DE4223496A1 - 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 - Google Patents

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

Info

Publication number
DE4223496A1
DE4223496A1 DE19924223496 DE4223496A DE4223496A1 DE 4223496 A1 DE4223496 A1 DE 4223496A1 DE 19924223496 DE19924223496 DE 19924223496 DE 4223496 A DE4223496 A DE 4223496A DE 4223496 A1 DE4223496 A1 DE 4223496A1
Authority
DE
Germany
Prior art keywords
housing
parts
crumple zone
bursting
turbines
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
DE19924223496
Other languages
German (de)
Inventor
Josef Baettig
Werner Graf
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ABB Schweiz Holding AG
ABB AB
Original Assignee
Asea Brown Boveri AG Switzerland
Asea Brown Boveri AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Asea Brown Boveri AG Switzerland, Asea Brown Boveri AB filed Critical Asea Brown Boveri AG Switzerland
Priority to DE19924223496 priority Critical patent/DE4223496A1/en
Publication of DE4223496A1 publication Critical patent/DE4223496A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16P—SAFETY DEVICES IN GENERAL; SAFETY DEVICES FOR PRESSES
    • F16P7/00—Emergency devices preventing damage to a machine or apparatus

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Supercharger (AREA)

Abstract

The device is formed from an inner ring (6), outer ring (7) and interposed crumple zone (8) all connected together eg by welding and made from ductile material. The ring device is fixed at a slight distance from the circumferential plane between the housing wall and the rotating parts. The device can be cast on the housing and additional supports can be attached to the device itself or to the housing. Side brake elements can be additionally fitted on the hub of the rotating parts. USE/ADVANTAGE - The parts of the turbine which may become fractured through centrifugal forces cannot penetrate through the housing to cause damage.

Description

Technisches GebietTechnical field

Die Erfindung betrifft eine Vorrichtung zum Reduzieren der kinetischen Energie von berstenden Teilen in Maschinen, die mit hoher Geschwindigkeit umlaufen, insbesondere in Turbinen.The invention relates to a device for reducing the kinetic energy of bursting parts in machines that Rotate at high speed, especially in turbines.

Stand der TechnikState of the art

Im Turbinenbau ist es bekannt, daß die umlaufenden Teile der Turbine unter Umständen außerordentlich hohen Fliehkräften ausgesetzt werden. Diese Fliehkräfte können einen Bruch oder ein Zerbersten der Turbine bewirken. Auf Grund der hohen ki­ netischen Energie ist es möglich, daß die Bruchstücke das Gehäuse durchschlagen. Herausfliegende Bauteile können Men­ schen gefährden und benachbarte Maschinenteile beschädigen.In turbine construction, it is known that the rotating parts of the Turbine may have extremely high centrifugal forces get abandoned. These centrifugal forces can break or cause the turbine to rupture. Due to the high ki netic energy, it is possible that the fragments Break through the housing. Parts that fly out can men endanger people and damage neighboring machine parts.

Es sind Fangvorrichtungen zum Auffangen der Bruchstücke eines Rotors bekannt, der bei hoher Arbeitsgeschwindigkeit zer­ birst. Diese Fangvorrichtungen weisen in der Umlaufebene des Maschinenteils einen Schutzring auf, der im Querschnitt U- förmig ausgebildet ist, wobei die offene Seite dieser Ringnut nach innen weist und der Schutzring durch Reibung im Maschi­ nengehäuse drehbar gelagert ist. Die Ringnut kann auch eine dünne Abdeckung zur Erhöhung des Wirkungsgrades der Turbine haben oder sie kann mit einem Futter aus verhältnismäßig weichem Material, z. B. Aluminium gefüllt sein. Diese bekann­ ten Schutzringe haben den Nachteil, daß sie nur einen Teil der kinetische Energie des berstenden Teiles infolge Reibung vernichten. Wird das Futter des Schutzringes nicht dick genug ausgeführt, können die Bruchstücke mit der Innenfläche des Schutzringes in Berührung kommen, zurückprallen und aus dem Gehäuse herausgeschleudert werden.They are safety devices to catch the fragments of one Known rotor that zer at high working speed bursts. These safety devices point in the orbital plane of the Part of the machine on a protective ring is shaped, the open side of this annular groove points inwards and the protective ring due to friction in the machine nengehäuse is rotatably mounted. The ring groove can also be a thin cover to increase the efficiency of the turbine  have or they can be proportionate with a feed soft material, e.g. B. Aluminum filled. This got th guard rings have the disadvantage that they are only a part the kinetic energy of the bursting part due to friction destroy. If the lining of the guard ring is not thick enough executed, the fragments with the inner surface of the Guard ring come into contact, rebound and out of the Housing are thrown out.

