CN117940653A - Oil cooled exhaust gas turbine apparatus - 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 apparatus

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 an oil cooled exhaust gas turbine apparatus having radial bearings and a sealing device.

Background

Exhaust gas turbine devices such as exhaust gas turbochargers are known for increasing the power of an internal combustion engine. In such an exhaust gas turbocharger, the turbine is disposed in the exhaust gas path of the internal combustion engine, and the compressor is disposed upstream of the internal combustion engine, the compressor being connected to the turbine via a common shaft. The shaft is typically supported by a shaft bearing supported in a bearing housing. Thus, exhaust gas turbochargers are generally composed of a rotor, a shaft support assembly, a flow guiding housing portion (compressor housing and turbine housing), and a support housing. The rotor includes a shaft, an impeller, and a turbine wheel.

An exhaust gas turbine device allows energy stored in the exhaust gas of an internal combustion engine to be converted into rotational energy. In the case of turbochargers using such rotational energy to charge an internal combustion engine, the capacity in the cylinder and the fuel mixture increase, and thus a significant power increase of the engine is obtained. In the case of a power turbine, rotational energy may 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, an electrical generator or a mechanical consumer is connected to the turbine shaft.

The bearings of the exhaust gas turbine device are typically lubricated by a lubricating oil.

Due to the high process pressures in the turbine side and compressor side flow areas, 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 support housing generally corresponds to atmospheric pressure. However, the gas pressure in the compressor-side and turbine-side flow channels depends on the current operating point of the exhaust-gas turbocharger and is located above the pressure in the cavity of the bearing housing at most operating points. However, in some cases, negative pressure (e.g., during part load operation or at rest) is also considered.

The lubrication oil supplied to the packing system support is typically required to be sealed by a shaft seal to avoid leakage of oil into the gas path of the component. However, in an oil cooled filling system, the oil load within the oil filled system may increase excessively due to different pressure conditions, thereby making oil leakage more likely to occur, for example at the shaft seal. In particular in oil cooling systems, lubricating oil can also be used to cool the bearing housing, and high oil loads can lead to increased oil leakage.

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

Disclosure of Invention

In view of the foregoing, an oil-cooled exhaust gas turbine apparatus is provided. The exhaust gas turbine apparatus includes a rotatable shaft having a turbine wheel; a bearing member including a bearing for rotatably supporting the shaft; a bearing housing accommodating the bearing member therein and including a seal bushing portion extending radially inward toward the shaft at an axial location between the turbine wheel and the bearing member; for providing a first sealing means axially between the turbine wheel and the support member; and an oil cooling chamber for cooling the inner surface of the support housing. The exhaust gas turbine apparatus further comprises an oil passage for providing oil into the oil cooling chamber for cooling the inner wall of the bearing housing using the oil as cooling medium; and an oil drain chamber axially disposed between the support member and the seal bushing portion. The exhaust gas turbine arrangement further comprises an oil retaining wall surrounding the radially outer side of the oil discharge chamber in at least the vertical top circumferential section for covering the oil discharge chamber from the oil cooling chamber.

Embodiments are also directed to methods for operating the apparatus. It includes method aspects for implementing each function of the device.

Drawings

So that the manner in which the above recited features of the present disclosure can be understood in detail, a more particular description of the disclosure, briefly summarized above, may be had by reference to embodiments. The drawings relate to embodiments of the present disclosure and are described below:

FIG. 1 illustrates a cross-sectional elevation view of an exhaust gas turbine apparatus according to embodiments described herein;

FIG. 2 illustrates a cross-sectional side view of an exhaust gas turbine apparatus according to embodiments described herein;

FIG. 3 illustrates a cross-sectional side view of an exhaust gas turbine apparatus according to embodiments described herein;

FIG. 4 illustrates a cross-sectional side view of an exhaust gas turbine apparatus according to embodiments described herein; and

Fig. 5A and 5B illustrate cross-sectional side views and enlarged views of an exhaust gas turbine apparatus according to embodiments described herein.

Detailed Description

Reference will now be made in detail to the various embodiments of the disclosure, one or more examples of which are illustrated in the figures. In the following description of the drawings, like reference numerals refer to like parts. In general, only the differences with respect to the respective embodiments are described. Each example is provided by way of explanation of the present disclosure, and is not meant as a limitation of the present disclosure. Furthermore, features illustrated or described as part of one embodiment can be used on or in conjunction with other embodiments to yield yet a further embodiment. This specification is intended to include such modifications and alterations.

