A heat dissipation structure for an OSFP optical module

Abstract

This invention discloses a heat dissipation structure for an OSFP optical module, belonging to the field of OSFP optical modules. It includes a hollow housing and a circuit board. The housing includes a bottom shell and a top shell covering the bottom shell. Multiple parallel heat dissipation fins are provided on the outer top surface of the top shell. A support assembly is provided on the outer top surface of the top shell. The support assembly includes a support column vertically fixed to the upper surface of the top shell and a limiting crossbar horizontally fixed to the top of the side wall of the support column. The support column and the heat dissipation fins are parallel to each other. This solution uses a frame-like limiting structure formed by the support column and the limiting crossbar to lock the originally independent and extremely thin heat dissipation fins into a high-strength integrated array, thereby enhancing the pressure and shear resistance of the optical module's front end. This prevents damage or deformation of the fins due to mechanical stress in extreme environments such as dense insertion / removal, transportation, or high-intensity vibration, effectively ensuring the smooth and stable flow of heat dissipation.

Description

Technical Field

[0001] This invention relates to the field of OSFP optical modules, and more specifically, to a heat dissipation structure for OSFP optical modules. Background Technology

[0002] As optical communication networks evolve towards 400G, 800G, and even 1.6T, OSFP packaging has become the mainstream packaging form for high-speed optical modules due to its excellent heat dissipation potential and electrical performance. Under high-speed operation, the core optoelectronic devices inside the OSFP module (such as DSP chips, laser drivers, and photoelectric conversion components TOSA / ROSA) will generate enormous heat.

[0003] In existing technologies, high-power optical modules such as OSFPs primarily rely on system fans for forced convection cooling. The design of their surface heat sink fins often struggles to achieve an ideal balance between "effective heat dissipation area" and "aerodynamic drag," resulting in the following technical drawbacks:

[0004] Simply increasing the density of fins to maximize heat dissipation area can lead to a sharp increase in airflow resistance. This not only prevents cooling airflow from penetrating the fin array (creating an airflow bypass effect), but also causes severe heat accumulation above core components (such as DSP chips), leading to thermal failure. Furthermore, conventional straight, continuous fins are prone to forming a thermal boundary layer on the surface, weakening convective heat transfer efficiency, and the singular airflow direction can easily create localized heat dissipation dead zones.

[0005] To address this, a heat dissipation structure for OSFP optical modules is proposed. Summary of the Invention

[0006] To address the problems existing in the prior art, the purpose of this invention is to provide a heat dissipation structure for OSFP optical modules, which can improve heat dissipation by breaking the thermal boundary layer on the surface of the heat dissipation fins through gas flow.

[0007] To solve the above problems, the present invention adopts the following technical solution.

[0008] A heat dissipation structure for an OSFP optical module includes a hollow housing and a circuit board;

[0009] The shell includes a bottom shell and a top shell that covers the bottom shell;

[0010] The outer top surface of the top shell is provided with multiple parallel heat dissipation fins;

[0011] Support components are provided on the outer top surface of the top shell;

[0012] The support assembly includes a support column that is vertically fixed to the upper surface of the top shell, and a limiting crossbar that is horizontally fixed to the top of the side wall of the support column;

[0013] Among them, the supporting column is parallel to the heat dissipation fins; a horizontal positioning groove is opened on the vertical edge of the same side of all heat dissipation fins, and a limiting crossbar is horizontally spanned and embedded in each horizontal positioning groove, and the limiting crossbar is fixedly connected to each heat dissipation fin.

[0014] The support column is made of a high thermal conductivity material and has a vertically opened hot pneumatic cavity inside. An elastic diaphragm is installed horizontally and sealed inside the hot pneumatic cavity. The elastic diaphragm divides the cavity into a phase change expansion chamber at the bottom and a pneumatic extrusion chamber at the top. The phase change expansion chamber is filled with a low boiling point phase change working fluid.

[0015] The limiting crossbar has a hollow interior forming a transverse flow guide cavity, which is in fluid communication with the top of the pneumatic extrusion chamber; the limiting crossbar has multiple jet micro-holes on the side facing the heat dissipation fins that are in communication with the transverse flow guide cavity.

