Coolable turbine module for a turbomachine, and turbomachine

Abstract

The invention relates to a turbine module (100) for a turbomachine (1), comprising a turbine housing (101) with an annular outer wall (2) and an inner housing (3), and an annular channel (4) for distributing a cooling fluid in a circumferential direction (U) of the turbine module, wherein the annular channel sits on the outside of the outer wall, has at least one inlet (5) for the cooling fluid to flow into the annular channel, and openings (6) for the cooling fluid to flow out into cooling lines (7) of the inner housing. It is provided that a separating device (8) extending in the circumferential direction is provided within the annular channel, which divides the annular channel into a radially inner interior space (9) and a radially outer exterior space (10). The invention further relates to a corresponding compressor module (200) and an associated turbomachine (1).

Description

[0001] The invention relates to a turbine module for a turbomachine, comprising a turbine housing with an annular outer wall and an inner housing, and an annular channel for distributing a cooling fluid in a circumferential direction of the turbine module, wherein the annular channel sits directly on the outer wall on the outside, has at least one inlet for the cooling fluid to flow into the annular channel, and has openings for the cooling fluid to flow out into cooling lines of the inner housing.The invention further relates to a compressor module for a turbomachine, comprising a compressor housing with an annular outer wall and an inner housing, and an annular channel for distributing a thermal fluid in a circumferential direction of the compressor module. The annular channel sits directly on the outer wall on the outside, has at least one inlet for the thermal fluid to flow into the annular channel, and has openings for the thermal fluid to flow out into heat lines of the inner housing. Furthermore, the invention relates to a turbomachine, in particular an aircraft gas turbine.

[0002] It is known from the prior art that cooling air from the compressor can be supplied to components in turbomachines subject to high temperatures, such as high- and low-pressure turbine blades. In the inlet area of ​​turbomachines, especially aircraft gas turbines, heated air from the high-pressure compressor can be used to heat components such as guide vanes and prevent icing. In both applications, it is desirable to supply compressor air to the target component to be cooled or heated with the most uniform temperature distribution possible and with as little heat loss or heat input as possible.

[0003] The cooling of the inner casing, in particular by air, preferably from the compressor, can be achieved in the prior art using an annular duct positioned at the axial height of the inner casing of the turbine module. The cool bleed air is directed from the annular duct into respective struts of the inner casing to ensure that the temperature of the material remains below a critical temperature. It is necessary that the bleed air absorbs as little heat as possible between the source, in particular the compressor, and the sink, in particular the strut, and that the bleed air temperature in the annular duct has as little circumferential variation as possible. In particular, it may be desirable to achieve temperature homogeneity in the circumferential direction in order to cool the individual struts evenly around the circumference. This can be particularly important if there is only a single air supply at the circumference.

[0004] The situation is analogous when heating the components of the compressor module. The heating of the inner casing, for example a bearing star of the low-pressure compressor (LPV), in particular by warm bleed air, preferably from the HPV, can be achieved in the prior art using an annular duct positioned at the axial height of the inner casing of the compressor module. The warm air is directed from the annular duct into the respective struts of the inner casing to ensure that the material temperature remains above freezing during critical flight phases. It is necessary that the bleed air loses as little heat as possible between the source, in particular the HPV, and the sink, in particular the strut, and that the bleed air temperature in the annular duct exhibits as little circumferential variation as possible. In particular, it may be desirable to achieve temperature homogeneity in the circumferential direction in order to heat the individual struts evenly around the circumference.This can be particularly important if there is only a single air supply at the perimeter.

[0005] The invention is based on the object of providing a turbine module, a compressor module and a turbomachine by means of which a heat inflow to the cooling fluid or a heat outflow from the heat fluid within the annular channel can be reduced.

[0006] The problem is solved by the subject matter of the independent patent claims. Advantageous developments of the invention are described by the dependent patent claims, the following description, and the figures.

[0007] A first aspect of the invention provides a turbine module for a turbomachine. The turbine module comprises at least one turbine housing with an annular outer wall and an inner housing. The turbine module further comprises at least one annular channel for distributing a cooling fluid in a circumferential direction of the turbine module. The annular channel sits directly on the outer wall on the outside. The annular channel has at least one inlet for the cooling fluid to flow into the annular channel. In addition, the annular channel has openings for the cooling fluid to flow out into cooling lines of the inner housing. A separating device extending in the circumferential direction is provided within the annular channel, which divides the annular channel into a radially inner interior space and a radially outer exterior space.

[0008] The use of the separating device in the annular channel advantageously ensures that the outer space of the annular channel is better shielded from the outer wall of the turbine housing. This advantageously ensures that heat input into the cooling fluid in the outer space is significantly reduced. When the cooling fluid is distributed circumferentially, significantly less heat exchange occurs, allowing temperature gradients in the circumferential direction to be reduced. Thus, virtually uniform temperature in the annular channel can be ensured, allowing the inner housing to be cooled evenly all around by the cooling fluid.

[0009] The inner housing to be cooled can, in particular, have static elements to which, for example, moving and rotating components can be attached or mounted. The inner housing can preferably have struts that extend in a radial direction from the outer wall to a core or to a turbine center frame (TCF) of the turbine module and firmly connect the outer wall to the TCF. The struts can, in particular, be evenly distributed in the circumferential direction. The cooling lines can, in particular, be formed within the inner housing. The cooling lines can preferably be cavities within the struts and within the TCF, which guide the cooling fluid in a targeted manner.