In the following description of the drawings, the same reference numerals refer to the same or similar parts. In general, only the differences with respect to the respective embodiments are described. Unless otherwise specified, the description of a portion or aspect in one embodiment also applies to the corresponding portion or aspect in another embodiment.

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

According to an embodiment, the turbine apparatus comprises a bearing member comprising a bearing for rotatably supporting the shaft. The shaft is rotatable within the support. The support may be a sliding bearing or a rolling bearing. The support may be (include) a radial bearing and/or an axial bearing. The support may include a support bushing to allow the shaft to rotate within the support. The support member may comprise a support flange for mounting the support member within the support housing.

According to embodiments, which may be combined with any of the other embodiments described herein, the turbine apparatus may comprise 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 the central cavity of the support housing. The support member may be mounted to the support housing by a support flange. The support housing may at least partially radially surround a support member comprising a 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, i.e. the bearing housing may delimit the bearing member towards the turbine wheel. In particular, the support housing can define the support member axially.

According to an embodiment, the bearing housing comprises a seal bushing portion extending radially inwards towards the shaft at an axial position between the turbine wheel and the bearing member. The seal bushing portion may be a wall of the bearing housing facing the turbine. For example, the seal bushing portion may be integrally formed with the bearing housing. Or the seal bushing portion may be a separate component from the bearing housing. Additionally or alternatively, the sealing liner portion and the support member may be separate components with respect to each other, i.e. the sealing liner portion and the support member may be non-integrally formed with respect to each other. Furthermore, the support member may be a separate component with respect to the support housing. Thus, both the sealing liner portion and the support member may be separate components from the support housing, i.e. both the sealing liner portion and the support member may be formed non-integrally with the support housing. Additionally or alternatively, the seal bushing portion may be separate (non-integral) from the bearing housing, and the bearing member may be integrally formed with the bearing housing. Or the seal bushing portion may be integrally formed with the bearing housing and the bearing member may be separate (non-integral) from the bearing housing.

According to embodiments, which may be combined with any of the other embodiments described herein, the exhaust gas turbine arrangement may comprise an oil supply system. The oil supply system may supply oil, in particular lubricating oil, to the support member, in particular to the support, for lubricating the support. The oil supply system may be configured to supply oil, in particular cooling oil, to the oil channel and through the oil channel to the oil cooling chamber. Accordingly, the oil supply system may be configured to provide oil to the support member and the oil cooling chamber for cooling the support housing, in particular for cooling the turbine-facing wall of the support housing.

According to an embodiment, which may be combined with any of the other embodiments described herein, the turbine apparatus, in particular the bearing housing, may comprise an oil cooling chamber for cooling the inner surface of the bearing housing. The inner surface of the bearing housing may comprise the inner side of the sealing bush part, i.e. the side of the sealing bush part facing the bearing member. Additionally or alternatively, the inner surface of the bearing housing may be the inner side of the bearing housing facing the turbine wall. The oil cooling chamber may be a space between the support member and the support housing and/or the seal bushing portion. In other words, the oil cooling chamber may be provided by the support housing and the support member. Furthermore, 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 at a vertical top region of the shaft. The oil cooling chamber may be axially defined by the support housing and the support member. Further, the seal bushing portion may at least partially define an oil cooling chamber from radially inside and axially from the turbine wheel.

According to an embodiment, the oil cooling chamber may be provided with oil for cooling an inner surface of the oil cooling chamber. The oil cooling chamber may receive oil, in particular lubricating oil, from the oil channel. The oil passage may be arranged within the turbine device. In other words, the exhaust gas turbine device may comprise an oil channel. In particular, the support member, e.g. the support flange, may comprise an oil channel. The oil channel may be a hole in a wall of the turbine device. The oil passage may be directed toward the inner surface of the bearing housing and/or the oil cooling chamber to spray oil toward the inner surface of the bearing housing and/or the oil cooling chamber. The oil passages may be holes and/or nozzles for spraying oil towards the inner surface of the oil cooling chamber for cooling the inner surface and thus the bearing housing. It is possible to cool by the cooling oil flowing down the inner surface of the bearing housing.

According to an embodiment, the oil cooling chamber may comprise an oil recess for receiving oil from the oil cooling chamber. The oil recess may be arranged at the bearing member and/or the seal bushing portion. For example, the oil recess may be integrally formed with one of the support member and/or the seal 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 drain channel may extend at least partially circumferentially for guiding cooling oil down the drain channel around the rotatable shaft. The drain passage may be configured to direct cooling oil to the drain port. The oil recess and/or the drain channel may be arranged in a radially inward position compared to the position of the oil channel.