[0016] Furthermore, the low-boiling-point phase change working fluid in the phase change expansion chamber is an electronic-grade insulating fluorinated liquid.

[0017] Furthermore, the inner bottom surface of the top shell is provided with a downwardly protruding heat-conducting boss.

[0018] Furthermore, a flow-induced vibration component is provided within the jet micro-orifice;

[0019] The flow-induced vibration assembly includes an elastic microcantilever fixed at one end to the inner wall of the jet microorifice, and a turbulence block suspended at the free end of the elastic microcantilever; the turbulence block is suspended in the center of the exhaust channel of the jet microorifice.

[0020] Furthermore, the elastic diaphragm is a bistable snap-start elastic diaphragm, which has a downwardly concave initial steady-state structure and an upwardly convex trigger steady-state structure.

[0021] Furthermore, a flexible capillary wick is suspended at the center of the lower surface of the elastic diaphragm; the bottom end of the flexible capillary wick hangs down naturally and is immersed in the phase change working fluid at the bottom of the phase change expansion chamber.

[0022] Furthermore, the elastic microcantilever is made of a two-way shape memory alloy.

[0023] Furthermore, a one-way air intake micro-valve is installed on the top shell; the output end of the one-way air intake micro-valve extends into the pneumatic extrusion chamber;

[0024] A one-way exhaust micro-valve is fixedly embedded in the pneumatic extrusion chamber, and the output end of the one-way exhaust micro-valve extends into the transverse guide cavity.

[0025] Furthermore, a porous sintered metal layer is laid on the inner bottom surface of the phase change expansion chamber, and the porous sintered metal layer is immersed in the low-boiling-point phase change working fluid at the bottom of the phase change expansion chamber.

[0026] The bottom end of the flexible capillary liquid-absorbing core extends and is directly attached to the upper surface of the porous sintered metal layer.

[0027] Furthermore, a dustproof and breathable membrane is installed at the air inlet of the one-way air intake micro-valve; and several auxiliary heat dissipation horizontal lines are provided on the bottom outer surface of the bottom shell.

[0028] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0029] (1) This solution uses a frame-type limiting structure composed of support columns and limiting crossbars to lock the originally independent and extremely thin heat dissipation fins into a high-strength overall array, thereby enhancing the pressure resistance and shear resistance of the front end of the optical module and preventing the fins from being damaged or deformed due to mechanical stress in extreme environments such as dense plugging and unplugging, transportation or high-intensity vibration, thus playing a long-term role in ensuring the smooth and stable heat dissipation channel.

[0030] (2) This scheme can directly convert harmful heat load into high-frequency, high initial kinetic energy pulse turbulence through the nonlinear buckling rapid release mechanism of the bistable jump elastic diaphragm, thereby forming an aerodynamic brush that breaks through and peels off the airflow stagnation zone and thermal boundary layer deep in the heat dissipation fins, thereby improving the heat dissipation response speed and heat exchange efficiency of the optical module under transient thermal shock.

[0031] (3) This solution transforms the reciprocating deformation of the elastic diaphragm into a true “one-way cold air pump” by combining a one-way intake micro-valve and a one-way exhaust micro-valve. Fresh cold air is drawn in during the intake phase and ejected at high speed during the exhalation phase, which improves the heat dissipation effect. At the same time, the elastic micro-cantilever made of shape memory alloy can automatically change the exhaust direction, realize targeted deflection and wide sweep of the heat source root and other hidden areas, and further improve the heat carrying capacity of the airflow in a single injection. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0033] Figure 2 This is a front cross-sectional view of the present invention;

[0034] Figure 3 For the present invention Figure 1 Enlarged structural diagram at point M;

[0035] Figure 4 For the present invention Figure 2 Enlarged structural diagram at point A;

[0036] Figure 5 For the present invention Figure 2 Enlarged structural diagram at point B;

[0037] Figure 6This is a schematic diagram of the combined structure of the heat dissipation fins and the limiting crossbar of the present invention;

[0038] Figure 7 This is a schematic diagram of the combined structure of the heat dissipation fins and the transverse positioning groove of the present invention.

