CN117940653A - Oil-cooled exhaust gas turbine equipment - Google Patents

Abstract

According to embodiments described herein, an oil cooled exhaust gas turbine apparatus (100) is provided. An exhaust gas turbine device comprises a rotatable shaft (105) with a turbine wheel (106), a support member (110) comprising a support (112), a support housing (120) comprising a sealing bushing portion (130) for providing first sealing means (132) axially between the turbine wheel and the support member, an oil cooling chamber (140) for cooling an inner surface (122) of the support housing, an oil passage (114) for providing oil into the oil cooling chamber (140), an oil discharge chamber (150) axially arranged between the support member (110) and the sealing bushing portion (130), and an oil retaining wall (160) surrounding a radial outside of the oil discharge chamber in at least a vertical top circumferential section for covering the oil discharge chamber from the oil cooling chamber.

Description

Oil-cooled exhaust gas turbine equipment

Technical Field

Embodiments of the present disclosure relate to exhaust gas turbine devices such as turbochargers, and more particularly to oil-cooled exhaust gas turbine devices. In more detail, embodiments of the present disclosure relate to oil-cooled exhaust gas turbine devices having radial bearings and sealing arrangements.

Background technique

Exhaust gas turbine devices such as exhaust gas turbochargers are known to be used to increase the power of internal combustion engines. In such an exhaust gas turbocharger, the turbine is arranged in the exhaust gas path of the internal combustion engine, and the compressor is arranged upstream of the internal combustion engine, and the compressor is connected to the turbine via a common shaft. The shaft is usually supported by a shaft support supported in a support housing. Therefore, the exhaust gas turbocharger is usually composed of a rotor, a support assembly for the shaft, a guide housing part (compressor housing and turbine housing) and a support housing. The rotor includes a shaft, an impeller and a turbine impeller.

An exhaust gas turbine device allows the energy stored in the exhaust gases of an internal combustion engine to be converted into rotational energy. In the case of a turbocharger, this rotational energy is used to charge the internal combustion engine, the capacity and the fuel mixture in the cylinder are increased, and a significant power increase of the engine is obtained as a result. In the case of a power turbine, the rotational energy can be converted into electrical or mechanical energy. In this case, instead of a compressor, as in the case of an exhaust gas turbocharger, for example a generator or a mechanical consumer is connected to the turbine shaft.

The bearings of exhaust gas turbine systems are usually lubricated with lubricating oil.

Due to the high process pressures in the flow area on the turbine side and compressor side, the shaft of the exhaust gas turbocharger is sealed with a suitable sealing concept in connection with the bearing housing. The internal pressure in the bearing housing usually corresponds to atmospheric pressure. However, the gas pressure in the flow channels on the compressor side and turbine side depends on the current operating point of the exhaust gas turbocharger and lies above the pressure in the cavity of the bearing housing at most operating points. However, in certain cases, negative pressures are also to be taken into account (e.g. in partial load operation or at standstill).

The lubricating oil supplied to the bearings of the filling system usually needs to be sealed by means of a shaft seal to avoid oil leakage into the gas path of the component. However, in oil-cooled filling systems, the oil load within the filling system can increase excessively due to the different pressure conditions, making it more susceptible to oil leakage, for example at the shaft seal. Especially in oil-cooled systems, where the lubricating oil can also be used to cool the bearing housing, high oil loads can lead to increased oil leakage.

Therefore, there is a need for an oil-filled system with improved sealing performance to prevent oil leakage.

Summary of the invention

In view of the above, an oil-cooled exhaust gas turbine device is provided. The exhaust gas turbine device includes a rotatable shaft having a turbine impeller; a support member including a support for rotatably supporting the shaft; a support housing that accommodates the support member therein and includes a sealing bushing portion that extends radially inward toward the shaft at an axial position between the turbine impeller and the support member; a first sealing device for axially providing a first sealing device between the turbine impeller and the support member; and an oil cooling chamber for cooling the inner surface of the support housing. The exhaust gas turbine device also includes an oil channel for providing oil to the oil cooling chamber, for cooling the inner wall of the support housing using oil as a cooling medium; and an oil drain chamber, which is axially arranged between the support member and the sealing bushing portion. The exhaust gas turbine device also includes an oil retaining wall that surrounds the radial outer side of the oil drain chamber in at least the vertical top circumferential section, for covering the oil drain chamber from the oil cooling chamber.

