air inlet 240 is communicated with the first chamber 230a; for example, the air inlet 240 is arranged at one end of the first chamber 230a far from the second chamber 230b (that is: at the axial end of the motor part 110 far from the impeller part 120), so that the introduced gas can have a large-area contact with the surface of the motor part 110; another example is that the air inlet 240 is arranged on one side in the circumferential direction of the motor part 110 (that is: the upper side of the whole device), and the flow guiding channel 320 is located on the other side in the circumferential direction of the motor part 110 (that is: the lower side of the whole device), so that the air inlet 240 and the flow guiding channel 320 are on different sides of the motor part 110, and the introduced gas can have a large-area contact with the surface of the motor part 110 as much as possible. Of course, the flow guiding channel 320 can also be located on other different sides adjacent to the motor part 110 and the air inlet 240 (such as the left and right sides of the whole device), and it can also make the introduced gas flow through the surface of the motor part 110 as much as possible.

[0060] Based on this, when the turbine assembly 100 is operating, due to the space separation effect generated by the support member 310 between the turbine assembly 100 and the inner wall of the turbine housing 200, the external gas is first introduced into the first chamber 230a through the air inlet 240, and after flowing through the surface of the motor part 110, it enters the second chamber 230b through the diversion channel 320, and is finally introduced by the impeller part 120; since the motor part 110 is the main heat source of the turbine assembly 100, by fully dissipating the heat of the motor part 110, the heat dissipation effect of the turbine assembly 100 or the entire turbine device can be ensured. Therefore, during the process of the external gas flowing through the surface of the motor part 110, sufficient heat exchange with the motor part 110 can be achieved, and thus, relying on the flow effect of the gas, part of the heat generated by the motor part 110 can be taken away to achieve heat dissipation.

[0061] In one embodiment, please refer to Figure 4 、 Figure 6 and Figure 7, the support member 310 includes a first support member 310a and a second support member 310b; wherein, the first support member 310a is located on one side in the circumferential direction of the turbine assembly 100 (specifically, the motor part 110), and the side of the first support member 310a facing the motor part 110 adopts a structural form that generally matches the circumferential contour shape of the motor part 110; generally, the contour shape of the motor part 110 generally adopts a circular columnar structure; thus, in one embodiment, the side of the first support member 310a facing the motor part 110 is generally in the shape of a major arc or a semi-circular arc, so that after the first support member 310a is hermetically connected to the motor part 110, the first support member 310a can be used to partition the installation space 230 from one side in the circumferential direction of the motor part 110; based on the same reason, the second support member 310b is located on the other side in the circumferential direction of the turbine assembly 100 and is spaced opposite to the first support member 310a; in one embodiment, the side of the second support member 310b facing the motor part 110 is generally in the shape of a minor arc, so as to partition the installation space 230 on the other side in the circumferential direction of the motor part 110. In this way, by using the first support member 310a and the second support member 310b, the installation space 230 can be roughly divided into two parts, namely a first chamber 230a and a second chamber 230b; and based on the characteristic that the first support member 310a and the second support member 310b are spaced apart, when the turbine assembly 100 is placed between the first support member 310a and the second support member 310b, the first support member 310a, the second support member 310b, the inner wall of the turbine box 200 and the contour surface of the turbine assembly 100 can be used to jointly enclose and form a diversion channel 320, and the diversion channel 320 is communicated with the first chamber 230a and the second chamber 230b (at this time, the air inlet 240 can be on the same side of the motor part 110 as the first support member 310); in this implementation manner, the structural complexity inside the turbine box 200 can be minimized, and the first support member 310a and the second support member 310b can be directly used to support and clamp the turbine assembly 100; at the same time, the first support member 310a and the second support member 310b can be respectively located in different parts of the turbine box 200, such as respectively arranged on the inner walls of the top shell 210 and the base 220, so as to facilitate the disassembly and assembly of the turbine assembly 100.

[0062] In another embodiment, the first support member 310a and the second support member 310b can also jointly form an annular support structure, arrange one of the first support member 310a and the second support member 310b and the air inlet 240 on the same side in the circumferential direction of the motor part 110, and open a through-hole structure on the other one as the diversion channel 320.