[0039] Explanation of the labels in the diagram:

[0040] 1. Shell; 101. Bottom shell; 102. Top shell; 2. Circuit board; 3. Heat dissipation fins; 4. Support column; 5. Limiting crossbar; 6. Thermodynamic cavity; 601. Phase change expansion chamber; 602. Pneumatic extrusion chamber; 7. Elastic diaphragm; 8. Lateral flow guide cavity; 9. Jet micropores; 10. Thermally conductive boss; 11. Elastic microcantilever; 12. Turbulence block; 13. Flexible capillary liquid suction core; 14. One-way air intake microvalve; 15. One-way exhaust microvalve; 16. Porous sintered metal layer; 17. Dustproof and breathable membrane. Detailed Implementation

[0041] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0042] Example 1:

[0043] Please see Figures 1 to 7 A heat dissipation structure for an OSFP optical module includes a hollow housing 1 and a circuit board 2. The circuit board 2 is provided with core heat-generating components, including a DSP chip and a photoelectric conversion component.

[0044] The housing 1 includes a bottom shell 101 and a top shell 102 covering the bottom shell 101;

[0045] Multiple parallel heat dissipation fins 3 are provided on the outer top surface of the top shell 102;

[0046] A support assembly is provided on the outer top surface of the top shell 102;

[0047] The support assembly includes a support column 4 that is vertically fixed to the upper surface of the top shell 102, and a limiting crossbar 5 that is horizontally fixed to the top of the side wall of the support column 4.

[0048] Among them, the supporting column 4 is parallel to the heat dissipation fins 3; a horizontal positioning groove is opened on the vertical edge of the same side of all heat dissipation fins 3, and the limiting crossbar 5 is horizontally spanned and embedded in each horizontal positioning groove, and the limiting crossbar 5 is fixedly connected to each heat dissipation fin 3.

[0049] The frame-type limiting structure formed by the supporting column 4 and the limiting crossbar 5 locks the originally independent and extremely thin heat dissipation fins 3 into a high-strength integrated array; it enhances the pressure resistance and shear resistance of the front end of the optical module, thereby preventing the fins from being damaged or deformed due to mechanical stress in the optical module during dense plugging and unplugging, transportation or high-intensity vibration environment, and plays a role in ensuring a long-term stable heat dissipation channel.

[0050] The support column 4 is made of a high thermal conductivity material and has a vertically opened hot pneumatic cavity 6 inside. An elastic diaphragm 7 is installed in the hot pneumatic cavity 6 in a horizontally sealed manner. The elastic diaphragm 7 divides the cavity into a phase change expansion chamber 601 located below and a pneumatic extrusion chamber 602 located above. The phase change expansion chamber 601 is filled with a low boiling point phase change working fluid.

[0051] The limiting crossbar 5 has a hollow interior forming a transverse flow guide cavity 8, which is in fluid communication with the top of the pneumatic extrusion chamber 602; the limiting crossbar 5 has multiple jet microholes 9 on the side facing the heat dissipation fins 3 that are in communication with the transverse flow guide cavity 8.

[0052] When the module load suddenly increases and heat is transferred to the support column 4, the phase change working fluid is heated and vaporized and expands, forcing the elastic diaphragm 7 to bulge and deform upward, thereby compressing the air in the pneumatic compression chamber 602, forcing the air to be ejected at high speed through the transverse guide cavity 8 and the jet micro-hole 9, forming a disturbed micro-jet that directly hits the gap between adjacent heat dissipation fins 3.

[0053] By integrating a passive thermal pulsating micro-jet system inside the supporting column 4 and the limiting crossbar 5, the module temperature exhibits minute dynamic peaks and troughs during actual operation, accompanying transient changes in data throughput and dynamic adjustments to external cooling airflow. These temperature fluctuations alternately drive the boiling and condensation of the phase change working fluid, causing the elastic diaphragm 7 to undergo a "breathing" reciprocating deformation. This deformation continuously pumps high-speed airflow from the jet micro-holes 9, precisely penetrating the airflow stagnation zone and thermal boundary layer deep within the heat dissipation fins 3. This directly converts harmful heat loads into air kinetic energy that enhances convective heat transfer, thereby improving the heat dissipation response speed under transient thermal shock.

[0054] like Figure 2 As shown, the low-boiling-point phase change working fluid in the phase change expansion chamber 601 is an electronic-grade insulating fluorinated liquid; and the boiling point threshold of the electronic-grade insulating fluorinated liquid matches the temperature control trigger threshold of the core heating components of the optical module.

