BEARING HOUSING FOR TURBOCHARGERS

Abstract

A bearing housing for a turbocharger is disclosed. The bearing housing comprises a housing body and a flange positioned at an interface with an adjacent housing. Several interruption zones are formed on the flange, each zone defining a gap or recess to interrupt heat conduction paths. The interruption zones are configured to direct heat flow away from the housing body, thereby reducing thermal stress and improving the durability and thermal management of the bearing housing under high-temperature operating conditions.

Description

Technical field The present disclosure relates generally to turbocharger components for internal combustion engines and in particular to bearing housings used in turbochargers. background Turbochargers are widely used in internal combustion engines to improve power and efficiency by compressing the intake air and enabling a higher power density. These devices help engines produce more power without significantly increasing their size, making them an integral part of modern vehicle design. However, turbocharger systems, especially those with variable turbine geometry (VTG), present significant thermal challenges. The bearing housing that connects the turbine housing and the compressor housing is subjected to a high heat flow during operation. This heat transfer from the turbine housing to the bearing housing can cause the bearing housing flange temperatures to exceed 450 °C, resulting in considerable thermal stress. Effective cooling of the bearing housing is crucial to maintaining its structural integrity. Despite the integration of water cooling systems, it is often difficult to provide sufficient cooling for critical areas, particularly at the outer radial points or near the bearing housing-turbine housing flange. These areas are especially susceptible to overheating due to inadequate heat dissipation. Over time, exposure to high temperatures can degrade the material properties of the bearing housing, leading to cracks and structural failure of the flange. Such failure impairs the performance and durability of the turbocharger and necessitates costly repairs and replacements. It is therefore evident that a bearing housing design is needed that effectively manages heat transfer from the turbine housing to the bearing housing and ensures adequate cooling even in areas of high heat flow. Such a design would reduce thermal stress, prevent material degradation, and eliminate cracking problems at the bearing housing-turbine housing flange, thereby improving the durability and service life of turbocharger systems. Brief description According to one aspect of the disclosure, a bearing housing for a turbocharger is provided. The bearing housing comprises a bearing housing body and a flange positioned at an interface with an adjacent housing. The flange includes at least one interruption zone, the interruption zone defining a gap or recess for interrupting heat conduction paths. The interruption zone is configured to direct heat flow away from the bearing housing body, thereby reducing thermal stress and improving the operational reliability of the bearing housing. This configuration improves the thermal management of the turbocharger under high-temperature operating conditions. According to another aspect of the disclosure, a turbocharger system is provided. The turbocharger system comprises a turbine housing configured to receive exhaust gases from an internal combustion engine, a compressor housing configured to receive compressed air from a rotor shaft, and a bearing housing connecting the turbine housing and the compressor housing. The bearing housing comprises a bearing housing body and a flange positioned at an interface with an adjacent housing. The flange includes at least one interruption zone, the interruption zone defining a gap or recess for interrupting heat conduction paths. The interruption zone is configured to direct heat flow away from the bearing housing body, thereby reducing thermal stress and improving the durability and thermal efficiency of the turbocharger system. According to yet another aspect of the disclosure, a method for reducing thermal stress in a turbocharger bearing housing is provided. The method comprises forming a bearing housing body with a flange along its circumference for coupling to an adjacent housing component. The method further includes machining multiple interrupted zones in the flange, each interrupted zone defining a gap or recess to interrupt a heat conduction path between the bearing housing and the adjacent housing component. This method improves thermal management by diverting heat flow away from the bearing housing, reducing thermal stress, and enhancing the durability and operational efficiency of the turbocharger. These and other aspects and features of the present revelation will become more understandable upon reading the following detailed description in conjunction with the accompanying drawings. Brief description of the drawings Fig. 1 is a cross-sectional view of a turbocharger assembly, showing the turbine housing, the bearing housing, and the compressor housing according to one embodiment of the present disclosure. Fig. 2 is a perspective side view of the bearing housing according to one embodiment of the present disclosure. Fig. 3 is a schematic top view of the bearing housing, showing the arrangement of heat-dissipation zones according to one embodiment of the present disclosure. Fig. 4 is a perspective top view of the bearing housing, showing the configuration of heat-dissipation zones according to one embodiment of the present disclosure. Fig. 5 is a close-up view of the BH-TH housing interface between the bearing housing (BH) and the turbine housing (TH), showing the flange of the bearing housing coupled to the turbine housing according to one embodiment of