According to an embodiment, the exhaust gas turbine arrangement may comprise an oil drain. The oil drain may be disposed vertically below the shaft. The oil drain may be configured to receive oil from the oil cooling chamber. The oil drain may be further configured to provide received oil back to the oil supply system. Thus, the oil may be re-used for lubrication and/or cooling.

According to an embodiment, which may be combined with any of the other embodiments described herein, the seal bushing portion is configured to provide a first sealing arrangement axially between the turbine wheel and the support member. The sealing means may be radially arranged between the sealing bush portion and the shaft. In particular, the shaft may be rotatable and the sealing means may be arranged fixed relative to the sealing bush portion. The first sealing means may prevent (lubricating or cooling) oil from the bearing side (e.g. from the bearing and/or from the discharge chamber) from entering towards the turbine wheel, i.e. towards the gas channel of the exhaust gas turbine device. Furthermore, the first sealing means may prevent hot gas from entering from the turbine wheel towards the support side. Here, the term "prevent" means that the first sealing means has a significant sealing effect on oil and/or hot gas, so that a pressure drop is significantly maintained, for example by the sealing means (so that the bearing side can be kept substantially at atmospheric pressure even at an overpressure on the turbine side). On the other hand, the term "preventing" does not exclude, for example, small amounts of residual oil and/or hot gas ("blowby") passing through the first sealing means.

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

According to an embodiment, which may be combined with any of the other embodiments described herein, the first sealing means may be or comprise a sealing element, such as a piston ring. Additionally or alternatively, the first sealing means may be or comprise two (or more) sealing elements. In particular, the two sealing elements may be a catch chamber and a piston ring. The oil trap chamber and the piston ring may be arranged in a row axially in the direction towards the turbine, i.e. the piston ring may be arranged axially closer on the turbine side than the oil trap chamber. Furthermore, the first sealing means may comprise further piston rings, for example by having two piston rings adjacent to each other. Thus, the sealing device may have a total of two sealing elements (e.g. one piston ring and one oil trap chamber) or three sealing elements, e.g. two piston rings and one oil trap chamber. By selecting a total of two or three sealing elements for the sealing arrangement in this way, the first sealing arrangement can be suitably dimensioned to provide a good balance between (axial) space requirements and sealing function.

According to an embodiment, which may be combined with any of the other embodiments described herein, the shaft may provide a cavity for supporting the piston ring, e.g. for sandwiching the piston ring between the shaft and the (stationary) sealing bushing portion. Furthermore, when the oil-cooled exhaust gas turbine device is in operation, the piston rings may be pressed axially against the cavity of the shaft. The cavity may have a first wall and a second wall on axially opposite sides. The first wall may be arranged on a bearing side of the cavity and the second wall may be arranged on a turbine side of the cavity. Thus, the piston ring may be pressed axially against the first wall of the cavity. The first wall may further comprise a support side recess. Radially outward of the recess, the seal liner portion may include a radial recess adjacent the piston ring, i.e., a recess relative to the bearing side of the piston ring. Additionally or alternatively, the piston ring may be provided 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 that the piston ring may press against the shaft during operation.

According to an embodiment, the cavity may provide space on the turbine facing side of the piston ring to allow the piston ring to be pressed axially towards 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. Thus, less exhaust gas, so-called "blowby", may pass through the first sealing means, i.e. the sealing element.

According to an embodiment, the sealing liner portion may comprise a recess. The recess may extend towards the turbine side of the seal bushing portion. Thus, a higher pressure may act on the piston ring, thereby improving the compression of the piston ring against the first wall of the cavity. Therefore, the air tightness of the first sealing device can be improved and enhanced. The recess may further reduce blowby through the first seal or the sealing element of the first seal.

According to an embodiment, which may be combined with any of the other embodiments described herein, the exhaust gas turbine arrangement comprises an oil extraction chamber axially arranged between the support member and the sealing bushing portion. The oil discharge chamber may be a space axially formed between the support member and the seal bushing portion. Thus, the axial extension of the oil discharge chamber may depend on the distance between the support member and the seal bushing portion.

