• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a burst protection device (1) for a gas turbine engine, in particular a gas turbine turbomachine, comprising a turbine wheel (21) rotatably mounted in the turbine housing (20), the storm protection device (1) being mounted about a central axis (1). A) is annular in the circumferential direction and box-shaped in a cross-sectional direction to surround the turbine housing (20) in the region of the turbine wheel (21), wherein the burst protection device (1) from a plurality of circumferentially juxtaposed wall portions (10, 11, 12) is formed and at least one axially extending axial wall portion (10) and at least one radially extending radial wall portion (12) are indirectly interconnected via an intermediate wall portion (11) therebetween, and the intermediate wall portion (11) slopes and / or axially in at least a portion thereof bent against above the orientation of the axial wall section (10) and the radial wall section (12).
    公开号:CH714609A2
    申请号:CH00012/19
    申请日:2019-01-08
    公开日:2019-07-31
    发明作者:Braun Steffen；Albrecht Daniel；Denkel Harald；Weihard Stefan；Haas Bernd；Niebuhr Johannes；Spatz Urban
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description: The invention relates to a burst protection device for a gas turbine engine according to the preamble of claim 1 with a turbine housing, which comprises a turbine wheel rotatably arranged in the turbine housing. The invention also relates to an internal combustion engine with such a gas turbine engine, and to a gas turbine engine with such a burst protection device.
    A turbocharger, also called turbocharger (ATL) or colloquially turbo, is an optional assembly of an internal combustion engine and is used to increase performance or efficiency.
    An exhaust gas turbocharger consists of a compressor and a turbine, which are connected to one another by a common shaft. The turbine, driven by the exhaust gases from the internal combustion engine, supplies the drive energy for the compressor. In most cases, radial compressors and centripetal turbines are used for turbochargers.
    The basic principle is to use part of the energy of the engine exhaust gas to increase the pressure in the intake system and thereby to convey more outside air into the cylinder than with the uncharged engine, which leads to an increase in efficiency. Turbochargers can therefore use the pressure (accumulation charge) and the kinetic energy of the exhaust gases (impact charge). With an additional charge air cooler, a higher working pressure can be achieved in the cylinder at the same temperature.
    Conceptually, the compressor and the turbine have an air guide spiral, in the turbine this is used to guide the exhaust gases and in the compressor to transport the intake air for the engine.
    Currently known high-performance turbomachines, such as exhaust gas turbochargers of supercharged internal combustion engines, pose a high risk to their surroundings in the event of a technical failure of the rotating parts of the turbocharger. Particularly when operating in situations in which people can be in the immediate vicinity of the turbomachine , it must be ensured that in the event of a failure, ie When bursting, all parts are caught safely and completely and cannot injure anyone.
    In order to prevent the penetration of fragments through the outer wall of the turbocharger and thus the risk to people or damage to neighboring machine parts, the turbochargers were provided in the area radially outside the turbine wheel with relatively thick walls in the turbine housing in the past. However, these solutions have a number of disadvantages, e.g. the considerable additional weight of the housing and the risk of blowholes due to the poor castability of such a turbine housing. In addition, such a thickened housing heats up differently, which can lead to thermal cracks.
    DE 4 223 496 A1 discloses a device for reducing the kinetic energy of bursting parts for machines rotating at high speed. This device, which is arranged in the interior of an axial turbine, consists of several interconnected protective rings, between each of which a crumple zone made of ductile material is formed. However, such a solution is not suitable for radial turbines because, due to their radial gas entry, no burst protection devices can be used in the radial region of the turbine.
    From US 4 875 837 A a multi-layer burst protection is known, in which a heat-insulating material is introduced in an iron plate, and which is attached at a distance to a turbine housing and to a spiral part of the turbine housing. A disadvantage of the burst protection described there, however, is the fact that this burst protection only surrounds a 120 ° angular range of the spiral part of the housing and is therefore partially open.
    From the document DE 19 640 654 A1 a further burst protection is known, which is provided outside a gas inlet housing of a radial turbine for a turbocharger, which is designed as a spiral sheet metal shell and is detachably connected to the gas inlet housing by means of several screws.
    Furthermore, solutions are known in which bent sheets are arranged as a burst protection around the spiral, which, however, are structurally simple in order to reduce the manufacturing costs, but which have only limited strength and rigidity and are also related to behavior behave unfavorably in response to the natural frequencies occurring during operation.