the present disclosure.Figure 6 is a side close-up view of the BH-TH housing interface, showing the interruption zones as gaps for redirecting heat flow according to one embodiment of the present disclosure. Figure 7 is a perspective close-up view of the BH-TH housing interface, showing the gap created by the interruption zones for improved thermal management according to another embodiment of the present disclosure. Figure 8 is a flowchart of a method for reducing thermal stress in a turbocharger bearing housing according to one embodiment of the present disclosure. The figures represent one embodiment of the present invention for illustrative purposes only. A person skilled in the art will readily recognize from the following discussion that alternative embodiments of the structures and methods shown here can be used without deviating from the principles described herein. Detailed description With reference to the drawings and specifically to the example shown in Fig. 1, a turbocharger 100 is shown in cross-sectional view. Although the following detailed description describes an exemplary embodiment in connection with a turbocharger 100 for internal combustion engines, it is understood that the description applies equally to other applications, including, but not limited to, gasoline or diesel engines in passenger cars, trucks, industrial machinery, and marine engines, as well as other high-performance drive systems requiring advanced thermal management and durability. With reference to Fig. 1, a cross-sectional view of a turbocharger 100 according to an embodiment of the disclosure is shown. The turbocharger 100 comprises a turbine housing 102, a compressor housing 104, and a bearing housing 106, which connects the turbine housing 102 and the compressor housing 104. A turbine wheel 108 is positioned in the turbine housing 102 and is coupled to a compressor wheel 110 in the compressor housing 104 via a rotor shaft 112. The rotor shaft 112 extends through the bearing housing 106, which provides structural support and in which bearings for a rotary motion of the rotor shaft 112 are housed. The bearing housing 106 comprises a bearing housing body 114, which defines a shaft bore for receiving the rotor shaft 112. The bearing housing 106 may further include one or more cooling cores 118 configured to provide improved thermal management. The cooling cores 118 are positioned within or adjacent to the bearing housing body 114 and are configured to circulate a cooling medium, such as water or oil, to effectively reduce local thermal stress. By integrating cooling cores 118, heat generated at the BH-TH interface 116 and other critical areas of the bearing housing 106 can be dissipated more efficiently, thereby ensuring the operational reliability of the turbocharger 100 under high-temperature conditions. The geometry of the cooling cores 118 can vary depending on the application and thermal load.For example, the cooling cores 118 can be configured as spirally shaped channels surrounding the rotor shaft 112 to maximize heat transfer efficiency, or as linear passages extending radially along the bearing housing body 114 to target specific areas of thermal stress. In some embodiments, the cooling cores 118 can also include fins or turbulators to promote turbulent flow, thereby increasing the heat transfer efficiency between the coolant medium and the inner surfaces of the cooling cores 118. The turbine housing 102 draws in exhaust gases from an internal combustion engine through an inlet channel. The exhaust gases drive the turbine wheel 108, causing it to rotate. This rotational energy is transferred via the rotor shaft 112 to the compressor wheel 110, which compresses the inlet air. Compressed air exits the compressor housing 104 through an outlet channel and is directed to the engine for combustion. The bearing housing 106 is configured for coupling to the turbine housing 102 via a bearing housing-turbine housing interface 116 (“BH-TH interface 116”). The bearing housing 106 can be bolted to and / or integrated with the turbine housing 102 in the turbocharger 100. With reference to Fig. 2, a perspective side view of the bearing housing 106 according to an embodiment of the present disclosure is shown. The bearing housing body 120 comprises a flange 200 configured for coupling to the turbine housing 102. The flange 200 extends radially from the bearing housing body 120. The flange 200 incorporates several interruption zones 202 strategically distributed along its surface. These interruption zones 202 are designed as depressions or crevices that alter the heat conduction path, thereby improving thermal management. By redirecting the heat flow, the interruption zones 202 help maintain lower temperatures in critical areas of the bearing housing 106. In some embodiments, the bearing housing 106 can include a single interruption zone 202 positioned on the flange 200. This single interruption zone 202 can extend radially over a limited section of the circumference of the flange 200, thereby interrupting heat conduction in a localized area or “overheated spot.” Such a configuration can be advantageous for applications requiring targeted thermal management in areas of high heat flow while maintaining the structural strength of the remaining areas of the flange 200. In one embodiment, the cooling cores 118 can comprise channels, passages, or cavities formed in the bearing housing body 114. These channels are connected to an external cooling system that supplies a coolant medium, such as engine coolant or a dedicated cooling fluid. The coolant flow through the cooling cores 118 is configured to dissipate heat from high-flow areas of the bearing housing 106, particularly near the flange 200 and the shaft bore of the rotor shaft 112. The cooling cores 118 can be strategically positioned to address specific thermal