According to an embodiment, the oil discharge chamber may extend radially outwards from the shaft and/or the support (e.g. a support bushing of the support member). Thus, on the radial bottom side, the oil drain chamber may be defined by the shaft, the seal bushing portion and/or the support. For example, the support may intrude into the oil discharge chamber, thereby defining the oil discharge chamber radially inward. On the vertical top side, the oil discharge chamber may be delimited by an oil retaining wall. In particular, the oil discharge 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 discharge chamber may at least partly surround the shaft. The oil discharge chamber may be opened vertically below the shaft to allow oil to leave the oil discharge chamber. For example, the oil drain chamber may receive oil from the support, and may direct the oil to an oil drain disposed vertically below the shaft. In other words, the oil discharge chamber may have an oil discharge opening at a vertical bottom side of the oil discharge chamber vertically below the shaft. In particular, the opening may define a circumferential opening angle α of greater than 0 ° to at least 180 °. The opening angle may open in a vertically downward direction.

According to an embodiment, which may be combined with any of the other embodiments described herein, the exhaust gas turbine arrangement comprises an oil retaining wall surrounding the radially outer side of the oil discharge chamber in at least the vertical top circumferential section for covering the oil discharge chamber from the oil cooling chamber. Thus, the oil retaining wall may be configured to define an oil discharge chamber. The oil retaining wall may be configured to avoid or prevent oil from entering the oil discharge chamber. From a radial view, i.e. from a front view, the oil retaining wall may at least partly surround the shaft at the top side of the shaft.

The term "cover" as used throughout this disclosure may be understood as there is no direct straight line path between the oil cooling chamber and the oil extraction 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 discharge chamber may be defined by the absence of an oil retaining wall at the vertical bottom circumferential section. The vertical bottom circumferential section may be opposite the vertical top circumferential section. The oil retaining wall may thus be regarded as a (partial) semicircle arranged around the rotational axis 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 channel. In particular, the support member may comprise an oil channel, and the oil retaining wall may be arranged radially inside the oil channel.

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

According to an embodiment, the second sealing means may be arranged between the oil retaining wall and the support member and/or between the oil retaining wall and the sealing bushing portion. The second sealing means may be selected from the group consisting of a sealing gap, a sealing ring, a labyrinth seal, a contact seal, sealing air and/or combinations thereof. The second sealing means may have an extension in a radial or axial direction. For example, when one of the support member and the seal bushing portion overlaps the oil retaining wall, the second sealing means may be arranged radially between the oil retaining wall and one of the support member and the seal bushing portion. In another example, the second sealing means may be axially arranged between the oil retaining wall and one of the support member and the sealing liner portion when the oil retaining wall is level with the one of the support member and the sealing liner portion.

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

According to an embodiment, the oil retaining wall may further comprise a wall tip portion axially overlapping the other of the sealing liner portion and the support member. In particular, the wall tip portion may be opposite to the corresponding wall base portion. Or the wall tip portion may be flush with the other of the seal bushing portion and the support member. Furthermore, the oil retaining wall may comprise a radial wall portion extending radially outwardly from the wall portion, in particular at the wall tip portion. The radial wall portion may be flush or axially overlapping with the other of the seal bushing portion and the support member. Therefore, the outflow of oil from the oil cooling wall can be prevented more effectively.

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 seal bushing portion, the oil recess may be formed at a transition of the oil retaining wall with one of the support member and the seal bushing portion. Thus, the drain passage may be configured to direct oil received from the oil cooling chamber and/or the oil retaining wall to the oil drain.

Advantageously, the oil cooled exhaust gas turbine apparatus provided herein advantageously prevents cooling oil and/or secondary oil (i.e. swirling or reflected oil from the support or shaft) from directly entering the oil discharge chamber, i.e. the chamber between the support member and the first sealing means, while still ensuring proper cooling of the turbine side support housing due to ensuring cooling oil discharge. Thus, the oil tightness is improved and oil leakage can be prevented and/or avoided. Advantageously, the oil load at the first sealing means is reduced and the sealing performance at the first sealing means is enhanced.

Fig. 1 schematically illustrates a cross-sectional elevation view of an exhaust gas turbine apparatus 100 according to embodiments described herein, with the viewing direction along the axis of the turbine. The cross-section of fig. 1 is indicated with A-A in fig. 2, as described below. The exhaust gas turbine apparatus 100 includes a rotatable shaft 105 and an oil cooling chamber 140. The exhaust gas turbine device 100 may further comprise a support, in particular a sliding bearing. An oil baffle wall 160 is disposed between the oil cooling chamber 140 and the shaft and defines an oil discharge 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 disposed at a vertical bottom side of the shaft 105. The oil baffle wall 160 may 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.