[0010] The annular channel can be arranged, in particular, in an axial direction of the turbine housing at the same height as the inner housing, in particular as the struts. In particular, the annular channel sits directly on the outer wall. The annular channel, also referred to as an air box, for example, is designed to guide the cooling fluid within its interior and to distribute the cooling fluid preferably evenly in the circumferential direction. The annular channel can be formed completely circumferentially, such that the annular channel can assume a closed annular shape. The annular channel can, in particular, have a certain width in the axial direction and a certain height in the radial direction, wherein a length of the ring can substantially correspond to a circumference of the outer wall at this axial position. The annular channel can, in particular, have walls within which the cooling fluid can be guided.The cross-section of the annular channel can preferably be substantially rectangular, or, for example, semicircular or semi-elliptical. The annular channel can preferably have a radially inner inner wall, a radially outer outer wall, an axially forward front wall, and an axially rearward rear wall.

[0011] The annular channel can, in particular, have precisely one inlet through which the cooling fluid can flow into the annular channel. The cooling fluid can, in particular, be air, which can be drawn off from the compressor or from the environment and supplied to the annular channel through the inlet. The inlet is preferably arranged in a radially outer region of the annular channel or in the outer space, so that heat input from the turbine into a cooling fluid supply line, which can be connected to the inlet, is minimal.

[0012] The cooling fluid flowing into the annular channel through the inlet can, in turn, flow out of the annular channel through the openings. In particular, exactly one opening or multiple openings can be provided for each strut of the inner casing. In particular, each opening can fluidly connect the annular channel to a respective cooling line of the strut or to the cooling lines of the inner casing. The opening can, in particular, extend through the inner wall of the annular channel or the outer wall of the turbine casing to the cooling line.

[0013] The hot turbine gas can be arranged to flow directly inside the outer wall of the turbine housing, thereby heating the outer wall. The outer wall thus limits the flow of the turbine gas radially outward. No turbine gas flows directly outside the heated outer wall, where the annular channel rests.

[0014] The separating device within the annular channel preferably runs completely in the circumferential direction, so that the separating device is also essentially annular or cylindrical. The separating device essentially spatially separates the annular channel into the interior and exterior spaces. However, it is not necessary for the interior and exterior spaces to be fluidically sealed off from one another by the separating device. The exterior space is formed in particular essentially by the outer wall of the annular channel, an outer section of the front and rear walls, and an outer side of the separating device, and the interior space is formed in particular essentially by the inner wall of the annular channel, an inner section of the front and rear walls, and an inner side of the separating device, so that the exterior space is essentially shielded from the interior or the outer wall of the turbine housing by the separating device.Preferably, the volume of the exterior space can be significantly larger than the volume of the interior space. In particular, the height of the exterior space in the radial direction can also be significantly larger than the height of the interior space.

[0015] One embodiment provides that the outer space of the annular channel has the at least one inlet and the openings. Because the cooling fluid flows from the inlet into the outer space, is distributed within the outer space, in particular in the circumferential direction, and flows out again from the outer space through the openings in the outer space, it can advantageously be ensured that no cooling fluid, or only a small amount, flows into the inner space. In particular, the flow velocity of the cooling fluid in the inner space is thus zero or at least almost zero, or is considerably reduced compared to the flow velocity of the cooling fluid in the outer space. Due to the reduced flow velocity of the cooling fluid in the inner space, only a small amount of heat can be transferred or convection can take place from the outer wall of the turbine housing to the inner side of the separating device. The cooling fluid in the inner space can therefore advantageously be used as insulation oract as an insulating air cushion. Heat transfer in the interior can thus be dominated by free convection, which is significantly lower than forced convection at higher flow velocities. Overall, this advantageously results in significantly lower heating of the cooling fluid in the exterior space, improving cooling performance. Furthermore, a more homogeneous temperature distribution of the cooling fluid in the exterior space along the circumference can be achieved, allowing for even cooling of the interior housing.

[0016] One embodiment provides that the separating device forms the openings, wherein the openings are each fluidically connected to the cooling lines of the inner housing via a respective tube element. In particular, the openings can be formed on the outer side of the separating device. The tube element can in particular be formed through the separating device. Furthermore, the tube element can in particular be formed through the interior. In particular, the tube element can lead through the inner wall of the annular channel or through the outer wall of the turbine housing and open into the cooling line. The interior of the tube element, in which the cooling fluid can be guided, can in particular be fluidically separated from the interior by the wall of the tube element.The tubular element thus advantageously ensures that the cooling fluid can flow from the exterior directly into the cooling lines without the cooling fluid flowing into the interior. Rather, the flowing cooling fluid is fluidically shielded from the interior by the tubular element. This advantageously preserves the insulating air cushion of the interior, improving the cooling effect and the homogeneity of the temperature distribution in the circumferential direction.

[0017] The opening can, in particular, be a through-hole through the separating device, wherein the tubular element has a hole on the outer side at its edge, in particular, welded to it. The outer wall of the turbine housing can also have a hole to which the tubular element has a hole at its edge, in particular, welded.

[0018] One embodiment provides that at least a portion of the outer wall of the turbine housing forms the radially inner inner wall of the annular channel. In other words, at least the portion of the outer wall of the turbine housing simultaneously corresponds to the inner wall of the annular channel. A separate inner wall of the annular channel can thus advantageously be dispensed with, thus saving material and weight. In particular, the annular channel can have a U-shaped profile prior to assembly with the turbine housing, wherein the edges of the U-shaped profile can be connected directly to the outer wall, in particular joined, preferably welded.