challenges, such as overheated areas near the bearing housing-turbine housing interface 116. In some embodiments, the interruption zones 202 are positioned symmetrically around the circumference of the flange 200. As shown in Fig. 2, each interruption zone 202 is recessed into the flange 200 and extends radially to optimize heat dissipation. This arrangement contributes to the overall thermal performance of the bearing housing 106 without compromising its structural integrity. The interruption zones 202 are dimensioned to ensure a balance between heat dissipation and structural strength. For example, the width of each interruption zone 202 can range from approximately 1 mm to 100 mm. The design ensures that the interruption zones 202 effectively reduce heat transfer while maintaining the flange 200's ability to securely connect the turbine casing 102 and the bearing housing 106. With reference to Fig. 3, a schematic top view of the bearing housing 106 is shown, illustrating the spatial arrangement of the interruption zones 202 around the flange 200. In this embodiment, three interruption zones 202 are equidistantly spaced at intervals of approximately 120 degrees. Open areas 204 between adjacent interruption zones 202 provide additional heat dissipation by promoting convection of the heat to be dissipated. The connecting surfaces 206 on the radial edges of the flange 200 are configured for secure coupling to the turbine housing 102. These surfaces are positioned to complement the interruption zones 202, thus ensuring effective thermal management without compromising the mechanical connection between the components. With reference to Fig. 4, a perspective top view of the bearing housing 106 is shown, highlighting the relationship between the interrupted zones 202 and the open areas 204. The recessed design of the interrupted zones 202 creates offsets that improve the thermal management properties of the flange 200 and direct heat flow away from the bearing housing body 12. The open areas 204, formed between the interruption zones 202, contribute to heat dissipation through convection and conduction, thereby reducing heat buildup in the flange 200. This design ensures that the flange 200 can withstand high-temperature operating conditions while maintaining structural reliability. The cooling cores 118 complement the thermal interruption zones 202 and open areas 204 described here, providing a versatile approach to thermal management in the bearing housing 106. While the interruption zones 202 disrupt heat pathways and promote natural convection, the cooling cores 118 actively dissipate heat through forced convection by circulating a coolant medium. The bearing housing 106, comprising the bearing housing body 120 and the flange 200, is constructed of materials capable of withstanding significant thermal and mechanical stresses. For example, an aluminum alloy can be used to improve thermal conductivity and durability. This choice of material, in conjunction with the arrangement of discontinuity zones 202 and open areas 204, ensures that the bearing housing 106 remains effective and durable under high heat flow conditions. Furthermore, the bearing housing 106 can be made of cast iron or similar cast materials. The bearing housing body 120 and the flange 200 are constructed from thermally conductive and durable materials capable of withstanding high thermal stresses. In certain embodiments, an aluminum alloy with a thermal conductivity exceeding 150 W / m·K can be used. This material ensures efficient heat dissipation from the bearing housing body 120 while maintaining mechanical strength to resist deformation under thermal and mechanical stresses. Alternatively, other materials, such as high-temperature alloys or composites, can be used depending on the specific operating conditions. The integrated design of the bearing housing 106, comprising the flange 200, the interrupted zones 202, and the open areas 204, provides a robust solution for managing thermal loads in the turbocharger 100. This supports reliable performance and an extended service life of the turbocharger 100 while ensuring optimal thermal efficiency. In some embodiments, a thermal barrier layer can be applied to the flange 200 to further improve heat dissipation and reduce heat absorption into the bearing housing 106. The thermal barrier layer can be composed of a ceramic-based material or other insulating compounds known for their ability to withstand high temperatures and prevent heat conduction. This additional protective layer increases the operational reliability of the bearing housing 106 in environments with extreme heat flow. With reference to Fig. 5, a close-up view of the interface between the bearing housing 106 and the turbine housing 102 is shown according to an embodiment of the present disclosure. The flange 200 of the bearing housing 106 is aligned with a mating surface on the turbine housing 102, thereby ensuring a precise coupling. The interrupted zones 202 on the flange 200 are positioned to manage the heat conduction path at this interface, thereby reducing the heat transferred from the turbine housing 102 to the bearing housing 106. These features maintain thermal stability in high-temperature areas near the turbine housing 102. The interruption zones 202 are configured to limit direct contact between the flange 200 and the turbine casing 102. This design minimizes heat transfer while maintaining structural integrity to ensure proper alignment and operational reliability. The open areas 204 formed between the interruption zones 202 provide additional paths for convection cooling, further enhancing the thermal management capabilities of the bearing housing 106. With reference to Fig. 6, a side view of the interface between the bearing housing 106 and the turbine housing 102 is shown, revealing the interruption