    It is therefore an object of the present invention to avoid said disadvantages and to provide an improved, easy-to-manufacture and safe burst protection device for radial turbines of turbochargers and thus to further improve the safety of turbochargers, with adverse effects due to the natural frequencies occurring during operation being reduced should be.
    [0013] This object is achieved by the combination of features according to patent claim 1.
    A basic idea of the invention is to design a burst protection device in such a way that it is shaped around the spiral of the turbine and has a specifically shaped structure consisting of several sections which run radially circumferentially and at least one axial section and at least one axial section Radial section extending in the radial direction are connected to one another via an intermediate obliquely arranged intermediate section, which preferably slopes and / or bends in at least one partial area relative to the orientation of the axial section and the radial section.
    CH 714 609 A2 According to the invention, therefore, a burst protection device for a gas turbine engine, in particular a gas radial turbine machine, is provided with a turbine housing, which comprises a turbine wheel rotatably arranged in the turbine housing, the burst protection device being ring-shaped around a central axis in the circumferential direction and box-shaped in a cross-sectional direction is designed to encompass the turbine housing in the region of the turbine wheel, wherein the burst protection device is further formed from a plurality of wall sections arranged next to one another in the circumferential direction and at least one axial wall section extending in the axial direction and at least one radial wall section extending in the radial direction are indirectly connected to one another via an intermediate intermediate wall section and the intermediate wall section in the axial direction at least in a partial area obliquely and / or bent with respect to the orientation of the axis alwandabschnittes and the radial wall section.
    It is advantageous that the burst protection device is also formed in one piece from a plurality of wall sections arranged side by side in the circumferential direction.
    It when two radial wall sections extend in the radial direction and are indirectly connected to the axial wall section via a respective intermediate wall section is particularly advantageous. The burst protection device thus preferably has two radial wall sections extending in the radial direction, between which the axial wall section is located. As a result, viewed in cross section through the burst protection device (in the case of a cut transverse to the circumferential direction), an inwardly open box shape for receiving a spiral-shaped exhaust gas duct of the turbine, in the center of which the turbine wheel sits.
    In a preferred embodiment of the invention it is provided that the two radial wall sections extending in the radial direction are each oriented relative to the axial wall section at an angle of approximately 90 ° and the intermediate wall sections with respect to the axial wall section at an angle a with respect to its axial extent and / or run curved.
    It is also advantageous if the burst protection device is formed in one piece from one or more sheet metal parts which have a high dielectric strength.
    In a further advantageous embodiment of the invention it is provided that the intermediate wall sections are designed as wall sections which run essentially flat in one direction and are at a positive or negative angle a between 30 ° and 60 °, preferably between 40 °, relative to the axial direction and 50 ° and are particularly preferably oriented at an angle of 45 °. In any case, angles on the order of 90 ° (as is partially known from the prior art) are undesirable, since this shape has proven to be unfavorable for various properties of the burst protection device, such as have shown strength, vibration behavior, rigidity, etc.
    Another aspect of the present invention relates to a gas turbine engine, in particular a gas radial turbine engine, having a turbine housing which has a turbine wheel which is rotatably arranged in the turbine housing, and a burst protection device, as described above, which is arranged around the turbine housing.
    A preferred embodiment provides that the turbine housing forms a spiral gas duct, which has an exhaust gas supply on one side and the burst protection device at least partially encompasses the gas duct.
    A further advantageous embodiment provides that the axial wall section of the burst protection device extends in the axial direction over a central partial section of the spiral gas guide channel, while the front and rear partial sections not covered by the axial wall section are at least partially covered by the obliquely oriented intermediate wall sections. As a result, the burst protection can be guided along the surface contour of the gas duct and thus of the turbine housing with a small distance, which has a favorable effect on the reduction of the kinetic energy of burst splinters in the event of a burst.
    It is advantageously provided that a first radial wall section is arranged in front of a front side wall section and a second radial wall section behind a rear side wall section of the gas guide channel, and the front and rear radial wall sections are each connected to the axial wall section via oblique or curved intermediate wall sections.
    Another aspect of the present invention relates to an internal combustion engine with a gas turbine engine as described above.
    Other advantageous developments of the invention are characterized in the dependent claims or are shown below together with the description of the preferred embodiment of the invention with reference to the figures. Show it:
    Fig. 1 shows a first embodiment of a bursting device according to the present invention and
    Fig. 2 shows an alternative embodiment of a bursting device according to the present invention.