Darstellung der ErfindungPresentation of the invention

Die Erfindung versucht all diese Nachteile zu vermeiden. Es ist deshalb Aufgabe der Erfindung, eine Vorrichtung (Berst­ schutz) zu schaffen, welche bei geringem Montageaufwand die kinetische Energie von berstenden Teilen in rotierenden Systemen, insbesondere Turbinen, reduziert und damit die Gefährdung von Menschen und Material durch unkontrolliert herausfliegende berstende Bauteile beseitigt wird.The invention tries to avoid all these disadvantages. It is therefore the object of the invention, a device (burst protection) to create, which with little installation effort kinetic energy of bursting parts in rotating Systems, especially turbines, reduced and thus the Danger to people and material from uncontrolled flying out bursting components is eliminated.

Erfindungsgemäß wird dies dadurch erreicht, daß die Vor­ richtung aus mindestens einem inneren Ring, mindestens einem äußeren Ring und einer sich zwischen innerem Ring und äußerem Ring befindenden Knautschzone, welche miteinander ver­ bunden sind, gebildet wird, aus duktilem Material besteht und in geringem Abstand von der Umlaufebene zwischen der Gehäuse­ wand und den rotierenden Teilen befestigt ist.According to the invention this is achieved in that the front direction from at least one inner ring, at least one outer ring and one between inner ring and outer Ring located crumple zone, which ver are bound, is formed, consists of ductile material and at a short distance from the circumferential plane between the housing wall and the rotating parts is attached.

Die Vorteile der Erfindung liegen darin, daß ein Durchschla­ gen des Gehäuses von berstenden Bauteilen verhindert wird und damit die Gefahr einer Verletzung von Menschen bzw. einer Be­ schädigung von Material beseitigt wird.The advantages of the invention are that a penetration against the housing from bursting components and thus the risk of injury to people or injury damage to material is eliminated.

Es ist besonders zweckmäßig, wenn die Ringe und und die Knautschzone miteinander durch Schweißen zusammengefügt sind. It is particularly useful if the rings and and the Crumple zone joined together by welding are.  

Ferner ist es im Hinblick auf einen geringen Montageaufwand vorteilhaft, wenn die Vorrichtung direkt am Gehäuse ange­ bracht, z. B. angegossen ist.Furthermore, it is in view of a low installation effort advantageous if the device is directly on the housing brings, e.g. B. is cast on.

Schließlich wird mit Vorteil eine zusätzliche Abstützung, beispielsweise in Form von Nocken, an der Vorrichtung selbst oder am Gehäuse angebracht. Dadurch können die Abmaße des Berstschutzes verringert werden. Finally, additional support is advantageous, for example in the form of cams on the device itself or attached to the housing. This allows the dimensions of the Burst protection can be reduced.

Außerdem ist es zweckmäßig, wenn zusätzlich an der Nabe der rotierenden Teile seitliche Bremselemente angebracht sind, weil dadurch die auf den Berstschutz auftreffende kinetische Energie reduziert wird.In addition, it is useful if the rotating parts are attached to the side brake elements, because this means the kinetic impact on the burst protection Energy is reduced.