The embodiments are also directed to a method for operating the device, which includes method aspects for implementing each function of the device.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to be able to understand the above features of the present disclosure in detail, the present disclosure may be described in more detail with reference to the embodiments, as briefly summarized above. The accompanying drawings relate to the embodiments of the present disclosure and are described as follows:

FIG1 shows a cross-sectional front view of an exhaust gas turbine arrangement according to an embodiment described herein;

FIG. 2 shows a cross-sectional side view of an exhaust gas turbine arrangement according to an embodiment described herein;

FIG3 shows a cross-sectional side view of an exhaust gas turbine arrangement according to an embodiment described herein;

FIG. 4 shows a cross-sectional side view of an exhaust gas turbine arrangement according to an embodiment described herein; and

5A and 5B show a cross-sectional side view and an enlarged view of an exhaust gas turbine arrangement according to embodiments described herein.

Detailed ways

Reference will now be made in detail to various embodiments of the present disclosure, one or more examples of which are shown in the accompanying drawings. In the following description of the drawings, the same reference numerals refer to the same parts. In general, only the differences with respect to the various embodiments are described. Each example is provided by way of explanation of the present disclosure and is not meant to be a limitation of the present disclosure. In addition, features shown or described as part of one embodiment may be used on other embodiments or used in combination with other embodiments to produce yet another embodiment. This specification is intended to include such modifications and variations.

In the following description of the drawings, the same reference numerals refer to the same or similar components. Generally speaking, only the differences with respect to the various embodiments are described. Unless otherwise specified, the description of a part or aspect in one embodiment also applies to the corresponding part or aspect in another embodiment.

According to an embodiment that can be combined with any other embodiment described herein, an oil-cooled exhaust gas turbine device is provided. The exhaust gas turbine device can be a turbocharger or a power turbine. The exhaust gas turbine device includes a rotatable shaft with a turbine impeller. The turbine can be a radial turbine (having a substantially radial flow component on the upstream side of the turbine impeller, which also includes mixed flow or diagonal turbines). The shaft can rotate around an axis of rotation, in particular a horizontal axis of rotation. The shaft can connect the turbine impeller and the compressor impeller (or another load such as a generator) on axially opposite sides of the shaft.

According to an embodiment, a turbine device comprises a support member, which includes a support for rotatably supporting a shaft. The shaft can rotate in the support member. The support member can be a sliding bearing or a rolling bearing. The support member can be (including) a radial bearing and/or an axial bearing. The support member can include a support bushing to allow the shaft to rotate in the support member. The support member can include a support flange for mounting the support member in a support housing.

According to an embodiment that can be combined with any other embodiment described herein, a turbine device may include a support housing. The support housing may be configured to house or accommodate a support member. The support member may be separate from the support housing and removably insertable into a central cavity of the support housing. The support member may be mounted to the support housing via a support flange. The support housing may at least partially radially surround the support member including the support.

According to an embodiment, the bearing housing may extend axially towards the turbine wheel. The bearing housing may provide a barrier between the bearing member and the turbine wheel, ie the bearing housing may delimit the bearing member towards the turbine wheel. In particular, the bearing housing may delimit the bearing member axially.

According to an embodiment, the support housing includes a sealing bushing portion that extends radially inward toward the shaft at an axial position between the turbine impeller and the support member. The sealing bushing portion may be a wall of the support housing that faces the turbine. For example, the sealing bushing portion may be formed integrally with the support housing. Alternatively, the sealing bushing portion may be an independent component relative to the support housing. Additionally or alternatively, the sealing bushing portion and the support member may be independent components relative to each other, i.e., the sealing bushing portion and the support member may be non-integrally formed relative to each other. In addition, the support member may be an independent component relative to the support housing. Therefore, both the sealing bushing portion and the support member may be components separated from the support housing, i.e., both the sealing bushing portion and the support member may be non-integrally formed with the support housing. Additionally or alternatively, the sealing bushing portion may be separated from the support housing (non-integrally), while the support member may be formed integrally with the support housing. Alternatively, the sealing bushing portion may be formed integrally with the support housing, and the support member may be separated from the support housing (non-integrally).