[0019] One embodiment provides that the separating device has at least one metal sheet which extends essentially in the circumferential direction and in the axial direction of the turbine module. In the radial direction, the at least one metal sheet extends much less than the extents of the metal sheet in the circumferential direction and in the axial direction. The metal sheet can be understood to be a rolled metal whose width in the axial direction and length in the circumferential direction are much greater than its thickness in the radial direction. The width of the at least one metal sheet can essentially correspond to a width of the annular channel. The metal sheet can in particular be shaped such that it has a rounding in the circumferential direction, such that a distance of the at least one metal sheet from the inner wall of the annular channel or outer wall of the turbine housing is essentially constant over the entire length in the circumferential direction.The at least one sheet may have stiffeners to increase stability, in particular corresponding linear recesses or beads, bulges, flat recesses, or the like. The at least one sheet may be flanged or beveled at the axially front and rear edges.

[0020] One embodiment provides for the separating device to be a sheet metal element. The sheet metal element can be joined, in particular welded, at its respective ends, so that the sheet metal element assumes a closed, cylindrical shape.

[0021] One embodiment provides for spacer elements of the turbine module to be provided, which space the at least one sheet metal element from the outer wall of the turbine housing. The spacer elements can, in particular, be formed at specific points in order to keep heat conduction as low as possible. The spacer elements can also be elongated, in particular rail-shaped. The spacer elements can advantageously ensure that the separating device is, at least almost completely, not in direct contact with the outer wall of the turbine housing, so that the interior space can be formed. Preferably, radially inner spacer elements can be provided between the outer wall of the turbine housing and the inner side of the separating device.For example, these spacer elements can extend radially to a height of a few millimeters, so that the separating device is spaced a few millimeters from the outer wall of the turbine housing. In particular, additional radially outer spacer elements can also be formed between the outer wall of the annular channel and the outer side of the separating device.

[0022] One embodiment provides for the spacer elements to be formed integrally with the separating device. In particular, the spacer elements can be formed from the sheet metal, for example, in the form of point-like protrusions in the respective sheet metal, or in the form of scalloped rails. Such spacer elements can be manufactured particularly easily. Furthermore, the spacer elements do not first have to be firmly connected to the respective sheet metal, thus eliminating the need for a joining step.

[0023] Alternatively, it can be provided that the spacer elements are formed integrally with the outer wall of the turbine housing, for example as punctiform or elongated elevations.

[0024] One embodiment provides for the separating device to be segmented into a plurality of sheets in the circumferential direction. In other words, each sheet does not extend over the entire length in the circumferential direction, but only over a partial area in the circumferential direction. In particular, the plurality of sheets are each formed in the shape of a circular arc, with the plurality of sheets together forming the circle.

[0025] Preferably, adjacent sheets are arranged so as to overlap one another at their distal ends. The respective two distal ends of a sheet are opposite one another in the circumferential direction, with one edge of each end extending in the axial direction. Overlapping can be understood to mean that a distal end of a first sheet lies above or below a distal end of a second sheet adjacent to the first sheet, with above being understood to mean radially outside and below being understood to mean radially inside. The adjacent sheets can preferably contact one another in the overlap region so that no cooling fluid can flow through the overlap region from the outside into the interior. In particular, it can be provided that a first distal end of a sheet lies above and an opposite, second distal end of the same sheet lies below.Overall, the overlaps of the separating device are thus arranged in a quasi-step-like manner in the circumferential direction. One advantage of the overlapping arrangement of adjacent sheets is that the sheets can expand or contract in the circumferential direction due to thermal interactions, whereby the overlap area becomes larger or smaller. This advantageously prevents stresses in the sheets.

[0026] One embodiment provides that each sheet of the plurality of sheets is firmly connected to the outer wall of the turbine housing at its distal, radially outwardly overlapping end region by means of at least one first spacer element. In particular, the sheet is firmly connected to the turbine housing by means of the first spacer elements, maintaining an expansion distance adjacent to the overlap region. Preferably, the first spacer elements can thus be formed as protrusions that are recessed in the circumferential direction. The first spacer elements can, for example, be welded to the sheet and / or to the outer wall.

[0027] One embodiment provides that each sheet of the plurality of sheets is slidably connected to the outer wall of the turbine housing in the circumferential direction at least at its distal, radially inwardly overlapping end region by means of at least one second spacer element. This advantageously ensures that the inwardly overlapping end region can expand or contract due to thermal interaction, with the sheet sliding relative to the outer wall. The second spacer elements can be either firmly connected to the outer wall and loosely connected to the sheet, or firmly connected to the sheet and loosely connected to the outer wall.

[0028] The combination of the fixed, outer end region and the loose, inner end region results in the technical effect that the sheet metal can be securely held at both ends. The loose, inner end region can advantageously be secured radially outward by the fixed, outer end region of the adjacent sheet metal.

[0029] One embodiment provides that the separating device is spaced from an axial front wall of the annular channel and / or from an axial rear wall of the annular channel. This ensures that the exterior and interior spaces are not completely fluidically sealed off from one another, thus allowing at least pressure equalization between the exterior and interior spaces. Preferably, only a gap is provided between the front or rear wall and the axial, circumferential edges of the separating device, so that cooling fluid exchange can be kept as low as possible and thus only a minimal heat exchange can take place. In particular, the gap should be designed such that it is small enough to prevent excessive ventilation of the interior space, and large enough so that axial expansion of the separating device does not lead to interaction with the front and / or rear walls.