zones 202 as gaps positioned along the flange 200. This side view illustrates the depth and spacing of the interruption zones 202, which create thermal offsets along the flange 200. These gaps ensure that heat flow from the turbine housing 102 is directed away from critical areas of the bearing housing 106. This configuration promotes improved heat dissipation and prevents localized overheating that could impair material properties or cause structural failure. With reference to Fig. 7, a perspective close-up view of the interface between the bearing housing 106 and the turbine housing 102 according to an embodiment of the present disclosure is shown. This view illustrates additional details of the interruption zones 202 and the gaps they create along the flange 200. The perspective view shows how the gaps form discrete areas of thermal insulation, thereby reducing direct heat transfer between the turbine housing 102 and the bearing housing 106. The arrangement of the gaps further facilitates natural convection, allowing air to circulate efficiently and dissipate heat from the flange 200. The machining process for forming the discontinuity zones 202 can include precision techniques such as CNC milling, laser cutting, or electrical discharge machining (EDM). Alternatively, the discontinuity zones 202 can be formed by casting, die casting, or another casting process, as is generally known in engineering. These processes allow for the formation of highly precise and consistent discontinuity zones 202 with controlled dimensions. For example, the width and depth of the gaps or recesses can be adjusted during machining to optimize heat dissipation while maintaining the structural integrity of the flange 200.The process may also include finishing treatments to ensure smooth surfaces within the discontinuity zones 202, thereby reducing potential stress concentrations that could otherwise lead to material fatigue or cracking. Together, the configurations shown in Fig. 5, Fig. 6 and Fig. 7 represent the strategic use of interruption zones 202 and columns for managing thermal loads at the BH-TH interface 116. These features improve the overall thermal performance of the turbocharger 100 and enhance reliability and service life under high-temperature conditions. Industrial applicability In practice, this disclosure can be applied in numerous industries, including, but not limited to, the automotive industry, construction, energy production, agriculture, and heavy machinery manufacturing. Specifically, the systems, components, and methods described herein can be used in turbocharged engines for passenger cars, trucks, industrial machinery, and marine engines. These teachings are particularly advantageous in environments requiring advanced thermal management for components in turbochargers exposed to high temperatures, such as the bearing housing 106. With reference to Fig. 8, a method 500 for reducing the thermal stress in a bearing housing 106 of a turbocharger 100 is presented. This method 500 comprises forming, machining, and strategically positioning features in the bearing housing 106 to manage heat transfer and extend the service life of the turbocharger 100. In step 504, the procedure 500 comprises the machining of one or more interruption zones 202 in the flange 200. Each interruption zone 202 defines a gap or recess that interrupts the heat conduction path between the bearing housing 106 and the turbine housing 102. These interruption zones 202 are spaced symmetrically around the flange 200 to ensure uniform heat management across the interface. The machining process may include precision techniques in forming the interruption zone 202 to achieve optimized dimensions for heat dissipation. In step 506, the procedure 500 involves positioning the interrupted zones 202 to direct heat flow away from the bearing housing 106 to areas capable of dissipating heat more efficiently. The interrupted zones 202 and the open areas 204 between them allow natural convection and conduction to dissipate accumulated heat. This configuration prevents overheating in the flange 200 and maintains the structural integrity of the bearing housing 106 even under prolonged exposure to high-temperature operating conditions. The method 500 described here addresses the challenges of thermal management in the turbocharger 100, particularly in areas where a high heat flow is transferred from the turbine housing 102 to the bearing housing 106. By implementing these steps, method 500 ensures improved thermal stability, a reduced risk of material degradation, and increased reliability of the turbocharger 100 in demanding operating environments. The principles described here also apply to turbocharged engines in hybrid powertrains, where thermal management remains critical for achieving optimal performance. By integrating the described bearing housing designs, such systems can better accommodate fluctuating temperature loads caused by dynamic engine operation.Furthermore, the interruption zones 202 described here can be adapted for use in other thermal management systems, such as those in gas turbines or heat exchangers, to improve durability and efficiency across a wide range of industrial applications. It is evident from the foregoing that the technology disclosed herein has industrial applicability in a wide range of industries, including, but not limited to, the automotive, construction, mining, and agricultural sectors. This technology is particularly useful for internal combustion engines equipped with turbochargers, where advanced thermal management is required to improve durability, efficiency, and performance. The described systems, components, and methods can be applied to turbocharged engines for passenger cars, trucks, industrial machinery, and other high-performance systems that require efficient thermal load distribution.