Kurze Beschreibung der ZeichnungBrief description of the drawing

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung anhand eines Abgasturboladers für Brennkraftmaschinen dar­ gestellt. Es zeigen:In the drawing is an embodiment of the invention using an exhaust gas turbocharger for internal combustion engines posed. Show it:

Fig. 1 einen Teillängsschnitt des Abgasturboladers, Fig. 1 a partial longitudinal section of the exhaust turbocharger,

Fig. 2 einen Teilquerschnitt durch einen Berstschutz mit zwei äußeren Ringen, Fig. 2 is a partial cross section through a burst protection with two outer rings,

Fig. 3 einen Teilquerschnitt durch einen Berstschutz mit einem äußeren Ring. Fig. 3 shows a partial cross section through a burst protection with an outer ring.

Es sind nur die für das Verständnis der Erfindung wesentli­ chen Elemente gezeigt. Nicht dargestellt sind beispielsweise der Schalldämpfer, das Verdichterrad und der Diffusor.It is only essential for understanding the invention Chen elements shown. For example, are not shown the silencer, the compressor wheel and the diffuser.

Weg zur Ausführung der ErfindungWay of carrying out the invention

In Fig. 1 ist der Teillängsschnitt eines Abgasturboladers dargestellt. In einem Gehäuse 1 ist auf einer gemeinsamen Welle mit dem hier nicht abgebildeten Verdichter eine Ab­ gasturbine untergebracht. Am Gehäuse 1 sind Abstütznocken 3 angebracht. An der Nabe des Turbinenrotors 2 befinden sich seitliche Bremselemente 4. Zwischen dem Gehäuse 1 und der rotierenden Turbinenschaufel ist ein ringförmiger Berst­ schutz 5 aus hochlegiertem Cr-Ni-Stahl angeordnet.In Fig. 1 the partial longitudinal section of an exhaust gas turbocharger is shown. In a housing 1 , a gas turbine is housed on a common shaft with the compressor, not shown here. Support cams 3 are attached to the housing 1 . Lateral brake elements 4 are located on the hub of the turbine rotor 2 . Between the housing 1 and the rotating turbine blade, an annular burst protection 5 made of high-alloy Cr-Ni steel is arranged.

Der Berstschutz 5 besteht gemäß Fig. 2 aus einem inneren Ring 6 und zwei äußeren Ringen 7. Dazwischen befindet sich die Knautschzone 8. Die Ringe 6, 7 und die Knautschzone 8 wurden durch Schweißen zusammengefügt. Eine andere mögliche Ausführungsform des Berstschutzes ist in Fig. 3 dargestellt.According to FIG. 2, the burst protection 5 consists of an inner ring 6 and two outer rings 7 . The crumple zone 8 is located in between. The rings 6 , 7 and the crumple zone 8 were joined together by welding. Another possible embodiment of the burst protection is shown in FIG. 3.

Die Abgase des Motors strömen in das Innere des Abgasturbo­ laders ein, wobei sie sich im Düsenring 9 entspannen und an den Turbinenschaufeln Leistung abgeben. Danach gelangen sie durch das Gaseintrittsgehäuse und durch Abgasleitungen ins Freie. Die für den Betrieb des Motors nötige Luft gelangt durch einen Saugstutzen oder einen Filter-Schalldämpfer in das Verdichterrad, durchströmt den Diffusor und verläßt den Lader durch Druckstutzen am Luftaustrittsgehäuse.The exhaust gases of the engine flow into the interior of the turbocharger, whereby they relax in the nozzle ring 9 and give off power to the turbine blades. Then they get out through the gas inlet housing and through exhaust pipes. The air required to operate the engine enters the compressor wheel through a suction port or a filter silencer, flows through the diffuser and leaves the charger through pressure ports on the air outlet housing.