[0030] A second aspect of the invention provides a compressor module for a turbomachine. The compressor module comprises at least one compressor housing with an annular outer wall and an inner housing, as well as an annular channel for distributing a thermal fluid in a circumferential direction of the compressor module. The annular channel sits directly on the outer wall on the outside. The annular channel has at least one inlet for the thermal fluid to flow into the annular channel, as well as openings for the thermal fluid to flow out into heat lines of the inner housing. It is provided that a separating device running in the circumferential direction is provided within the annular channel, which divides the annular channel into a radially inner interior space and a radially outer exterior space.

[0031] The use of the separating device in the annular channel advantageously ensures that the outer space of the annular channel is better shielded from the outer wall of the compressor housing. This advantageously ensures that heat flow from the heat fluid into the outer space is significantly reduced. When the heat fluid is distributed circumferentially, significantly less heat exchange occurs, so that temperature gradients in the circumferential direction can be reduced. Thus, virtually uniform temperature can be ensured in the annular channel, allowing the inner housing to be evenly heated all around by the heat fluid. This advantageously allows for even defrosting of inlet guide vanes (IGVs), for example.

[0032] The inner housing to be heated can, in particular, have static elements to which, for example, moving and rotating components can be attached or mounted. The inner housing can preferably have struts that extend in a radial direction from the outer wall to a core or to a compressor center frame (CCF) of the compressor module and firmly connect the outer wall to the CCF. The struts can, in particular, be evenly distributed in the circumferential direction. The heat pipes can, in particular, be formed within the inner housing. The heat pipes can preferably be cavities within the struts and within the CCF, which guide the heating fluid in a targeted manner. The struts can correspond to the IGVs.

[0033] The annular channel can be arranged, in particular, in an axial direction of the compressor housing at the same height as the inner housing, in particular as the struts. In particular, the annular channel sits directly on the outer wall. The annular channel, also referred to as an air box, for example, is designed to guide the thermal fluid within its interior and to distribute the thermal fluid preferably evenly in the circumferential direction. The annular channel can be formed completely circumferentially, so that the annular channel can assume a closed ring shape. The annular channel can, in particular, have a certain width in the axial direction and a certain height in the radial direction, wherein a length of the ring can essentially correspond to a circumference of the outer wall at this axial position. The annular channel can, in particular, have walls within which the thermal fluid can be guided.The cross-section of the annular channel can preferably be substantially rectangular, or, for example, semicircular or semi-elliptical. The annular channel can preferably have a radially inner inner wall, a radially outer outer wall, an axially forward front wall, and an axially rearward rear wall.

[0034] The annular channel can, in particular, have precisely one inlet through which the heat fluid can flow into the annular channel. The heat fluid can, in particular, be air, which can be tapped from the high-pressure compressor (HDV) and supplied to the annular channel through the inlet. The inlet is preferably arranged in a radially outer region of the annular channel or arranged in the exterior space, so that heat flow to the compressor from a heat fluid supply line, which can be connected to the inlet, is low.

[0035] The thermal fluid flowing into the annular channel through the inlet can, in turn, flow out of the annular channel through the openings. In particular, exactly one opening or multiple openings can be provided for each strut of the inner housing. In particular, each opening can fluidically connect the annular channel to a respective heat line of the strut or to the heat lines of the inner housing. The opening can, in particular, extend through the inner wall of the annular channel or the outer wall of the compressor housing to the heat line.

[0036] Cold ambient air can be arranged to flow directly inside the outer wall of the compressor housing, thereby cooling the outer wall. The outer wall thus limits the flow of cold ambient air radially outward. No ambient air flows directly outside the cooled outer wall, where the annular duct rests.

[0037] The separating device within the annular channel preferably runs completely in the circumferential direction, so that the separating device is also essentially annular or cylindrical. The separating device essentially spatially separates the annular channel into the interior and exterior spaces. However, it is not necessary for the interior and exterior spaces to be fluidically separated from one another by the separating device. The exterior space is formed in particular essentially by the outer wall of the annular channel, an outer section of the front and rear walls, and an outer side of the separating device, and the interior space is formed in particular essentially by the inner wall of the annular channel, an inner section of the front and rear walls, and an inner side of the separating device, so that the exterior space is essentially shielded from the interior or the outer wall of the compressor housing by the separating device.Preferably, the volume of the exterior space can be significantly larger than the volume of the interior space. In particular, the height of the exterior space in the radial direction can also be significantly larger than the height of the interior space.

[0038] One embodiment of the compressor module provides that the outer space of the annular channel has the at least one inlet and the openings. Because the thermal fluid flows from the inlet into the outer space, is distributed within the outer space, in particular in the circumferential direction, and flows out from the outer space again through the openings of the outer space, it can advantageously be ensured that thermal fluid does not flow into the inner space or only flows to a small extent. In particular, the flow velocity of the thermal fluid in the inner space is thus zero or at least almost zero or is significantly reduced compared to the flow velocity of the thermal fluid in the outer space. Due to the reduced flow velocity of the thermal fluid in the inner space, only a low level of heat transfer or reduced heat convection can take place from the inner side of the separating device to the outer wall of the compressor housing.The thermal fluid in the interior can thus advantageously act as insulation or as an insulating air cushion. Heat transfer in the interior can thus be dominated by free convection, which is significantly lower than forced convection at higher flow velocities. Overall, this advantageously results in significantly less cooling of the thermal fluid in the exterior space, improving thermal performance. Furthermore, a more homogeneous temperature distribution of the thermal fluid in the exterior space in the circumferential direction can be achieved, allowing for even heating of the interior housing.