FIG. 2 schematically illustrates a cross-sectional side view of an exhaust gas turbine apparatus 100 according to embodiments described herein. Fig. 2 shows a portion of the support housing 120 and the support member 110. The exhaust gas turbine apparatus 100 comprises a support housing 120 and a support member 110, the support member 110 comprising a support 112, a shaft connected to the turbine wheel 106 being mounted in the support 112. The shaft is connected to the turbine wheel 106 and is rotatable within the support 112. The support member 110 may be provided as a module that is removable from the support housing 120 as a whole.

The exhaust gas turbine apparatus 100 further comprises an oil channel 114 for providing cooling oil to the oil cooling chamber 140, i.e. to the inner surface 122 of the oil cooling chamber 140, for cooling the turbine side wall of the bearing housing 120. The cooling oil may be obtained from an oil lubrication system of the support member 110. An oil discharge chamber 150 is axially provided between the support member 110 and the seal bushing portion 130. The oil discharge chamber 150 is delimited radially outside the shaft 105, in particular at the vertical top, by an oil retaining wall 160.

In the embodiment shown in fig. 2, the oil baffle wall 160 is integrally formed with the seal bushing portion 130 and overlaps the support member 110. The oil retaining wall includes a wall tip portion 162 and a radially outwardly extending radial wall portion 164. A second sealing means 166, such as a sealing gap, is provided between the oil retaining wall and the support member. A first sealing device 132 is provided radially between the sealing bush portion 130 and the shaft 105. In the embodiment of fig. 2, the first sealing means comprises an oil trap chamber and piston rings for providing a seal (axially between the oil drain chamber 150 and the turbine wheel 106) against the turbine wheel 106, i.e. against a gas channel in fluid connection with the turbine wheel 106.

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

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

FIG. 3 schematically illustrates a side view of an exhaust gas turbine apparatus 100 according to embodiments described herein. It should be understood that only a portion at the top region of the shaft is shown. In the embodiment of fig. 3, the oil retaining wall 160 is shown as being integrally formed with the support member 110, such as with a support flange of the support member. In particular, the oil retaining wall 160 may be disposed radially below the oil passage 114. The oil retaining wall may extend toward the seal bushing portion 130. In particular, the oil retaining wall may partially overlap the sealing bushing to prevent (cooling) oil from reaching the oil drain chamber. In this embodiment, as shown in fig. 3, the second sealing means 166 may be, for example, a protrusion protruding from the seal bushing portion 130. It will be appreciated that the second sealing means 166 may additionally or alternatively be selected from the second sealing means described herein. For example, a sealing gap may be provided between the protrusion and the oil retaining wall. Cooling oil from the oil cooling chamber may be provided to the oil recess 142 and may be directed to the oil drain opening via a drain channel as described herein.

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

According to embodiments, which may be combined with any of the other embodiments described herein, as exemplarily shown in fig. 5A and 5B (enlarged view of fig. 5A), the first sealing device 132 may comprise or consist of the oil trap chamber 571 and the piston ring 572. In particular, the first sealing means may comprise (only) one piston ring 572. As exemplarily shown in the enlarged view of fig. 5B, a piston ring may be disposed between the seal bushing portion 132 and the shaft 105. In particular, the piston ring 572 may be disposed in the shaft cavity 570. The cavity may include a bearing-side first wall that includes a recess 574. On the axially opposite side, the cavity may comprise a second wall, which may taper towards the turbine side. Radially outward of the bearing-side recess, a recess may be provided at the seal liner portion. The piston ring may be disposed in a recess of the seal liner portion. In operation, the piston ring may press against a sidewall of the cavity 570 (e.g., against a shaft wall, such as a first wall of a cavity in a shaft). On the turbine facing side of the piston ring, a recess 578 may be provided at the seal liner portion to allow higher pressure to be provided to the piston ring to enhance its sealing ability. Additionally or alternatively, the recess may facilitate axial movement of the piston ring by reducing the radial force, so that axial compression of the piston ring against the cavity side wall (bearing side first wall) may be facilitated and the sealing ability of the piston ring enhanced.

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

The embodiments described herein may advantageously provide an oil cooled exhaust gas turbine apparatus having increased or improved oil tightness and reduced oil loading at the transition between the shaft and the turbine side gas passage.

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, and the scope thereof is determined by the claims that follow.