    The invention is described in more detail below with reference to FIGS. 1 and 2, the same reference symbols indicating the same structural and / or functional features.
    CH 714 609 A2 [0028] FIGS. 1 and 2 show in a sectional view two exemplary embodiments of an alternative design of a burst protection device 1 in a mounting situation around a turbocharger (shown in a partial view).
    Shown in each case is the turbine housing 20 of a gas turbine engine with a turbine wheel 21 which is rotatably arranged in the turbine housing 20 and which is fastened on the turbocharger axis 23 by means of fastening means 24. The turbine housing 20 comprises a spiral gas guide channel 22 for guiding the exhaust gas flow, which has an exhaust gas supply, not shown, on one side.
    Furthermore, a burst protection device 1 is shown in both embodiments, which at least partially encompasses the spiral turbine housing in the region of the gas guide duct 22.
    The burst protection device 1 is shaped such that it is ring-shaped in the circumferential direction and box-shaped in a cross-sectional direction around the central axis A, which runs through the turbocharger axis 23, around the turbine housing 20, in the region of the turbine wheel 21 embrace.
    In the two embodiments of FIGS. 1 and 2, the burst protection device 1 is in each case formed in one piece from a puncture-resistant sheet metal from a plurality of wall sections 10, 11, 12 arranged next to one another in the circumferential direction, one in each case in the axial direction (ie in the direction of the turbocharger axis 23 ) extending axial wall section 10 of the burst protection device 1 extends in a cover-shaped manner around the turbine housing 20. The respective wall sections 10, 11, 12 are designed as flat wall sections. However, the partition section 11 may e.g. also run as a curved section 11 ', as shown by way of example in FIG. 1 with the thinner curved line.
    In the upper exemplary embodiment according to FIG. 1, a radial wall section 12 which also extends in the radial direction (i.e. transversely to the axial direction) is indirectly connected to the axial wall section 10 via an inclined intermediate wall section 11.
    In the lower embodiment according to FIG. 2, two radial wall sections 12 extending in the radial direction are indirectly connected to the axial wall section 10 via an inclined intermediate wall section 11.
    The intermediate wall sections 11 are arranged obliquely with respect to the axial wall section 10 at an angle a of approximately 55 ° with respect to its axial extent. Alternatively, as shown in FIG. 2 with the left or right angle a, they can each be at a positive or negative angle a between 30 ° and 60 °, preferably between 40 ° and 50 ° and particularly preferably at an angle be oriented from 45 °. The angles can be the same or different, depending on how you want to adapt the burst protection device 1 along the outer contour of the turbine housing 20. As already explained, the shape of the intermediate wall section 11 can also be a combination of a linear and curved shape in order to carry out a specific adaptation.
    The axial wall section 10 of the burst protection device 1 runs in the embodiment according to FIG. 2 in the axial direction over a central partial section 22m of the spiral gas guide channel 22, while the partial sections not covered by the axial wall section 10 are at least partially covered by the obliquely oriented intermediate wall sections 11. The first (left) radial wall section 12 is arranged in front of a front side wall section 22v and the second (right) radial wall section 12 behind a rear side wall section 22h of the gas routing channel 22, the front and rear radial wall section 12 each having the axial wall section 10 over the previously described inclined intermediate wall sections 11 are connected.
    The embodiment of the invention is not limited to the preferred exemplary embodiments specified above. Rather, a number of variants are conceivable which make use of the solution shown, even in the case of fundamentally different types.
    权利要求:
    Claims (11)
    [1]
    claims
    1. Burst protection device (1) for a gas turbine machine, in particular a gas radial turbine machine, with a turbine housing (20) which comprises a turbine wheel (21) rotatably arranged in the turbine housing (20), the burst protection device (1) about a central axis (A) is ring-shaped in the circumferential direction and box-shaped in a cross-sectional direction in order to encompass the turbine housing (20) in the region of the turbine wheel (21), the burst protection device (1) being formed from a plurality of wall sections (10, 11, 12) arranged next to one another in the circumferential direction and at least one axial wall section (10) extending in the axial direction and at least one radial wall section (12) extending in the radial direction are indirectly connected to one another via an intermediate intermediate wall section (11) and the intermediate wall section (11) in the axial direction at least in a partial area obliquely and / or curved relative to one another the orientation de s axial wall section (10) and the radial wall section (12).