According to an embodiment, which can be combined with any other embodiment described herein, the exhaust gas turbine device can include an oil supply system. The oil supply system can supply oil, in particular lubricating oil, to the support member, in particular to the support, for lubricating the support. The oil supply system can be configured to supply oil, in particular cooling oil, to the oil channel and through the oil channel to the oil cooling chamber. Thus, the oil supply system can be configured to supply oil to the support member and the oil cooling chamber for cooling the support housing, in particular for cooling a wall of the support housing facing the turbine.

According to an embodiment that can be combined with any other embodiment described herein, the turbine device, in particular the support housing, may include an oil cooling chamber for cooling the inner surface of the support housing. The inner surface of the support housing may include the inner side of the sealing bushing portion, i.e. the side of the sealing bushing portion facing the support member. Additionally or alternatively, the inner surface of the support housing may be the inner side of the support housing facing the turbine wall. The oil cooling chamber may be a space between the support member and the support housing and/or the sealing bushing portion. In other words, the oil cooling chamber may be provided by the support housing and the support member. In addition, the oil cooling chamber may be at least partially defined by the shaft and/or the support.

According to an embodiment, the oil cooling chamber may at least partially surround the shaft. The oil cooling chamber may (at least partially) surround the shaft, in particular the oil cooling chamber may be arranged in a vertical top region of the shaft. The oil cooling chamber may be axially delimited by the bearing housing and the bearing member. Furthermore, the sealing bushing portion may at least partially delimit the oil cooling chamber radially from the inside and axially from the turbine wheel.

According to an embodiment, the oil cooling chamber may be provided with oil for cooling the inner surface of the oil cooling chamber. The oil cooling chamber may receive oil from an oil channel, in particular lubricating oil. The oil channel may be arranged in the turbine device. In other words, the exhaust gas turbine device may include an oil channel. In particular, a support member, such as a support flange, may include an oil channel. The oil channel may be a hole in the wall of the turbine device. The oil channel may be directed toward the inner surface of the support housing and/or the oil cooling chamber to spray oil toward the inner surface of the support housing and/or the oil cooling chamber. The oil channel may be a hole and/or a nozzle for spraying oil toward the inner surface of the oil cooling chamber for cooling the inner surface and thereby for cooling the support housing. Cooling may be performed by the cooling oil flowing down the inner surface of the support housing.

According to an embodiment, the oil cooling chamber may include an oil recess for receiving oil from the oil cooling chamber. The oil recess may be arranged at the support member and/or the sealing bushing portion. For example, the oil recess may be formed integrally with one of the support member and/or the sealing bushing portion. The inner surface of the oil cooling chamber may extend radially inward to the oil recess for guiding oil from the inner surface to the oil recess. The oil recess may form a discharge passage. The discharge passage may extend at least partially circumferentially for guiding cooling oil downward along the discharge passage around the rotatable shaft. The discharge passage may be configured to guide cooling oil to an oil drain port. The oil recess and/or the discharge passage may be arranged at a radially inward position compared to the position of the oil passage.

According to an embodiment, the exhaust gas turbine device may include an oil drain. The oil drain may be arranged vertically below the shaft. The oil drain may be configured to receive oil from the oil cooling chamber. The oil drain may further be configured to provide the received oil back to the oil supply system. Thus, the oil may be reused for lubrication and/or cooling.

According to an embodiment that can be combined with any other embodiment described herein, the sealing bushing portion is configured to provide a first sealing device axially between the turbine impeller and the support member. The sealing device can be radially arranged between the sealing bushing portion and the shaft. In particular, the shaft can rotate and the sealing device can be arranged to be fixed relative to the sealing bushing portion. The first sealing device can prevent (lubricating or cooling) oil from the support side (for example, from the support and/or from the discharge chamber) from entering toward the turbine impeller, that is, toward the gas channel of the exhaust gas turbine device. In addition, the first sealing device can prevent hot gas from entering from the turbine impeller toward the support side. Here, the term "prevent" means that the first sealing device has a significant sealing effect on oil and/or hot gas, so that, for example, the pressure drop is significantly maintained by the sealing device (so that even under overpressure on the turbine side, the support side can be basically kept at atmospheric pressure). On the other hand, the term "prevent" does not exclude, for example, a small amount of residual oil and/or hot gas ("blow-by") through the first sealing device.