[0055] By employing electronic-grade insulating fluorinated liquid as the phase change working fluid in the thermally driven microfluidic system, the extremely low latent heat of vaporization and highly adjustable boiling point of the fluorinated liquid give the aerodynamic structure extremely high thermal response sensitivity, enabling it to rapidly vaporize and respond instantly when the temperature of the optical module rises slightly. On the other hand, its excellent dielectric insulation properties completely eliminate the potential leakage and short-circuit risks of the working fluid in the miniaturized packaging structure, meeting the stringent electrical reliability requirements of high-speed optical modules.

[0056] like Figure 5 As shown, the inner bottom surface of the top shell 102 is provided with a downwardly protruding heat-conducting boss 10. The lower surface of the heat-conducting boss 10 is directly attached to the upper surface of the core heat-generating component through an insulating heat-conducting medium, thereby facilitating heat dissipation.

[0057] like Figure 4 As shown, a flow-induced vibration component is provided inside the jet micro-orifice 9;

[0058] The flow-induced vibration assembly includes an elastic microcantilever 11 with one end fixed to the inner wall of the jet micro-orifice 9, and a turbulence block 12 suspended at the free end of the elastic microcantilever 11; the turbulence block 12 is suspended at the center of the exhaust channel of the jet micro-orifice 9.

[0059] When the high-speed airflow discharged from the pneumatic compression chamber 602 impacts the turbulence block 12, the pneumatic pressure and the restoring force of the elastic microcantilever 11 are coupled together, forcing the turbulence block 12 to undergo high-frequency aerodynamic flutter.

[0060] This high-frequency vibration modulates the originally flat, narrow-coverage unidirectional microjet into a turbulent, pulsating jet that sweeps across a wide area at multiple angles. This powerful "dynamic sweeping" airflow forms an invisible aerodynamic brush, thereby expanding the effective contact area between the cooling airflow and the heat dissipation fins 3. Furthermore, it can cut and peel off the thermal boundary layer attached to the fin surface with turbulence, thus improving the convective heat transfer enhancement effect.

[0061] like Figure 5 As shown, the elastic diaphragm 7 is a bistable snap-start elastic diaphragm 7, which has a downwardly concave initial steady-state structure and an upwardly convex trigger steady-state structure.

[0062] When the phase change working fluid in the phase change expansion chamber 601 is heated and vaporized, and the accumulated fluid pressure reaches the preset first pressure threshold, the bistable jump elastic diaphragm 7 instantly buckles and reverses to the trigger steady state, and rapidly compresses the air in the pneumatic compression chamber 602 in the form of pulses, forming a high-frequency transient microjet.

[0063] The bistable jump elastic diaphragm 7 is existing technology and will only be briefly described below without further elaboration: To ensure the high-frequency transient burst force of the above-mentioned microjet system at the microscale, the bistable jump elastic diaphragm 7 in this embodiment adopts a mechanical design based on the principle of nonlinear buckling instability. Its physical mechanism is similar to the mature thermosensitive jump structure (such as a metal dome or a temperature-controlled bimetallic strip) in the field of precision industrial control, but in this scheme, it is cross-boundary coupled with the fluid phase change system.

[0064] The specific working mechanism is as follows: In the initial energy storage stage of the phase change working fluid being heated and expanded, the bistable jump elastic diaphragm 7 relies on its own structural stiffness to maintain the initial steady state of being concave. At this time, the elastic diaphragm 7 is in the "elastic energy storage" state with high strain energy, which transforms the slow thermodynamic expansion process into the accumulation of mechanical potential energy.

[0065] When the fluid pressure inside the phase change expansion chamber 601 reaches the critical instability load of the elastic diaphragm 7 structure, the stress balance of the elastic diaphragm 7 is instantly broken, and a nonlinear buckling reversal occurs within an extremely short time (milliseconds), transitioning to an upward-convex triggered steady state. This nonlinear transformation from "slow thermal expansion" to "extremely rapid mechanical release" breaks through the physical bottleneck of low flow velocity and lack of explosive force in the traditional linear elastic diaphragm 7, providing a pulsed aerodynamic gas source with extremely high initial kinetic energy for the jet micro-orifice 9, thereby ensuring the reliable generation of high Reynolds number turbulent jets.