[0039] One embodiment of the compressor module provides that the separating device forms the openings, wherein the openings are each fluidically connected to the heat lines of the inner housing via a respective tube element. In particular, the openings can be formed on the outer side of the separating device. The tube element can in particular be formed through the separating device. Furthermore, the tube element can in particular be formed through the interior space. In particular, the tube element can lead through the inner wall of the annular channel or through the outer wall of the compressor housing and open into the heat line. The interior of the tube element, in which the heat fluid can be guided, can in particular be fluidically separated from the interior space by the wall of the tube element.The tubular element thus advantageously ensures that the thermal fluid can flow from the exterior directly into the heat pipes without the thermal fluid flowing into the interior. Rather, the flowing thermal fluid is fluidically shielded from the interior by the tubular element. This advantageously preserves the insulating air cushion of the interior, improving the thermal effect and the homogeneity of the temperature distribution in the circumferential direction.

[0040] The opening can, in particular, be a through-hole through the separating device, wherein the tubular element has a hole on the outer side at its edge, in particular, welded to it. The outer wall of the compressor housing can also have a hole to which the tubular element has a hole at its edge, in particular, welded.

[0041] One embodiment of the compressor module provides that at least a portion of the outer wall of the compressor housing forms the radially inner inner wall of the annular channel. In other words, at least the portion of the outer wall of the compressor housing simultaneously corresponds to the inner wall of the annular channel. A separate inner wall of the annular channel can thus advantageously be dispensed with, thus saving material and weight. In particular, the annular channel can have a U-shaped profile prior to assembly with the compressor housing, wherein the edges of the U-shaped profile can be connected directly to the outer wall, in particular joined, preferably welded.

[0042] One embodiment of the compressor module provides that the separating device has at least one metal sheet which extends essentially in the circumferential direction and in the axial direction of the compressor module. In the radial direction, the at least one metal sheet extends much less than the extents of the metal sheet in the circumferential direction and in the axial direction. The metal sheet can be understood to be a rolled metal whose width in the axial direction and length in the circumferential direction are much greater than its thickness in the radial direction. The width of the at least one metal sheet can essentially correspond to a width of the annular channel. The metal sheet can in particular be shaped such that it has a rounding in the circumferential direction, such that a distance of the at least one metal sheet from the inner wall of the annular channel or outer wall of the compressor housing is essentially constant over the entire length in the circumferential direction.The at least one sheet may have stiffeners to increase stability, in particular corresponding linear recesses or beads, bulges, flat recesses, or the like. The at least one sheet may be flanged or beveled at the axially front and rear edges.

[0043] One embodiment of the compressor module provides for the separating device to be a sheet metal element. The sheet metal element can be joined, in particular welded, at its respective ends, so that the sheet metal element assumes a closed, cylindrical shape.

[0044] One embodiment of the compressor module provides for spacer elements of the compressor module, which space the at least one metal sheet from the outer wall of the compressor housing. The spacer elements can be formed, in particular, at specific points in order to keep heat conduction as low as possible. The spacer elements can also be elongated, in particular rail-shaped. The spacer elements can advantageously ensure that the separating device is, at least almost completely, not in direct contact with the outer wall of the compressor housing, so that the interior space can be formed. Preferably, radially inner spacer elements can be provided between the outer wall of the compressor housing and the inner side of the separating device.For example, these spacer elements can extend radially to a height of a few millimeters, so that the separating device is spaced a few millimeters from the outer wall of the compressor housing. In particular, additional radially outer spacer elements can also be formed between the outer wall of the annular channel and the outer side of the separating device.

[0045] One embodiment of the compressor module provides for the spacer elements to be formed integrally with the separating device. In particular, the spacer elements can be formed from the sheet metal, for example, in the form of point-like protrusions in the respective sheet metal, or in the form of scalloped rails. Such spacer elements can be manufactured particularly easily. Furthermore, the spacer elements do not first have to be firmly connected to the respective sheet metal, thus eliminating the need for a joining step.

[0046] Alternatively, it can be provided that the spacer elements are formed integrally with the outer wall of the compressor housing, for example as punctual or elongated elevations.

[0047] One embodiment of the compressor module provides that the separating device is segmented into a plurality of plates in the circumferential direction. In other words, each plate does not extend over the entire length in the circumferential direction, but only over a partial area in the circumferential direction. In particular, the plurality of plates are each formed in the shape of a circular arc, with the plurality of plates together forming the circle.

[0048] Preferably, adjacent sheets are arranged so as to overlap one another at their distal ends. The respective two distal ends of a sheet are opposite one another in the circumferential direction, with one edge of each end extending in the axial direction. Overlapping can be understood to mean that a distal end of a first sheet lies above or below a distal end of a second sheet adjacent to the first sheet, with above being understood to mean radially outside and below being understood to mean radially inside. The adjacent sheets can preferably contact one another in the overlap region so that no thermal fluid can flow through the overlap region from the outside into the interior. In particular, it can be provided that a first distal end of a sheet lies above and an opposite, second distal end of the same sheet lies below.Overall, the overlaps of the separating device are thus arranged in a quasi-step-like manner in the circumferential direction. One advantage of the overlapping arrangement of adjacent sheets is that the sheets can expand or contract in the circumferential direction due to thermal interactions, whereby the overlap area becomes larger or smaller. This advantageously prevents stresses in the sheets.

[0049] One embodiment of the compressor module provides that each sheet of the plurality of sheets is firmly connected to the outer wall of the compressor housing at its distal, radially outwardly overlapping end region by means of at least one first spacer element. In particular, the sheet is firmly connected to the compressor housing by means of the first spacer elements, maintaining an expansion distance adjacent to the overlap region. Preferably, the first spacer elements can thus be formed as protrusions that are recessed in the circumferential direction. The first spacer elements can, for example, be welded to the sheet and / or to the outer wall.