According to an embodiment, the first sealing device may include a plurality of sealing elements to prevent oil from reaching the turbine wheel. The sealing element may include one or more oil catch chambers, piston rings, sealing rings, sealing gaps, labyrinth seals, sealing air and/or combinations thereof. Advantageously, the plurality of sealing elements within the first sealing device results in a reduced oil load that can reach the turbine wheel.

According to an embodiment that can be combined with any other embodiment described herein, the first sealing device can be or include a sealing element, such as a piston ring. Additionally or alternatively, the first sealing device can be or include two (or more) sealing elements. In particular, the two sealing elements can be an oil catch chamber and a piston ring. Axially in the direction toward the turbine, the oil catch chamber and the piston ring can be arranged in a row, that is, the piston ring can be arranged to be axially closer on the turbine side compared to the oil catch chamber. In addition, the first sealing device can include additional piston rings, for example by having two piston rings adjacent to each other. Therefore, the sealing device can have a total of two sealing elements (e.g., one piston ring and one oil catch chamber) or three sealing elements, for example, two piston rings, one oil catch chamber). By selecting a total of two or three sealing elements for the sealing device in this way, the first sealing device can be appropriately sized to provide a good balance between (axial) space requirements and sealing function.

According to an embodiment that can be combined with any other embodiment described herein, the shaft can provide a cavity for supporting the piston ring, for example, for clamping the piston ring between the shaft and the (fixed) sealing bushing part. In addition, when the oil-cooled exhaust gas turbine device is in operation, the piston ring can be axially pressed against the cavity of the shaft. The cavity can have a first wall and a second wall on axially opposite sides. The first wall can be arranged on the supporting side of the cavity, and the second wall can be arranged on the turbine side of the cavity. Therefore, the piston ring can be axially pressed against the first wall of the cavity. The first wall can also include a supporting side recess. On the radial outside of the recess, the sealing bushing part may include a radial recess adjacent to the piston ring, i.e., a recess relative to the supporting side of the piston ring. Additionally or alternatively, the piston ring may be arranged at the recess, i.e., the recess may extend in the axial direction to provide the piston ring at the shaft, in particular to support the piston ring so that it can be pressed against the shaft during operation.

According to an embodiment, the cavity may provide space on the side of the piston ring facing the turbine to allow the piston ring to be pressed axially against the first wall of the cavity. The space may be provided between the second wall of the cavity and the piston ring. The second wall may be tapered. As a result, less exhaust gas, so-called "blow-by", can pass through the first sealing device, i.e. the sealing element.

According to an embodiment, the sealing bushing portion may include a notch. The notch may extend towards the turbine side of the sealing bushing portion. Thus, a higher pressure may act on the piston ring, thereby improving the squeezing of the piston ring against the first wall of the cavity. Thus, the airtightness of the first sealing device can be improved and enhanced. The notch may further reduce blowby through the first sealing device or the sealing element of the first sealing device.

According to an embodiment, which can be combined with any other embodiment described herein, the exhaust gas turbine device comprises an oil drain chamber arranged axially between the support member and the sealing bushing portion. The oil drain chamber can be a space formed axially between the support member and the sealing bushing portion. Therefore, the axial extension of the oil drain chamber can depend on the distance between the support member and the sealing bushing portion.

According to an embodiment, the oil drain chamber may extend radially outward from the shaft and/or the support, such as a support bushing of the support member. Thus, on the radial bottom side, the oil drain chamber may be defined by the shaft, the sealing bushing portion and/or the support member. For example, the support member may intrude into the oil drain chamber, thereby defining the oil drain chamber radially on the inside. On the vertical top side, the oil drain chamber may be bounded by an oil retaining wall. In particular, the oil drain chamber may be formed at least by a side wall of the support member facing the turbine and a side wall of the sealing bushing portion facing the support member, and optionally by the shaft.