[0066] like Figure 5 As shown, a flexible capillary liquid-absorbing core 13 is suspended at the center of the lower surface of the elastic diaphragm 7; the bottom end of the flexible capillary liquid-absorbing core 13 hangs down naturally and is immersed in the phase change working medium at the bottom of the phase change expansion chamber 601.

[0067] The flexible capillary suction core 13 is used to adsorb low-boiling-point phase change working fluid when the elastic diaphragm 7 is in the initial steady state; and when the elastic diaphragm 7 bulges upward and deforms, it is driven to at least partially detach from the liquid surface of the low-boiling-point phase change working fluid to form a suspended phase change evaporation surface.

[0068] First, in the initial stage of a slight increase in system temperature, the flexible capillary wick 13 uses microporous capillary force to draw the fluorinated liquid at the bottom to the near end of the elastic diaphragm 7, thereby expanding the effective surface area of ​​the gas-liquid phase change and increasing the initial evaporation rate.

[0069] Secondly, when the elastic diaphragm 7 bulges upwards instantaneously, it causes the flexible capillary liquid-absorbing core 13 to be rapidly pulled up and detached from the bottom liquid surface. At this moment, the fluorinated liquid attached to the fiber pores is instantly and completely exposed to the high-temperature cavity, forming a 360-degree "suspended evaporation array" without dead angles, which causes the working fluid to vaporize explosively in a very short time, providing an extremely strong gas pressure support for the lifting action of the elastic diaphragm 7.

[0070] Finally, during the cooling and resetting phase, the flexible capillary wick 13 acts as a highly efficient liquid guiding channel. Utilizing surface tension and capillary backflow, it rapidly punctures and guides the liquid film condensed at the bottom of the elastic diaphragm 7 downwards and backflows. This eliminates the thermal resistance caused by the condensed liquid film and removes the interference of liquid adhesion on the quality of the elastic diaphragm 7, ensuring that the elastic diaphragm 7 quickly and accurately resets based on its own structural elasticity, thus preparing it for the next high-frequency pneumatic jet.

[0071] like Figure 4 As shown, to ensure that the elastic microcantilever 11 can accurately sense the temperature fluctuation of the underlying chip in the cold gas jet environment, the elastic microcantilever 11 is made of a two-way shape memory alloy material; and the fixed end of the elastic microcantilever 11 is directly anchored to the metal inner wall of the jet micro-hole 9 to form a thermal bridge; although cold gas is ejected from the jet micro-hole 9, the transient high heat energy conducted from the heat source by the limiting crossbar 5 through the support column 4 is preferentially conducted to the root of the elastic microcantilever 11 through the thermal bridge, so that it can overcome the influence of convection cooling and quickly reach the phase change trigger temperature to deflect;

[0072] Within the preset normal operating temperature range, the elastic microcantilever 11 remains straight, causing the turbulence block 12 to suspend at the center of the exhaust channel of the jet micro-hole 9, generating a symmetrically swept turbulent pulsating jet.

[0073] When the module load suddenly increases, causing the local temperature to exceed the preset high temperature threshold, the elastic microcantilever 11 undergoes adaptive bending deformation due to heat, causing the turbulence block 12 to shift towards the side closer to the bottom shell 101. This changes the fluid resistance distribution inside the exhaust channel, forcing the turbulent pulsating jet ejected from the jet micro-hole 9 to be targeted and deflected towards the root of the heat source where the core heat-generating component is located. Thus, during the adaptive deformation of the shape memory alloy due to heat, the exhaust flow direction is dynamically adjusted, achieving multi-angle wide-range sweeping of different areas of the heat dissipation fins 3, which further improves the overall heat dissipation effect.

[0074] like Figure 4 , Figure 5 As shown, a one-way air intake micro-valve 14 is installed on the top shell 102; the output end of the one-way air intake micro-valve 14 extends into the pneumatic compression chamber 602, and the one-way air intake micro-valve 14 only allows cold air from the external environment to flow into the pneumatic compression chamber 602 in one direction.