[0063] In one embodiment, there are multiple support members 310. Each support member 310 extends along the axial direction between the inner wall of the turbine box 200 and the contour surface of the turbine assembly 100 (i.e., from the end of the motor part 110 away from the impeller part 120 to the air inlet end 121), and the multiple support members 310 are arranged at intervals in the circumferential direction. In this way, on the one hand, it is equivalent to using the multiple support members 310 to divide the installation space 230 in the circumferential direction, so that each support member 310 can support and fix the turbine assembly 100 along the axial direction. On the other hand, the structural gap between two adjacent support members 310 can be used as the diversion channel 320, so that the gas can flow along the axial direction through the surfaces of the motor part 110 and the impeller part 120. At this time, the air inlet 240 can be communicated with the end of the installation space 230 away from the impeller part 120, so that the introduced gas can sequentially flow through the surfaces of the motor part 110 and the impeller part 120, thereby extending the distance of gas flow and ensuring the heat dissipation effect of the turbine assembly 100.

[0064] In other embodiments, the support member 310 can also adopt a spiral structural form, that is, the support member 310 presents a spiral walking structural configuration between the inner wall of the turbine box 200 and the contour surface of the turbine assembly 100. Thus, after the turbine box 200 and the turbine assembly 100 are combined, a diversion channel 320 that spirally surrounds the turbine assembly 100 can be formed in the installation space 230. This implementation method can further extend the distance of gas flow and achieve sufficient heat dissipation of the turbine assembly 100.

[0065] In one embodiment, please refer to Figures 2 to 5 and Figure 7 and Figure 8, the diversion structure 300 further includes a drainage structure which is arranged around the surface of the motor part 110 of the turbine assembly 100 in the circumferential direction, mainly used to guide the gas entering the first chamber 230a from the air inlet 240 to flow along the circumferential direction through the surface of the motor part 110 and finally flow to the diversion channel 320. The drainage structure includes a housing part 330 and a plurality of diversion vanes 340; wherein, the housing part 330 is arranged to cover and contact the surface of the motor part 110 of the turbine assembly 100 to form a covering structure around the contour of the motor part 110. The housing part 330 can be made of a heat-conducting material such as metal, so as to absorb and transfer the heat generated by the motor part 110 through the contact between the housing part 330 and the motor part 110; the diversion vanes 340 are fixedly arranged around the outer peripheral surface of the housing part 330 in the circumferential direction (such as integrally formed with the housing part 330 or independently installed on the housing part 330), and a plurality of diversion vanes 340 are arranged at intervals in the axial direction; on the one hand, by using the characteristic that a plurality of diversion vanes 340 are arranged at intervals, a drainage groove 350 can be formed between two adjacent diversion vanes 340 to be distributed around the surface of the motor part 110 in the circumferential direction. After the gas is introduced into the first chamber 230a through the air inlet 240, under the action of the drainage groove 350, the gas can flow along the circumferential direction through the surface of the motor part 110 to increase the contact area between the gas and the surface of the motor part 110, so that the gas can take away the heat during the flow process; on the other hand, in specific implementation, the diversion vanes 340 can be made of the same material as the housing part 330 or a material with a similar heat-conductivity coefficient, so as to absorb the heat conducted by the housing part 330 and dissipate the heat into the first chamber 310a to be taken away by the flowing gas; or take away the heat through contact with the gas.

[0066] In another embodiment, the housing part 330 can also be omitted, and a drainage structure can be directly constructed and formed by using a plurality of diversion vanes 340 to restrict or guide the gas to flow along the circumferential direction through the surface of the motor part 110. In other embodiments, the housing part 330 and the diversion vanes 340 can also be part of the motor part 110, that is, the housing of the motor part 110. By optimizing the structure design of the housing of the motor part 110 or selecting a turbine motor with a similar structure, after the motor part 110 is assembled in the turbine box 200, the corresponding drainage structure can be naturally formed.