[0050] One embodiment of the compressor module provides that each sheet of the plurality of sheets is slidably connected to the outer wall of the compressor housing in the circumferential direction at least at its distal, radially inwardly overlapping end region by means of at least one second spacer element. This advantageously ensures that the inwardly overlapping end region can expand or contract due to thermal interaction, with the sheet sliding relative to the outer wall. The second spacer elements can be either firmly connected to the outer wall and loosely connected to the sheet, or firmly connected to the sheet and loosely connected to the outer wall.

[0051] The combination of the fixed, outer end region and the loose, inner end region results in the technical effect that the sheet metal can be securely held at both ends. The loose, inner end region can advantageously be secured radially outward by the fixed, outer end region of the adjacent sheet metal.

[0052] One embodiment of the compressor module provides that the separating device is spaced apart from an axial front wall of the annular channel and / or from an axial rear wall of the annular channel. This ensures that the exterior and interior spaces are not completely fluidically sealed off from one another, thus allowing at least pressure equalization between the exterior and interior spaces. Preferably, only a gap is provided between the front wall or rear wall and the axial, circumferential edges of the separating device, so that heat fluid exchange can be kept as low as possible and thus only a minimal heat exchange can take place.In particular, the gap must be designed in such a way that it is small enough to prevent strong ventilation of the interior space and, on the other hand, large enough to prevent any expansion of the separating device in the axial direction from leading to interaction with the front and / or rear wall.

[0053] A further aspect of the invention provides a turbomachine, in particular an aircraft gas turbine. The turbomachine comprises at least one turbine module according to the invention and / or one compressor module according to the invention.

[0054] Further features of the invention emerge from the claims, the figures, and the description of the figures. The features and combinations of features mentioned above in the description, as well as the features and combinations of features mentioned below in the description of the figures and / or shown in the figures, can be encompassed by the invention not only in the respective combination specified, but also in other combinations. In particular, the invention can also encompass embodiments and combinations of features that do not have all the features of an originally formulated claim. Furthermore, the invention can encompass embodiments and combinations of features that go beyond or deviate from the combinations of features set out in the backreferences to the claims. In this case: FIG. 1 a schematic representation of an embodiment of a turbine module or compressor module of a turbomachine according to the invention in a longitudinal section; FIG: 2 a schematic representation of an embodiment of a turbine module or compressor module of a turbomachine according to the invention in a cross section; FIG. 3 a schematic representation of an embodiment of a section of a separating device with several sheets.

[0055] The invention is explained in more detail below using specific embodiments and associated schematic drawings. In the figures, identical or functionally equivalent elements may be provided with the same reference numerals. The description of identical or functionally equivalent elements may not necessarily be repeated for different figures.

[0056] The following are the FIG. 1 and the FIG. 2 described together, whereby the FIG. 1 a schematic representation of an embodiment of a turbine module 100 according to the invention of a turbomachine 1 in a longitudinal section, and the FIG. 2 in a cross-section. For simplification, the circumferential direction (U) is shown as straight, although in reality it may be circular or ring-shaped.

[0057] The turbine module 100 may comprise at least one turbine housing 101 with an annular outer wall 2 and an inner housing 3. The turbine module 100 further comprises an annular channel 4 for distributing a cooling fluid in and / or counter to a circumferential direction U ( FIG. 2 ) of the turbine module 100. The annular channel 4 is seated radially on the outside of the outer wall 2, viewed in the radial direction R, which is directed outwards from a center of the turbine module. The annular channel 4 has at least one inlet 5 for the cooling fluid to flow into the annular channel 4, as well as openings 6 for the cooling fluid to flow out into cooling lines 7 of the inner housing 3. The arrow 28 can in particular represent a main flow of the turbomachine 1, which can flow radially inside the outer wall of the outer wall 2 and can heat this, as well as the inner housing 3, in particular by forced convection.

[0058] Within the annular channel 4, a separating device 8 can be provided which runs in the circumferential direction U and divides the annular channel 4 into a radially inner interior space 9 and a radially outer exterior space 10. In particular, the exterior space 11 can have at least one inlet 5 and the openings 6. For example, the separating device 8 forms the openings 6 radially on the outside, i.e. directed towards the exterior space, wherein the openings 6 are each fluidically connected to the cooling lines 7 of the inner housing 3 via a respective tube element 11. The arrows 29 can in particular indicate the flow directions of the cooling fluid, which can flow from the inlet 5 into the annular channel 4, is preferably distributed in the circumferential direction and flows out of the annular channel 4 again through the openings 6, as well as flowing into the cooling lines 7.

[0059] It can be provided that at least a portion of the outer wall 2 of the turbine housing 101 forms a radially inner inner wall 12 of the annular channel 4.

[0060] For example, the separating device 8 can be designed as a metal sheet 13, 14, 15, which can extend, for example, in a ring shape around the outer wall 2 of the turbine housing 101, i.e., essentially in the circumferential direction U and in an axial direction X of the turbine module 100. However, the separating device 8 can preferably have a plurality of metal sheets 13, 14, 15. In particular, the separating device 8 can be spaced from an axial front wall 26 of the annular channel 4 and / or from an axial rear wall 27 of the annular channel 104. In particular, a gap can be provided here such that pressure equalization can take place between the interior space 9 and the exterior space 10, but preferably no ventilation of the interior space with the cooling fluid.