According to an embodiment, the oil drain chamber may at least partially surround the shaft. The oil drain chamber may be open vertically below the shaft to allow oil to leave the oil drain chamber. For example, the oil drain chamber may receive oil from the support and may direct the oil to an oil drain port arranged vertically below the shaft. In other words, the oil drain chamber may have an oil drain opening on the vertical bottom side of the oil drain chamber vertically below the shaft. In particular, the opening may define a circumferential opening angle α greater than 0° to at least 180°. The opening angle may be open in a vertically downward direction.

According to an embodiment which can be combined with any other embodiment described herein, the exhaust gas turbine device comprises an oil retaining wall which surrounds the radially outer side of the oil drain chamber in at least a vertical top circumferential section for covering the oil drain chamber from the oil cooling chamber. Thus, the oil retaining wall can be configured to delimit the oil drain chamber. The oil retaining wall can be configured to avoid or prevent oil from entering the oil drain chamber. From a radial view, i.e. from a front view, the oil retaining wall can at least partially surround the shaft on the top side of the shaft.

The term "covering" used throughout this disclosure may be understood as not having a direct straight path between the oil cooling chamber and the oil drain chamber.The oil cooling chamber and the oil drain chamber may be fluidly connected but may not be connected by a direct straight path therebetween.

According to an embodiment, the opening of the oil drain chamber can be defined by the absence of an oil retaining wall at a vertical bottom circumferential section. The vertical bottom circumferential section can be opposite to the vertical top circumferential section. Thus, the oil retaining wall can be regarded as a (partial) semicircle arranged around the axis of rotation of the shaft, in particular as a (partial) semicircle arranged at the vertical top side of the shaft.

According to an embodiment, the oil retaining wall may be arranged radially inside the oil passage. In particular, the support member may include the oil passage, and the oil retaining wall may be arranged radially inside the oil passage.

According to an embodiment, the oil retaining wall may be configured to prevent oil from entering the oil drain chamber from the oil cooling chamber. Therefore, the oil load in the oil drain chamber may be reduced, which reduces the amount of oil at the first sealing device. Therefore, oil leakage at the first sealing device may be prevented, avoided and/or reduced.

According to an embodiment, the second sealing device may be arranged between the oil retaining wall and the supporting member and/or between the oil retaining wall and the sealing bushing part. The second sealing device may be selected from a sealing gap, a sealing ring, a labyrinth seal, a contact seal, sealing air and/or a combination thereof. The second sealing device may have an extension in a radial or axial direction. For example, when one of the supporting member and the sealing bushing part overlaps with the oil retaining wall, the second sealing device may be radially arranged between the supporting member and one of the sealing bushing parts and the oil retaining wall. In another example, when the oil retaining wall is flush with one of the supporting member and the sealing bushing part, the second sealing device may be axially arranged between the supporting member and one of the sealing bushing parts and the oil retaining wall.

According to an embodiment, the oil retaining wall may be formed integrally with one of the sealing bushing portion and the support member (and may be formed separately from the other of the sealing bushing portion and the support member, i.e., not integrally). For example, the oil retaining wall may be an axial extension of one of the sealing bushing portion and the support member, i.e., an extension parallel to the direction of the rotation axis of the shaft. The oil retaining wall may include an axial wall portion that extends axially from a wall base at said one of the sealing bushing portion and the support member.

According to an embodiment, the oil retaining wall may also include a wall tip portion axially overlapping with the other of the sealing bushing portion and the support member. In particular, the wall tip portion may be opposite to the corresponding wall base. Alternatively, the wall tip portion may be flush with the other of the sealing bushing portion and the support member. In addition, the oil retaining wall may include a radial wall portion extending radially outward from the wall portion, in particular at the wall tip portion. The radial wall portion may be flush with or axially overlap with the other of the sealing bushing portion and the support member. Therefore, it is possible to more effectively prevent oil from flowing out of the oil cooling wall.

According to an embodiment, the oil retaining wall may be connected to the oil recess. For example, when the oil retaining wall is integrally formed with one of the support member and the sealing bushing portion, the oil recess may be formed at a transition between the oil retaining wall and one of the support member and the sealing bushing portion. Thus, the discharge passage may be configured to guide the oil received from the oil cooling chamber and/or the oil retaining wall to the oil drain port.