[0067] Please refer to Figures 1 to 8, A turbine device provided by an embodiment further includes a heat dissipation component 400. The heat dissipation component 400 includes a heat conducting member 410 and a heat dissipating member 420. Among them, the heat conducting member 410 is located in the installation space 230 and is in contact connection with the surface of the turbine assembly 100 (such as the surface of the motor part 110 or the housing part 330 of the foregoing embodiment), and is mainly used to absorb and conduct part of the heat generated by the turbine assembly 100. The heat dissipating member 420 is located outside the installation space 230 and is in contact connection with the heat conducting member 410, and is mainly used to absorb the heat absorbed and conducted by the heat conducting member 410 and at the same time dissipate heat to the external space of the turbine device. Based on comprehensive consideration of factors such as the internal structure of the turbine box 200 and the structural form of the diversion structure, the heat dissipation component 400 can be arranged in the axial direction or in the circumferential direction. Thus, for the overall turbine device, part of the heat generated by the turbine assembly 100 is carried away by the flowing gas during the process of the gas flowing through the surface of the turbine assembly 100, and the other part can rely on the heat dissipation component 400 to dissipate heat to the external space of the whole device in a heat conduction manner, so as to achieve a dual heat dissipation effect and effectively improve the heat dissipation efficiency.

[0068] In one embodiment, please refer to Figures 2 to 5 and Figure 7 and Figure 8, the heat conducting member 410 as a whole adopts a cylindrical structure approximately matching the shape of the turbine assembly 100, which includes a first contact end 411, a second contact end 412 and a heat conducting connection portion 413; wherein, the first contact end 411 adopts an annular structure and is in contact connection with one end of the motor part 110 of the turbine assembly 100 adjacent to the impeller part 120 or in contact connection with the impeller part 120 in a sleeved manner; the second contact end 412 is arranged opposite to the first contact end 412 in the axial direction, and it can adopt an annular structure similar to the first contact end 411 or a plate-like structure, so as to make a large-area contact connection with the end of the motor part 110 of the turbine assembly 100 away from the impeller part 120, and the heat dissipating member 420 is connected to the second contact end 412; and the heat conducting connection portion 413 is located between the first connection end 411 and the second connection end 412, one end of which is fixed to the first contact end 411 and the other end is fixed to the second contact end 412, and the heat conducting connection portion 413 is distributed around the motor part 110 of the turbine assembly 100 in the circumferential direction; the heat conducting connection portion 413 can adopt a cylindrical structure with a through-hole structure or be formed by combining a plurality of strip-shaped objects, so that the entire heat conducting connection portion 413 has a heat dissipation port 414 that can expose the surface of the motor part 110 of the turbine assembly 100 to the installation space 230; thus, the heat absorbed by the first contact end 411 can be partially conducted to the second contact end 412 through the heat conducting connection portion 413, and the heat absorbed by the second contact end 412 can be partially conducted to the heat dissipating member 420, and the heat is dissipated to the external space of the device by the heat dissipating member 420 to achieve the conduction heat dissipation of the turbine assembly 100. At the same time, due to the existence of the heat dissipation port 414, structural conditions are created for the gas introduced into the installation space 230 to flow through the surface of the motor part 110, so that the gas can directly contact the surface of the motor part 110, thereby completing the heat exchange.

[0069] In one embodiment, please refer to Figure 4 , Figure 7 and Figure 8 , the heat conducting connection portion 413 is spaced apart (or non-contact arranged) from the surface of the motor part 110, so as to form a certain structural gap between the heat conducting connection portion 413 and the surface of the motor part 110. Due to the existence of this structural gap, gas can enter the space formed by the heat conducting connection portion 413 and the surface of the motor part 110 through the heat dissipation port 414, thereby ensuring to the greatest extent that the gas can directly flow through the surface of the motor part 110 and creating conditions for enhancing the heat exchange effect.

[0070] In one embodiment, please refer to Figure 1 , Figure 2 , Figure 3 , Figure 5 and Figure 7, the heat dissipation component 420 includes a heat sink group 421 and a heat dissipation fan 422; among them, the heat sink group 421 is in contact connection with the second contact end 412, and the heat dissipation fan 422 is arranged at one end of the heat sink group 421 away from the second contact end 412; thus, through the cooperation of the heat sink group 421 and the heat dissipation fan 422, a forced heat dissipation structure can be formed in the external space of the turbine box 200 or the whole device, so that part of the heat absorbed by the heat dissipation component 400 can be quickly dissipated, further improving the heat dissipation efficiency.