    [2]
    2. Burst protection device (1) according to claim 1, characterized in that the burst protection device (1) is formed in one piece from a plurality of wall sections (10, 11, 12) arranged side by side in the circumferential direction
    CH 714 609 A2
    [3]
    3. burst protection device (1) according to claim 1 or 2, characterized in that the burst protection device (1) has two radial wall sections (12) extending between which the axial wall section (10) is located.
    [4]
    4. Burst protection device (1) according to claim 3, characterized in that the two radial wall sections (12) extending in the radial direction are each connected to the axial wall section (10) and the intermediate wall sections (11) with respect to the axial wall section (10) at an angle a the axial extent of which is oblique and / or curved.
    [5]
    5. burst protection device (1) according to one of the preceding claims 1 to 3, characterized in that the burst protection device (1) is formed in one piece from one or more sheet metal parts.
    [6]
    6. Burst protection device (1) according to one of the preceding claims 1 to 4, characterized in that the intermediate wall sections (11) are designed as flat wall sections, which are preferred over the axial direction at a positive or negative angle a between 30 ° and 60 ° are oriented between 40 ° and 50 ° and particularly preferably at an angle of 45 °.
    [7]
    7. Gas turbine machine, in particular gas radial turbine machine, with a turbine housing (20) which has a turbine wheel (21) rotatably arranged in the turbine housing (20), and a burst protection device (1) according to one of claims 1 to 6, which is arranged around the turbine housing is.
    [8]
    8. Gas turbine engine according to claim 7, characterized in that the turbine housing (20) forms a spiral gas duct (22) which has an exhaust gas supply on one side and the burst protection device (1) at least partially surrounds the gas duct (22).
    [9]
    9. Gas turbine machine according to claim 8, characterized in that the axial wall section (10) of the burst protection device (1) extends in the axial direction over a central section (22m) of the spiral gas duct (22), while those not covered by the axial wall section (10) Sections are at least partially covered by the diagonally oriented intermediate wall sections (11).
    [10]
    10. Gas turbine engine according to claim 8 or 9, characterized in that a first radial wall section (12) in front of a front side wall section (22v) and a second radial wall section (12) behind a rear side wall section (22h) of the gas duct (22) is arranged and the front and the rear radial wall section (12) is in each case connected to the axial wall section (10) via oblique or curved intermediate wall sections (11).
    [11]
    11. Internal combustion engine with a gas turbine engine according to one of claims 7 to 10.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2092174B1|2015-09-09|Turbocharger
    DE102009049841B4|2015-01-15|Gas turbine engine and internal combustion engine
    EP0834646A1|1998-04-08|Containment device for the radial turbine of a turbocharger
    DE2031612A1|1971-04-15|Multi-stage axial compressor with an air discharge system as an intermediate stage
    EP3450717B1|2021-10-06|Fan wheel
    DE102004023270A1|2005-01-20|An axial flow fan
    EP2627907A1|2013-08-21|Side channel blower, in particular a secondary air blower for an internal combustion machine
    EP2382393B1|2017-09-06|Side channel blower, in particular secondary air blower for an internal combustion engine
    DE3407946A1|1985-09-05|DEVICE FOR PREVENTING THE SPREADING OF TITANIUM FIRE IN TURBO MACHINES, ESPECIALLY GAS TURBINE OR. GAS TURBINE JET ENGINES
    DE4223496A1|1994-01-20|Reducing kinetic energy of bursting parts in turbines - involves crumple zone between inner and outer rings set between housing and rotor to absorb energy and contain fractured parts
    DE102016002722A1|2016-09-15|Turbocharger turbine nozzle and safety structure
    CH714609A2|2019-07-31|Bursting device for a gas turbine machine.
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    EP0806547B1|2001-10-10|Axial turbine for turbochargers
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    DE112016005630T5|2018-08-30|OUTBOARD PART FOR A RADIAL COMPRESSOR
    EP3056690B1|2019-08-21|Centrifugal compressor, exhaust gas turbocharger and corresponding method for operating a centrifugal compressor
    DE102016102732A1|2017-08-17|Mixed-flow turbine wheel of an exhaust gas turbocharger and exhaust gas turbine with such a turbine wheel
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    同族专利:
    公开号 | 公开日
    KR20190088408A|2019-07-26|
    JP2019124222A|2019-07-25|
    CN110056399A|2019-07-26|
    US10738647B2|2020-08-11|
    DE102018101066A1|2019-07-18|
    US20190218931A1|2019-07-18|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018101066.4A|DE102018101066A1|2018-01-18|2018-01-18|Bursting device for a gas turbine machine|
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