Claims (15)

1. An oil cooled exhaust gas turbine apparatus (100), the exhaust gas turbine apparatus comprising:

a rotatable shaft (105) having a turbine wheel (106);

a bearing member (110) including a bearing (112) for rotatably supporting the shaft;

a bearing housing (120) housing the bearing member (110) therein and including a seal bushing portion (130) extending radially inwardly toward the shaft at an axial location between the turbine wheel (106) and the bearing member (110) for providing a first seal arrangement (132) axially between the turbine wheel and the bearing member; and

An oil cooling chamber (140) for cooling an inner surface (122) of the bearing housing; wherein the method comprises the steps of

The exhaust gas turbine device comprises an oil channel (114) for providing oil into the oil cooling chamber (140) for cooling the inner wall of the bearing housing using the oil as cooling medium; and

An oil discharge chamber (150) axially arranged between the support member (110) and the seal bushing portion (130); and wherein

The exhaust gas turbine arrangement further comprises an oil retaining wall (160) surrounding a radially outer side of the oil extraction chamber in at least a vertical top circumferential section for covering the oil extraction chamber from the oil cooling chamber;

Wherein the oil retaining wall (160) is integrally formed with one of the seal bushing portion (130) and the support member (110); and

Wherein the oil retaining wall (160) further comprises a wall tip portion (162) axially overlapping the other of the seal bushing portion (130) and the support member (110).

2. The oil cooled exhaust gas turbine apparatus (100) according to claim 1, wherein the oil discharge chamber (150) extends radially outwards from the shaft (105) and/or from a support bushing of the support member (110).

3. The oil cooled exhaust gas turbine apparatus (100) of any preceding claim, wherein the oil retaining wall (160) comprises an axial wall portion extending axially from a wall base at the one of the seal bushing portion (130) and the support member (110).

4. The oil cooled exhaust gas turbine apparatus (100) according to claim 1, wherein the oil retaining wall (160) further comprises a radial wall portion (164) extending radially outwardly from a wall portion, in particular at the wall tip portion.

5. The oil cooled exhaust gas turbine arrangement (100) according to any one of the preceding claims, wherein the oil discharge chamber (150) is formed at least by a turbine-facing side wall of the support member (110) and a support member-facing side wall of the seal bushing portion (130), and optionally by the shaft.

6. The oil cooled exhaust gas turbine apparatus (100) according to any one of the preceding claims, wherein the oil cooling chamber (140) is axially delimited by the bearing housing (120) and the bearing member (110), and wherein the seal bushing portion (130) at least partly delimits the oil cooling chamber (140) axially from radially inside and from the turbine wheel (106).

7. The oil cooled exhaust gas turbine arrangement (100) according to any one of the preceding claims, wherein the oil discharge chamber (150) has an oil discharge opening (152) at a vertical bottom side of the oil discharge chamber (150), in particular wherein the opening defines a circumferential opening angle (a) of more than 0 ° to at least 180 °.

8. The oil cooled exhaust gas turbine apparatus (100) according to any one of the preceding claims, wherein the oil cooling chamber (140) comprises an oil recess (142) for receiving oil from the oil cooling chamber (140), and wherein the oil recess (142) forms a drain channel (144), the drain channel (144) extending at least partially circumferentially for guiding cooling oil down the oil drain channel (144) around the rotatable shaft.

9. The oil cooled exhaust gas turbine apparatus (100) according to any one of the preceding claims, wherein an oil drain is arranged vertically below the shaft (105), and wherein the drain channel (144) is configured to direct oil received from the oil cooling chamber (140) and/or the oil retaining wall (160) to the oil drain.

10. The oil cooled exhaust gas turbine apparatus (100) according to any one of the preceding claims, wherein the first sealing means (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. The oil cooled exhaust gas turbine apparatus (100) according to any one of the preceding claims, wherein a second sealing means (166) is provided between the oil retaining wall (160) and the support member (110) and/or between the oil retaining wall (160) and the sealing bushing portion (130).

12. The oil cooled exhaust gas turbine apparatus (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) comprises the oil channel (114).

13. The oil cooled exhaust gas turbine apparatus (100) according to any one of claims 11 or 12, wherein the second sealing means (166) is selected from a sealing gap, a sealing ring, a labyrinth seal, a contact seal, sealing air and/or a combination thereof.

14. The oil cooled exhaust gas turbine apparatus (100) according to any one of the preceding claims, wherein the support member (110) comprises an oil deflector plate (170) at a turbine facing side wall of the support member (110), and wherein the oil retaining wall (160) axially overlaps the oil deflector plate.

15. The oil cooled exhaust gas turbine apparatus (100) according to any one of the preceding claims, wherein the oil cooled exhaust gas turbine apparatus (100) is a turbocharger or a power turbine.