[0071] In addition, during specific implementation, a wire passing structure can also be arranged in the heat dissipation component 400, so that the externally drawn connection wire harness of the motor part 110 can be led out to the outside of the whole device through the wire passing structure, ensuring the safety of the operation of the turbine component 100; specifically, a wire harness through hole 430 can be arranged in a penetrating manner along the axial direction of the second contact end 412 and the heat sink group 421, and the wire harness through hole 430 is used as the wire passing structure, so that the externally drawn connection wire harness can be led out through the wire harness through hole 430; thus, when the gas in the turbine box 200 is oxygen-rich gas, after leading out the externally drawn connection wire harness from the turbine box 200 and then making an electrical connection with other associated devices, it can prevent the oxygen-rich gas from being accidentally ignited when the motor part 110 is powered on, providing a guarantee for the safe operation of the turbine component 100.

[0072] In one embodiment, please refer to Figure 3 , Figure 4 and Figure 5 , the turbine box 200 further has a drainage space 260 and a drainage port 270; among them, the drainage space 260 is arranged side by side with the installation space 230, such as arranged in an up-and-down or left-and-right arrangement manner, and the drainage space 260 is communicated with the installation space 260 through an air inlet 240, mainly used to extend the flow distance of the gas. Especially when the gas required by the turbine device or the medical device to which it is applied is oxygen-rich gas, the drainage space 260 can be used to make the air and oxygen and the like fully mixed to form oxygen-rich gas; for example, a plurality of flow guide plates 261 can be arranged in the drainage space 260 to construct a maze-like gas flow path in the drainage space 260 by using the flow guide plates 261, so as to realize the extension of the gas flow distance or the full mixing between gases; the drainage port 270 is communicated with the drainage space 260, so that external air and / or oxygen and the like can enter the drainage space 260. The turbine box also has a drainage space and a drainage port. In a specific embodiment, a gas purification device 271, such as a filter screen, a gas filter, etc., can be arranged at the drainage port 270 to ensure that the gas entering the turbine box 200 meets the corresponding requirements.

[0073] It should be noted that the turbine heat dissipation device described in this embodiment is not limited to being applied to the turbine assembly in any of the foregoing embodiments, and it can also be used to dissipate heat from turbine assemblies with other structural configurations or other application purposes to meet different application requirements.

[0074] Based on the turbine device of the foregoing embodiment, in combination with Figures 1 to 8 , the present application also provides a ventilator, which includes a housing, a turbine device, and other components that exist as needed; wherein, the turbine device adopts the turbine device of any of the foregoing embodiments, and the turbine device is installed and fixed in the housing in a detachable manner or the like. When the ventilator is operating, by utilizing the high-speed rotation effect generated by the motor part 110 driving the impeller part 120, external gas can enter the installation space 230 through the air inlet 240 and the like, and under the constraint of the guiding structure, flow through the surface of the turbine assembly 100, and finally be introduced into the impeller part 120 through the air inlet end 121. After being converted into the required high-pressure gas, it is discharged through the air outlet end 122 for use; during this process, part of the heat generated by the turbine assembly 100 can be carried away by the flowing gas, and the other part can be dissipated to the outside space of the turbine device or the ventilator through the heat dissipation assembly 400, thereby achieving a dual heat dissipation effect, effectively improving the heat dissipation efficiency, and providing guarantee for the safe operation of the turbine assembly 100 and extending the service life of the turbine assembly 100 and surrounding devices.

[0075] The above uses specific examples to elaborate on the present invention, which is only used to help understand the present invention and is not intended to limit the present invention. For those skilled in the technical field to which the present invention pertains, based on the idea of the present invention, several simple deductions, deformations, or substitutions can also be made.