Advantageously, the oil-cooled exhaust gas turbine device provided herein advantageously prevents cooling oil and/or secondary oil (i.e., swirl or reflected oil from the support or shaft) from directly entering the oil drain chamber, i.e., the cavity between the support member and the first sealing device, while still ensuring proper cooling of the turbine-side bearing housing by ensuring the drainage of the cooling oil. Thus, the oil sealing is improved and oil leakage can be prevented and/or avoided. Advantageously, the oil load at the first sealing device is reduced and the sealing performance at the first sealing device is enhanced.

FIG1 exemplarily shows a cross-sectional front view of an exhaust gas turbine device 100 according to an embodiment described herein, wherein the viewing direction is along the axis of the turbine. The cross section of FIG1 is indicated by A-A in FIG2 , as described below. The exhaust gas turbine device 100 includes a rotatable shaft 105 and an oil cooling chamber 140. The exhaust gas turbine device 100 may also include a support, in particular a sliding bearing. An oil retaining wall 160 is arranged between the oil cooling chamber 140 and the shaft, and defines an oil drain chamber 150. The oil drain chamber includes an oil drain opening. The opening defines a circumferential opening angle α. The oil retaining wall at least partially surrounds the shaft, and further defines an oil drain opening 152 arranged on the vertical bottom side of the shaft 105. The oil retaining wall 160 can prevent cooling oil from the oil cooling chamber from reaching the shaft, thereby reducing the amount of cooling oil reaching the shaft from the oil cooling chamber.

FIG2 exemplarily shows a cross-sectional side view of an exhaust gas turbine device 100 according to an embodiment described herein. FIG2 shows a portion of a support housing 120 and a support member 110. The exhaust gas turbine device 100 includes a support housing 120 and a support member 110, the support member 110 including a support 112, in which a shaft connected to a turbine impeller 106 is mounted. The shaft is connected to the turbine impeller 106 and can rotate within the support 112. The support member 110 can be provided as a module that can be removed from the support housing 120 as a whole.

The exhaust gas turbine device 100 further includes an oil passage 114 for supplying cooling oil to an oil cooling chamber 140, i.e., to an inner surface 122 of the oil cooling chamber 140, for cooling the turbine side wall of the support housing 120. The cooling oil may be obtained from an oil lubrication system of the support member 110. An oil drain chamber 150 is axially provided between the support member 110 and the sealing bushing portion 130. The oil drain chamber 150 is defined by an oil retaining wall 160 at the radially outer portion of the shaft 105, in particular at the vertical top.

In the embodiment shown in FIG. 2 , the oil retaining wall 160 is formed integrally with the sealing bushing portion 130 and overlaps with the supporting member 110. The oil retaining wall includes a wall tip portion 162 and a radial wall portion 164 extending radially outward. A second sealing device 166, such as a sealing gap, is provided between the oil retaining wall and the supporting member. A first sealing device 132 is provided radially between the sealing bushing portion 130 and the shaft 105. In the embodiment of FIG. 2 , the first sealing device includes an oil catch chamber and a piston ring for providing a seal to the turbine impeller 106 (axially between the oil discharge chamber 150 and the turbine impeller 106), i.e., a seal to a gas channel connected to the fluid of the turbine impeller 106.

The oil cooling chamber includes an oil recess 142 and a drain passage 144 to direct cooling oil from the oil cooling chamber 140 circumferentially around the shaft 105. Vertically below the shaft, the drain chamber 150 includes an oil drain opening 152 for allowing oil that may have reached the drain chamber to leave the drain chamber.

It should be understood that, according to an embodiment, the first sealing device may include more than one oil catch chamber, for example two to five oil catch chambers, in particular two to three oil catch chambers, even more in particular one to two oil catch chambers. For example, one or more additional webs provided radially by the sealing bushing portion in a direction toward the shaft and adjacent to the oil catch chamber may form an additional oil catch chamber. When there is more than one oil catch chamber, the individual oil catch chambers may be arranged axially in a row, in particular adjacent to each other.