Claims

Bearing housing for a turbocharger, comprising: a bearing housing body; a flange on the bearing housing body at an interface with an adjacent housing; a break zone formed in the flange, wherein the break zone defines a gap or recess for interrupting heat conduction paths; and wherein the break zone is configured to direct heat flow away from the bearing housing body for the purpose of reducing thermal stress on the bearing housing. Bearing housing according to claim 1, wherein several interruption zones are provided on the flange. Bearing housing according to claim 2, wherein the multiple interruption zones are evenly spaced around the flange. Bearing housing according to claim 2 or claim 3, wherein each of the multiple interruption zones are elongated gaps. Bearing housing according to one of the preceding claims, further comprising at least one cooling core positioned in the bearing housing body for circulating a cooling medium. Bearing housing according to one of the preceding claims, further comprising a thermal coating applied to the flange to improve heat dissipation. Bearing housing according to one of the preceding claims, wherein the flange is cast or machined to form the gap or gaps or recess(s) that is / are formed on the bearing housing body. Bearing housing according to one of the preceding claims, wherein the bearing housing body is made of an aluminum alloy with a thermal conductivity of more than 150 W / m·K. A turbocharger comprising: a turbine housing configured to receive exhaust gases from an internal combustion engine; a compressor housing configured to receive compressed air from a rotor shaft; a bearing housing connecting the turbine housing and the compressor housing, the bearing housing comprising: a bearing housing body; a flange on the bearing housing body at an interface with an adjacent housing; a break zone formed in the flange, the break zone defining a gap or recess for interrupting heat conduction paths; and the break zone being configured to direct heat flow away from the bearing housing body to reduce thermal stress on the bearing housing. Turbocharger according to claim 9, wherein several interruption zones are provided on the flange. Turbocharger according to claim 10, wherein the multiple interruption zones form an air gap in a bearing housing-turbine housing interface configured to allow convection cooling. Turbocharger according to claim 10 or claim 11, wherein the multiple interruption zones are evenly spaced around the flange. Turbocharger according to one of claims 10 to 12, wherein the multiple interruption zones are elongated gaps. Turbocharger according to one of claims 10 to 13, wherein the flange is cast or machined to form the multiple interruption zones. Turbocharger according to one of claims 9 to 14, further comprising a thermal insulation layer positioned between the bearing housing and the compressor housing. Turbocharger according to one of claims 9 to 15, further comprising at least one cooling core positioned in the bearing housing body for circulating a cooling medium. Method for reducing thermal stress in a bearing housing of a turbocharger, the method comprising: forming a bearing housing body with a flange along a circumference on the bearing housing body for coupling to an adjacent housing component; and casting or machining multiple interruption zones in the flange, each interruption zone defining a gap or recess for interrupting a heat conduction path between the bearing housing and the adjacent housing component. Method according to claim 17, positioning the multiple interruption zones to direct a heat flow away from the bearing housing to areas that are able to dissipate heat more efficiently. The method according to claim 17 or claim 18, further comprising the application of a thermal insulation layer to the flange to reduce heat absorption. Method according to one of claims 17 to 19, further comprising casting or machining the multiple interruption zones to form elongated gaps.

Images