[0061] The turbine module 100 can have spacer elements 16, 17 between the outer wall 2 of the turbine housing 101 and the inner wall 12 of the annular channel 4, which space the at least one sheet 13, 14, 15 from the outer wall 2 and the inner wall 12, respectively. For example, the spacer elements 16, 17 can be formed integrally with the separating device 8, i.e., for example, joined to the separating device 8, in particular welded, or formed from the separating device 8.

[0062] The FIG. 1 and FIG. 2 The embodiment of the turbine module 100 shown can also correspond to an embodiment of a compressor module 200 according to the invention, wherein the associated description can be read as adapted accordingly to the compressor module 200. In particular, the terms "turbine housing 101" should be replaced by "compressor housing 201," and "cooling fluid" by "heating fluid." The outer wall 2 and the inner housing 3 of the compressor housing 201 can be forced convectively cooled, in particular by the main flow 28 of the turbomachine 1.

[0063] In FIG. 3is a schematic representation of an embodiment of a section of a separating device 8 of a turbine module 100 or a compressor module 200 with a plurality of sheets 13, 14, 15, in particular an underside of the turbomachine 1. The separating device 8 can be segmented into the plurality of sheets 13, 14, 15, in particular in the circumferential direction U. The first sheet 13, which is only shown in sections, can be overlapped at its first distal end 18 (in the circumferential direction U) with a second distal end 20 of the sheet 14 adjacent in the circumferential direction U. The overlapping ends 18, 20 can be mounted movable or sliding relative to one another, in particular in the circumferential direction U, so that the sheets 13, 14, 15 can expand or contract in the circumferential direction as a result of heat input.

[0064] The first sheet 13 can be connected to a distal, radially inwardly overlapping end region 24 of the first sheet 13, which can be directly adjacent to the overlapping ends 18, 20, by means of a second spacer element 17, slidingly connected to the outer wall 2 of the turbine housing 1 or to the inner wall 12 in the circumferential direction U. The second spacer element 17 can be connected either integrally to the first sheet 13 or to the wall 2, 12.

[0065] The second sheet 14 adjacent to the first sheet 13 can be firmly connected to the outer wall 2 of the turbine housing 1 or to the inner wall 12 in the circumferential direction U by a first spacer element 16 at a distal, radially outwardly overlapping end region 22 of the second sheet 14, which can adjoin the overlapping ends 18, 20 directly, in particular welded to the outer wall via the first spacer element 16. As a result, the second sheet is fixed to the end region 22 in the axial direction X, the radial direction R, and the circumferential direction U.

[0066] A position of the first sheet 13 in the end region 24 can thus be fixed radially inward by the second spacer element 17 and radially outward by the overlapping end 18.

[0067] The sheets 17, 18, 19 can also have further, second spacer elements 17, as shown purely schematically in the center of the second sheet 14.

[0068] A radial fixation of a distal, radially inwardly overlapping end 25 of the second sheet 17 can be provided corresponding to the end 24 in connection with an adjacent, third sheet 15, wherein a distal, radially inwardly overlapping end region 25 of the second sheet can be slidably connected to the wall 2, 12 by means of the second spacer element 17, and a distal, radially outwardly overlapping end region 23 of the third sheet 15 can be firmly connected to the wall 2, 12 via the first spacer element, so that the second, distal end 21 of the third sheet 23, which overlaps with the first distal end 19 of the second sheet 14, can be fixed radially outwardly.

[0069] Overall, the examples show how a separating device 8 (heat shield) can be provided for an anti-icing annular duct 4 or cooling fluid annular duct 4. The annular duct 4 or air box can sit directly on the turbine housing 101 or compressor housing 201. An inner side of the annular duct 4 sees, in particular, the bleed air temperature of the cooling fluid or the heating fluid. The outer walls of the annular duct can see either the nacelle conditions or the annulus conditions of the main flow 29. Due to the significant temperature difference between the bleed air and the annulus as well as the high heat transfer coefficients (driven by the air velocity in the air box and the annulus), the greatest heat loss can occur via the outer wall 2. To insulate the outer wall and retain thermal energy in the bleed air for as long as possible, a separating device 4, for example a shield, can be mounted above or radially outside the outer wall 2.This allows an interior space 9 to be created, in particular as an intermediate cavity, in which the air velocity can be almost zero (free convection conditions), so that the heat transfer between the main flow 28 and the outer wall 2 can be significantly reduced, and thus the heat exchange between the main flow 2 and the outer wall 2.

[0070] The metal sheets 13, 14, 15 of the separating device can be attached (welded) at specific points, e.g., to a first spacer element 17, for example, a protrusion recessed in the circumferential direction U, in order to minimize heat conduction. The separating device 8 can be segmented into metal sheets 13, 14, 15, with overlapping joints. The separating device 8 can be designed and mounted such that thermal expansion (in the axial X and circumferential direction U) cannot lead to interaction with the front wall 26 and / or the rear wall (air box walls). The distances between the metal sheets 13, 14, 15 and the surrounding annular channel 4 should preferably be designed to be small at the same time to prevent excessive ventilation of the intermediate cavity. List of reference symbols:

[0071] 1 Turbomachine 2 Outer wall 3 Inner casing 4 Annular channel 5 Inlet 6 Openings 7 Cooling lines 8 Separator 9 Interior 10 Exterior 11 Tube element 12 Inner wall 13 First sheet 14 Second sheet 15 Third sheet 16 First spacer elements 17 Second spacer elements 18 First distal end of the first sheet 19 First distal end of the second sheet 20 Second distal end of the second sheet 21 Second distal end of the third sheet 22 Distal, radially outward overlapping end region of the second sheet 23 Distal, radially outward overlapping end region of the third sheet 24 Distal, radially inward overlapping end region of the first sheet 25 Distal, radially inward overlapping end region of the second sheet 26 Axial front wall of the annular channel 27 Axial rear wall of the annular channel 28 Main flow 29Fluid flow 100Turbine module 101Turbine housing 200Compressor module 201Compressor housing RRadial direction UCircumferential direction XAxial direction