FIG3 exemplarily shows a side view of an exhaust gas turbine device 100 according to an embodiment described herein. It should be understood that only a portion at the top area of the shaft is shown. In the embodiment of FIG3 , the oil retaining wall 160 is shown as being integrally formed with the support member 110, for example, integrally formed with the support flange of the support member. In particular, the oil retaining wall 160 can be arranged radially below the oil passage 114. The oil retaining wall can extend toward the sealing bushing portion 130. In particular, the oil retaining wall can overlap with the sealing bushing portion to prevent (cooling) oil from reaching the oil drain chamber. In the present embodiment, as shown in FIG3 , the second sealing device 166 can be, for example, a protrusion protruding from the sealing bushing portion 130. It can be understood that, additionally or alternatively, the second sealing device 166 can also be selected from the second sealing device described herein. For example, a sealing gap can be provided between the protrusion and the oil retaining wall. Cooling oil from the oil cooling chamber can be provided to the oil recess 142 and can be guided to the oil drain opening via a discharge channel as described herein.

According to an embodiment that can be combined with any other embodiment described herein, as exemplarily shown in FIG. 4 , the support member may include an oil deflector 170 located at the side wall of the support member facing the turbine. The oil deflector wall may overlap axially with the oil deflector 170, or may be flush with the oil deflector. According to an embodiment, the oil deflector may be an oil baffle. The oil deflector 170 may extend radially to the oil drain port 152. The oil deflector may be configured to provide a pre-discharge chamber. The pre-discharge chamber may be a chamber formed by the wall of the support member 110 facing the turbine and the oil deflector. In particular, the pre-discharge chamber may prevent lubricating oil from entering the oil drain chamber 150. Furthermore, the oil deflector may protect the support member 110 from the influence of cooling oil. Furthermore, the oil deflector may be configured to prevent (lubricating) oil from entering the oil drain chamber from the support member.

According to an embodiment that can be combined with any other embodiment described herein, as exemplarily shown in Figures 5A and 5B (enlarged view of Figure 5A), the first sealing device 132 may include an oil capture chamber 571 and a piston ring 572, or consist of them. In particular, the first sealing device may include (only) one piston ring 572. As exemplarily shown in the enlarged view of Figure 5B, the piston ring may be arranged between the sealing bushing portion 132 and the shaft 105. In particular, the piston ring 572 may be arranged in a cavity 570 of the shaft. The cavity may include a first wall on the bearing side, the first wall including a recess 574. On the axially opposite side, the cavity may include a second wall, which may taper toward the turbine side. A recess may be provided at the sealing bushing portion radially outside the recess on the bearing side. The piston ring may be arranged at the recess of the sealing bushing portion. In operation, the piston ring may be pressed against the side wall of the cavity 570 (e.g., against the shaft wall, such as the first wall of the cavity in the shaft). On the side of the piston ring facing the turbine, a notch 578 can be provided at the sealing bushing portion to allow a higher pressure to be provided to the piston ring, thereby enhancing its sealing ability. Additionally or alternatively, the notch can promote the axial movement of the piston ring by reducing the radial force, so that the axial extrusion of the piston ring against the cavity side wall (the first wall on the bearing side) can be promoted and the sealing ability of the piston ring can be enhanced.

In other respects, the description of FIGS. 1 and 2 also applies to FIGS. 3 , 4 , 5A and 5B , respectively.

The embodiments described herein may advantageously provide an oil-cooled exhaust gas turbine arrangement having increased or improved oil tightness and reduced oil load at the transition between the shaft and the turbine-side gas channel.

While the foregoing is directed to embodiments of the present disclosure, other and further embodiments of the disclosure may be devised without departing from the basic scope thereof, the scope of which is determined by the claims that follow.

Claims (15)