[0075] A one-way exhaust micro-valve 15 is fixedly embedded in the pneumatic extrusion chamber 602, and the output end of the one-way exhaust micro-valve 15 extends into the transverse guide cavity 8.

[0076] When the bistable snap elastic diaphragm 7 is cooled and reset and collapses downward, a negative pressure is generated in the pneumatic compression chamber 602, and the one-way air intake micro valve 14 is sucked open, guiding external cold air into the pneumatic compression chamber 602.

[0077] When the bistable jump elastic diaphragm 7 is heated and bulges upward, the air pressure in the pneumatic extrusion chamber 602 increases, the one-way air intake micro-valve 14 automatically closes, and the one-way exhaust micro-valve 15 opens, forcing the air in the pneumatic extrusion chamber 602 to be ejected at high speed only from the jet micro-hole 9.

[0078] By cooperating with the one-way intake micro-valve 14 and the one-way exhaust micro-valve 15, the system directly draws in fresh cold air from the outside during the "inhalation" phase when the diaphragm resets; during the "exhalation" phase when the diaphragm bulges, the valves close, ensuring that all the cold air is sprayed at high speed onto the heat dissipation fins 3, thereby improving the heat carrying capacity of a single injection and playing a role in improving the heat dissipation effect.

[0079] like Figure 5 As shown, a porous sintered metal layer 16 is laid on the inner bottom surface of the phase change expansion chamber 601. The porous sintered metal layer 16 is immersed in the low-boiling-point phase change working fluid at the bottom of the phase change expansion chamber 601. When the bistable snap elastic diaphragm 7 is in the reset state, the bottom end of the flexible capillary suction core 13 abuts against the upper surface of the porous sintered metal layer 16, forming a capillary reflux channel that relays the condensed phase change working fluid back to the bottom.

[0080] The bottom end of the flexible capillary liquid-absorbing core 13 extends and is directly attached to the upper surface of the porous sintered metal layer 16.

[0081] The porous sintered metal layer 16 has a large number of interconnected micropores inside, which are used to expand the heating area at the bottom of the phase change expansion chamber 601 and provide dense boiling vaporization nuclei for the low-boiling-point phase change working fluid, thereby accelerating the heating and vaporization of the phase change working fluid when the module load increases sharply.

[0082] By adding a porous sintered metal layer 16 to the bottom of the phase change expansion chamber 601, the surface area for heat transfer at the bottom of the phase change expansion chamber 601 is increased, thereby improving the heat conduction effect. Simultaneously, the porous sintered metal layer 16 promotes the immediate and uniform boiling of the low-boiling-point phase change working fluid as soon as the temperature reaches the threshold, achieving timely boiling. Furthermore, it is tightly bonded to the flexible capillary wick 13 above, and the microporous networks of both are physically integrated. The sintered layer itself possesses extremely strong capillary suction force, instantly "relaying" and absorbing the condensate drawn down from the wick like a dry sponge. This active forced reflux based on capillary force eliminates the lag in liquid dripping, allowing the fluorinated liquid in the flexible capillary wick 13 to quickly return to its original position, preparing for the next injection.

[0083] like Figure 5 As shown, a dustproof and breathable membrane 17 is installed at the air inlet of the one-way air inlet micro valve 14.

[0084] The dustproof and breathable membrane 17 is a polytetrafluoroethylene microporous filter membrane, which is used to block dust and impurities in the external environment from entering the pneumatic extrusion chamber 602 and the jet micropores 9 when the bistable snap elastic diaphragm 7 is cooled and reset and draws in external cold air.

[0085] The bottom outer surface of the bottom shell 101 is provided with several auxiliary heat dissipation horizontal lines to increase the heat exchange surface area at the bottom.

[0086] Usage: The frame-type limiting structure formed by the supporting column 4 and the limiting crossbar 5 locks the originally independent and extremely thin heat dissipation fins 3 into a high-strength integral array; it enhances the pressure resistance and shear resistance of the front end of the optical module, thereby preventing the fins from being damaged or deformed due to mechanical stress in the optical module during dense plugging and unplugging, transportation or high-intensity vibration environment, and plays a role in ensuring a long-term stable heat dissipation channel; when the module load suddenly increases and heat is transferred to the supporting column 4, the phase change working fluid is heated and vaporized and expands, and forces the elastic diaphragm 7 to bulge and deform upward, thereby compressing the air in the pneumatic compression chamber 602, forcing the air to be ejected at high speed through the transverse guide cavity 8 and the jet micro-hole 9, forming a disturbed micro-jet that directly hits the gap between adjacent heat dissipation fins 3.