Claims

1. Turbine module (100) for a turbomachine (1), comprising - a turbine housing (101) with an annular outer wall (2) and an inner housing (3), and - an annular channel (4) for distributing a cooling fluid in a circumferential direction (U) of the turbine module (100), wherein the annular channel (4) - sits on the outside of the outer wall (2), - has at least one inlet (5) for the cooling fluid to flow into the annular channel (4), and - has openings (6) for the cooling fluid to flow out into cooling lines (7) of the inner housing (3), characterized in that a separating device (8) extending in the circumferential direction (U) is provided within the annular channel (4) and divides the annular channel (4) into a radially inner interior space (9) and a radially outer exterior space (10).

2. Turbine module (100) according to claim 1, characterized in thatthe outer space (11) of the annular channel (4) has the at least one inlet (5) and the openings (6), wherein in particular the separating device (8) forms the openings (6) and the openings (6) are fluidically connected to the cooling lines (7) of the inner housing (3) via a respective tube element (11) and / or wherein at least a section of the outer wall (2) of the turbine housing (101) forms a radially inner inner wall (12) of the annular channel (4).

3. Turbine module (100) according to one of the preceding claims, characterized in thatthe separating device (8) has at least one metal sheet (13, 14, 15) which extends substantially in the circumferential direction (U) and in an axial direction (X) of the turbine module (100), wherein in particular spacer elements (16, 17) are provided which space the at least one metal sheet (13, 14, 15) from the outer wall (2) of the turbine housing (101), wherein preferably the spacer elements (16, 17) are formed integrally with the separating device (8) and further preferably the separating device (8) is segmented in the circumferential direction (U) into a plurality of metal sheets (13, 14, 15), wherein adjacent metal sheets (13, 14, 15) are arranged overlapping one another at their distal ends (18, 19, 20, 21).

4. Turbine module (100) according to claim 3, characterized in thatin each case one sheet (13, 14, 15) of the plurality of sheets (13, 14, 15) is firmly connected at its distal, radially outwardly overlapping end region (22, 23) by means of at least one first spacer element (16) to the outer wall (2) of the turbine housing (101), wherein in particular in each case one sheet (13, 14, 15) of the plurality of sheets (13, 14, 15) is slidably connected at least at its distal, radially inwardly overlapping end region (24, 25) by means of at least one second spacer element (17) to the outer wall (2) of the turbine housing (1) in the circumferential direction (U).

5. Turbine module (100) according to one of the preceding claims, characterized in that the separating device (8) is spaced from an axial front wall (26) of the annular channel (4) and / or from an axial rear wall (27) of the annular channel (104).

6. Compressor module (200) for a turbomachine (1), comprising - a compressor housing (201) with an annular outer wall (2) and an inner housing (3), and - an annular channel (4) for distributing a thermal fluid in a circumferential direction (U) of the compressor module (200), wherein the annular channel (4) - sits on the outside of the outer wall (2), - has at least one inlet (5) for the thermal fluid to flow into the annular channel (4), and - has openings (6) for the thermal fluid to flow out into heat lines of the inner housing (3), characterized in that a separating device (8) extending in the circumferential direction (U) is provided within the annular channel (4) and divides the annular channel (4) into a radially inner interior space (9) and a radially outer exterior space (10).

7. Compressor module (200) according to claim 6, characterized in thatthe outer space (10) of the annular channel (4) has the at least one inlet (5) and the openings (6), wherein in particular the separating device (8) forms the openings (6), wherein the openings (6) in this case are fluidically connected to the cooling lines (7) of the inner housing (3) via a respective tube element (11).

8. Compressor module (200) according to one of claims 6 to 7, characterized in that at least a section of the outer wall (2) of the compressor housing (201) forms a radially inner inner wall (12) of the annular channel (4), wherein the separating device (8) preferably has at least one sheet (13, 14, 15) which extends substantially in the circumferential direction (U) and in an axial direction (X) of the compressor module (200).

9. Compressor module (200) according to claim 8, characterized in thatSpacer elements (16, 17) are provided which space the at least one metal sheet (13, 14, 15) from the outer wall (2) of the compressor housing (201), wherein in particular the spacer elements (16, 17) are formed integrally with the separating device (8) and / or the separating device (8) is segmented in the circumferential direction (U) into a plurality of metal sheets (13, 14, 15), wherein adjacent metal sheets (13, 14, 15) are arranged overlapping one another at their distal ends (18, 19, 20, 21) and / or a metal sheet (13, 14, 15) of the plurality of metal sheets (13, 14, 15) is firmly connected to the outer wall (2) of the compressor housing (201) at its distal, radially outwardly overlapping end region (22, 23) by means of at least one first spacer element (16). wherein further preferably one sheet (13, 14, 15) of the plurality of sheets (13, 14, 15) is provided at least at its distal, radially inwardly overlapping end region (24,25) is slidably connected to the outer wall (2) of the compressor housing (201) in the circumferential direction (U) by means of at least one second spacer element (17).

10. Turbomachine (1), in particular an aircraft engine, comprising a turbine module (100) according to one of claims 1 to 5, and / or a compressor module (200) according to one of claims 6 to 9.

Images