1. An oil-cooled exhaust gas turbine device (100), the exhaust gas turbine device comprising: a rotatable shaft (105) having a turbine wheel (106); a support member (110) comprising a support (112) for rotatably supporting the shaft; a bearing housing (120) housing the bearing member (110) therein and including a sealing bushing portion (130) extending radially inwardly toward the shaft at an axial position between the turbine wheel (106) and the bearing member (110) for providing a first sealing means (132) axially between the turbine wheel and the bearing member; and an oil cooling chamber (140) for cooling the inner surface (122) of the support housing; wherein The exhaust gas turbine apparatus includes an oil passage (114) for supplying oil into the oil cooling chamber (140) to cool an inner wall of the bearing housing using the oil as a cooling medium; and an oil drain chamber (150) axially disposed between the support member (110) and the sealing bushing portion (130); and wherein The exhaust gas turbine device further comprises an oil retaining wall (160) which surrounds the radial outer side of the oil drain chamber in at least a vertical top circumferential section for covering the oil drain chamber from the oil cooling chamber; wherein the oil retaining wall (160) is integrally formed with one of the sealing bushing portion (130) and the supporting member (110); and The oil retaining wall (160) further includes a wall tip portion (162) axially overlapping the other of the sealing bushing portion (130) and the supporting member (110). 2. The oil-cooled exhaust gas turbine device (100) according to claim 1, wherein the oil drain chamber (150) extends radially outward from the shaft (105) and/or from a bearing bushing of the bearing component (110). 3. An oil-cooled exhaust gas turbine device (100) according to any one of the preceding claims, wherein the oil retaining wall (160) includes an axial wall portion, which extends axially from a wall base at the sealing bushing part (130) and the one of the support members (110). 4. The oil-cooled exhaust gas turbine device (100) according to claim 1, wherein the oil retaining wall (160) further includes a radial wall portion (164) extending radially outward from the wall portion, in particular at the wall tip portion. 5. An oil-cooled exhaust gas turbine device (100) according to any of the preceding claims, wherein the oil drain chamber (150) is formed at least by a side wall of the support member (110) facing the turbine and a side wall of the sealing bushing part (130) facing the support member, and optionally by the shaft. 6. An oil-cooled exhaust gas turbine device (100) according to any of the preceding claims, wherein the oil cooling chamber (140) is axially bounded by the support housing (120) and the support member (110), and wherein the sealing bushing portion (130) at least partially bounds the oil cooling chamber (140) radially from the inside and axially from the turbine impeller (106). 7. An oil-cooled exhaust gas turbine device (100) according to any of the preceding claims, wherein the oil drain chamber (150) has an oil drain opening (152) on the vertical bottom side of the oil drain chamber (150), in particular wherein the opening defines a circumferential opening angle (α) greater than 0° to at least 180°. 8. An oil-cooled exhaust gas turbine device (100) according to any of the preceding claims, wherein the oil cooling chamber (140) includes an oil recess (142) for receiving oil from the oil cooling chamber (140), and wherein the oil recess (142) forms a discharge channel (144), the discharge channel (144) extending at least partially circumferentially for guiding cooling oil downwardly along the oil discharge channel (144) around the rotatable shaft. 9. An oil-cooled exhaust gas turbine device (100) according to any one of the preceding claims, wherein an oil drain port is arranged vertically below the shaft (105), and wherein the discharge passage (144) is configured to guide the oil received from the oil cooling chamber (140) and/or the oil retaining wall (160) to the oil drain port. 10. An oil-cooled exhaust gas turbine device (100) according to any of the preceding claims, wherein the first sealing device (132) comprises a sealing element, and wherein the shaft (105) comprises a cavity (570) for supporting the sealing element, in particular wherein the sealing element is a piston ring (572). 11. An oil-cooled exhaust gas turbine device (100) according to any one of the preceding claims, wherein a second sealing device (166) is arranged between the oil retaining wall (160) and the supporting member (110) and/or between the oil retaining wall (160) and the sealing bushing part (130). 12. The oil-cooled exhaust gas turbine device (100) according to any one of the preceding claims, wherein the oil retaining wall (160) is arranged radially inside the oil channel (114), in particular wherein the support member (110) includes the oil channel (114). 13. The oil-cooled exhaust gas turbine device (100) according to any one of claims 11 or 12, wherein the second sealing device (166) is selected from a sealing gap, a sealing ring, a labyrinth seal, a contact seal, sealing air and/or a combination thereof. 14. An oil-cooled exhaust gas turbine device (100) according to any of the preceding claims, wherein the support member (110) comprises an oil deflector plate (170) located at a side wall of the support member (110) facing the turbine, and wherein the oil retaining wall (160) axially overlaps the oil deflector plate. 15. The oil-cooled exhaust gas turbine device (100) according to any one of the preceding claims, wherein the oil-cooled exhaust gas turbine device (100) is a turbocharger or a power turbine.