[0087] By integrating a passive thermal pulsating micro-jet system inside the supporting column 4 and the limiting crossbar 5, the module temperature exhibits minute dynamic peaks and troughs during actual operation, accompanying transient changes in data throughput and dynamic adjustments to external cooling airflow. These temperature fluctuations alternately drive the boiling and condensation of the phase change working fluid, causing the elastic diaphragm 7 to undergo a "breathing" reciprocating deformation. This deformation continuously pumps high-speed airflow from the jet micro-holes 9, precisely penetrating the airflow stagnation zone and thermal boundary layer deep within the heat dissipation fins 3. This directly converts harmful heat loads into air kinetic energy that enhances convective heat transfer, thereby improving the heat dissipation response speed under transient thermal shock.

[0088] When the high-speed airflow discharged from the pneumatic compression chamber 602 impacts the turbulence block 12, the pneumatic pressure and the restoring force of the elastic microcantilever 11 are coupled together, forcing the turbulence block 12 to undergo high-frequency aerodynamic flutter.

[0089] This high-frequency vibration modulates the originally flat, narrow-coverage unidirectional microjet into a turbulent, pulsating jet that sweeps across a wide area at multiple angles. This powerful "dynamic sweeping" airflow forms an invisible aerodynamic brush, thereby expanding the effective contact area between the cooling airflow and the heat dissipation fins 3. Furthermore, it can cut and peel off the thermal boundary layer attached to the fin surface with turbulence, improving the convective heat transfer effect.

[0090] When the phase change working fluid in the phase change expansion chamber 601 is heated and vaporized, and the accumulated fluid pressure reaches the preset first pressure threshold, the bistable jump elastic diaphragm 7 instantly buckles and reverses to the trigger steady state, and rapidly compresses the air in the pneumatic compression chamber 602 in the form of pulses, forming a high-frequency transient microjet.

[0091] The bistable jump elastic diaphragm 7 is existing technology and will only be briefly described below without further elaboration: To ensure the high-frequency transient burst force of the above-mentioned microjet system at the microscale, the bistable jump elastic diaphragm 7 in this embodiment adopts a mechanical design based on the principle of nonlinear buckling instability. Its physical mechanism is similar to the mature thermosensitive jump structure (such as a metal dome or a temperature-controlled bimetallic strip) in the field of precision industrial control, but in this scheme, it is cross-boundary coupled with the fluid phase change system.

[0092] The specific working mechanism is as follows: In the initial energy storage stage of the phase change working fluid being heated and expanded, the bistable jump elastic diaphragm 7 relies on its own structural stiffness to maintain the initial steady state of being concave. At this time, the elastic diaphragm 7 is in the "elastic energy storage" state with high strain energy, which transforms the slow thermodynamic expansion process into the accumulation of mechanical potential energy.

[0093] When the fluid pressure inside the phase change expansion chamber 601 reaches the critical instability load of the elastic diaphragm 7 structure, the stress balance of the elastic diaphragm 7 is instantly broken, and a nonlinear buckling reversal occurs within an extremely short time (milliseconds), transitioning to an upward-convex triggered steady state. This nonlinear transformation from "slow thermal expansion" to "extremely rapid mechanical release" breaks through the physical bottleneck of low flow velocity and lack of explosive force in the traditional linear elastic diaphragm 7, providing a pulsed aerodynamic gas source with extremely high initial kinetic energy for the jet micro-orifice 9, thereby ensuring the reliable generation of high Reynolds number turbulent jets.

[0094] The above are merely preferred embodiments of the present invention; however, the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and its improved concept, should be covered within the scope of protection of the present invention.