Claims

1. A turbine heat dissipation device, characterized in that, A turbine box is included, the turbine box having: Installation space for accommodating turbine components; An air inlet, for gas to enter the installation space, the air inlet being in communication with the installation space; as well as a flow guiding structure configured to allow gas to flow through the surface of the turbine assembly and then be introduced into the turbine assembly to take away at least part of the heat generated by the turbine assembly; the flow guiding structure is arranged in the installation space and divides the installation space into a first chamber and a second chamber, the first chamber is used to accommodate the motor part of the turbine assembly, and the second chamber is used to accommodate the impeller part of the turbine assembly, and the flow guiding structure includes a flow guiding channel and a flow guiding structure; The air inlet and the guide channel are located on opposite sides of the motor part in the circumferential direction, the guide channel connects the first chamber and the second chamber, and the air inlet connects the first chamber, so that the gas can flow through the surface of the motor part and then be introduced into the impeller part by the guide channel; The drainage structure includes a shell portion and a plurality of guide vanes, the shell portion is used to cover and contact the surface of the motor portion, the guide vanes are fixed around the outer circumferential surface of the shell portion along the circumferential direction, and the plurality of guide vanes are arranged at intervals along the axial direction of the motor portion to form a drainage groove between two adjacent guide vanes; the drainage groove is used to guide the gas to flow from the air inlet along the circumferential direction to the drainage channel.

2. The turbine heat dissipation device according to claim 1, characterized in that, The guide structure also includes a support member, which is arranged around the outer circumference of the turbine assembly in a circumferential direction; the side of the support member facing the turbine assembly is used for sealingly connecting the turbine assembly, and the side of the support member facing away from the turbine assembly is fixed to the inner wall of the turbine box, so that the support member can support and fix the turbine assembly and divide the installation space into a first chamber and a second chamber; the guide channel runs through the support member.

3. The turbine heat dissipation device according to claim 2, characterized in that, The support member comprises: a first support member, located at the outer periphery of the turbine assembly, wherein a side of the first support member facing the turbine assembly is substantially in a major arc structure or a semicircular arc structure so as to be able to contact and seal with a portion of the outer peripheral surface of the turbine assembly; and A second support member is located at the outer periphery of the turbine assembly and is spaced apart from the first support member, wherein a side of the second support member facing the turbine assembly is substantially in a minor arc structure so as to be able to contact and seal with another portion of the outer peripheral surface of the turbine assembly; When the turbine assembly is placed between the first support member and the second support member, the flow guide channel is formed by the adjacent first support member, the second support member, the inner wall of the turbine box and the turbine assembly.

4. The turbine heat dissipation device according to claim 1, characterized in that, Also included is a heat dissipation component, the heat dissipation component comprising: a heat conducting member, located in the installation space, and used for contacting and connecting a surface of the turbine assembly to absorb part of the heat generated by the turbine assembly; and The heat sink is located outside the installation space and is in contact with the heat conducting member to dissipate heat absorbed by the heat conducting member.

5. The turbine heat dissipation device according to claim 4, characterized in that, The heat conducting member comprises: A first contact end, used for contacting and connecting an end of the motor portion of the turbine assembly adjacent to the impeller portion or the impeller portion of the turbine assembly; A second contact end for contacting and connecting one end of the motor part of the turbine assembly away from the impeller part, the second contact end being connected to the heat sink; and A heat conduction connection part is disposed around the outer periphery of the motor part of the turbine assembly. One end of the heat conduction connection part is fixed to the first contact end, and the other end is fixed to the second contact end. The heat conduction connection part has a heat dissipation opening for exposing the surface of the motor part of the turbine assembly to the installation space so that gas can flow through the surface of the motor part of the turbine assembly.

6. The turbine heat dissipation device according to claim 1, characterized in that, The turbine box further has a diversion space and a diversion port; The diversion port communicates with the diversion space for air and / or oxygen to enter the diversion space; The diversion space communicates with the installation space through an air inlet for air or oxygen to enter the installation space through the air inlet; or the diversion space is used to mix air and oxygen so that the mixture of air and oxygen enters the installation space through the air inlet.

7. A turbine device, characterized in that, Comprising: A heat dissipation device using the turbine heat dissipation device according to any one of claims 1-6; And A turbine assembly disposed in the installation space.

8. A ventilator, characterized in that, Comprising a casing and a turbine device disposed in the casing, the turbine device using the turbine device according to claim 7.

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