Claims

1. A heat dissipation structure for an OSFP optical module, comprising a hollow housing (1) and a circuit board (2). Its features are: The housing (1) includes a bottom shell (101) and a top shell (102) covering the bottom shell (101). The top surface of the top shell (102) is provided with a plurality of parallel heat dissipation fins (3). A support assembly is provided on the outer top surface of the top shell (102); The support assembly includes a support column (4) that is vertically fixed to the upper surface of the top shell (102), and a limiting crossbar (5) that is horizontally fixed to the top of the side wall of the support column (4). The supporting column (4) is parallel to the heat dissipation fins (3); a horizontal positioning groove is provided on the vertical edge of the same side of all the heat dissipation fins (3), the limiting crossbar (5) is horizontally spanned and embedded in each horizontal positioning groove, and the limiting crossbar (5) is fixedly connected to each heat dissipation fin (3). The supporting column (4) is made of a high thermal conductivity material and has a vertically opened hot pneumatic cavity (6) inside. An elastic diaphragm (7) is installed in the hot pneumatic cavity (6) and is sealed in the horizontal direction. The elastic diaphragm (7) divides the cavity into a phase change expansion chamber (601) located below and a pneumatic extrusion chamber (602) located above. The phase change expansion chamber (601) is filled with a low boiling point phase change working fluid. The limiting crossbar (5) has a hollow interior forming a transverse flow guide cavity (8), which is in fluid communication with the top of the pneumatic extrusion chamber (602); the limiting crossbar (5) has multiple jet microholes (9) on the side facing the heat dissipation fins (3) that are in communication with the transverse flow guide cavity (8).

2. The heat dissipation structure of an OSFP optical module according to claim 1, characterized in that: The low-boiling-point phase change working fluid in the phase change expansion chamber (601) is an electronic-grade insulating fluorinated liquid.

3. The heat dissipation structure of an OSFP optical module according to claim 2, characterized in that: The inner bottom surface of the top shell (102) is provided with a downwardly protruding heat-conducting boss (10).

4. The heat dissipation structure of an OSFP optical module according to claim 3, characterized in that: The jet micro-orifice (9) is provided with a flow-induced vibration component; The flow-induced vibration assembly includes an elastic microcantilever (11) with one end fixed to the inner wall of the jet microhole (9), and a turbulence block (12) suspended at the free end of the elastic microcantilever (11); the turbulence block (12) is suspended at the center of the exhaust channel of the jet microhole (9).

5. The heat dissipation structure of an OSFP optical module according to claim 4, characterized in that: The elastic diaphragm (7) is a bistable snap-start elastic diaphragm (7), which has a downwardly concave initial steady-state structure and an upwardly convex trigger steady-state structure.

6. The heat dissipation structure of an OSFP optical module according to claim 5, characterized in that: The flexible capillary liquid-absorbing core (13) is suspended at the center of the lower surface of the elastic diaphragm (7); the bottom end of the flexible capillary liquid-absorbing core (13) hangs down naturally and is immersed in the phase change working medium at the bottom of the phase change expansion chamber (601).

7. The heat dissipation structure of an OSFP optical module according to claim 6, characterized in that: The elastic microcantilever (11) is made of two-way shape memory alloy.

8. The heat dissipation structure of an OSFP optical module according to claim 1, characterized in that: A one-way air intake micro-valve (14) is installed on the top shell (102); the output end of the one-way air intake micro-valve (14) extends into the pneumatic extrusion chamber (602); A one-way exhaust micro-valve (15) is fixedly embedded in the pneumatic extrusion chamber (602), and the output end of the one-way exhaust micro-valve (15) extends into the transverse guide cavity (8).

9. The heat dissipation structure of an OSFP optical module according to claim 6, characterized in that: The inner bottom surface of the phase change expansion chamber (601) is covered with a porous sintered metal layer (16), which is immersed in the low boiling point phase change working fluid at the bottom of the phase change expansion chamber (601). When the bistable snap elastic diaphragm (7) is in the reset state, the bottom end of the flexible capillary suction core (13) abuts against the upper surface of the porous sintered metal layer (16), forming a capillary reflux channel that relays the condensed phase change working fluid back to the bottom.

10. The heat dissipation structure of an OSFP optical module according to claim 8, characterized in that: The air inlet of the one-way air intake micro-valve (14) is equipped with a dustproof and breathable membrane (17); the bottom outer surface of the bottom shell (101) is provided with several auxiliary heat dissipation horizontal lines.

Images