Bei bestimmten Betriebsbedingungen können Zustände eintreten, die dazu führen, daß die rotierenden Teile, z. B. die Turbi­ nenschaufeln, bersten und infolge der Fliehkraftwirkung nach außen geschleudert werden. Sie treffen dann mit hoher kine­ tischer Energie auf den zwischen dem Gehäuse 1 und dem Tur­ binenrotor 2 befestigten Berstschutz 5 auf. Der Berstschutz 5 wird deformiert. Dabei wird die kinetische Energie der ber­ stenden Teile reduziert, was dazu führt, daß die berstenden Teile nicht das Gehäuse 1 durchschlagen, sondern dort aufge­ fangen werden. Durch die am Gehäuse 1 angebrachten Abstütz­ nocken 3 wird eine Reduzierung der Abmasse des Berstschutzes 5 erreicht. Die sich an der Nabe der Turbinenrotors 2 befin­ denden seitlichen Bremselemente 4 reduzieren zusätzlich die kinetische Energie der berstenden Teile. Under certain operating conditions, conditions can occur which lead to the rotating parts, e.g. B. the turbine blades, burst and are thrown outwards due to the centrifugal force. They then meet with high kinetic energy on the burst protection 5 attached between the housing 1 and the turbine rotor 2 . The burst protection 5 is deformed. The kinetic energy of the overestimating parts is reduced, which means that the bursting parts do not break through the housing 1 , but are caught there. By the attached to the housing 1 support cam 3 , a reduction in the dimensions of the burst protection 5 is achieved. The lateral brake elements 4 located on the hub of the turbine rotor 2 additionally reduce the kinetic energy of the bursting parts.

Der Vorteil der Erfindung besteht darin, daß ein Heraus­ fliegen der Bauteile und damit eine Gefährdung von Menschen bzw. Material verhindert wird. Desweiteren wird durch den Einbau des Berstschutzes auch die Gefahr des Abprallens weitgehend eliminiert, so daß eine Gefährdung durch Quer­ schläger praktisch ausgeschlossen ist. Der zusätzliche Mon­ tageaufwand ist gering.The advantage of the invention is that an out fly the components and thus endanger people or material is prevented. Furthermore, the Installation of the burst protection also the risk of ricocheting largely eliminated, so that a risk from cross racket is practically excluded. The additional month daily expenditure is low.

BezugszeichenlisteReference list

1 Gehäuse
2 Turbinenrotor
3 Abstütznocken
4 Bremselement
5 Berstschutz
6 innerer Ring
7 äußerer Ring
8 Knautschzone
9 Düsenring 1 housing
2 turbine rotors
3 support cams
4 braking element
5 burst protection
6 inner ring
7 outer ring
8 crumple zone
9 nozzle ring

Claims (6)

1. Vorrichtung zum Reduzieren der kinetischen Energie von berstenden Teilen in rotierenden Maschinen, insbesonde­ re in Turbinen, in Form eines Schutzringes, dadurch ge­ kennzeichnet, daß diese aus mindestens einem inneren Ring (6), mindestens einem äußeren Ring (7) und einer sich zwischen innerem Ring (6) und äußerem Ring (7) be­ findenden Knautschzone (8), welche miteinander verbunden sind, gebildet wird, aus duktilem Material besteht und in geringem Abstand von der Umlaufebene zwischen der Ge­ häusewand und den rotierenden Teilen befestigt ist.1. Device for reducing the kinetic energy of bursting parts in rotating machines, in particular in turbines, in the form of a protective ring, characterized in that they consist of at least one inner ring ( 6 ), at least one outer ring ( 7 ) and one between the inner ring ( 6 ) and outer ring ( 7 ) be located crumple zone ( 8 ) which are connected to one another, is formed, is made of ductile material and is attached at a short distance from the circumferential plane between the housing wall and the rotating parts. 2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß diese direkt am Gehäuse (1) angebracht ist.2. Device according to claim 1, characterized in that it is attached directly to the housing ( 1 ). 3. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, daß diese am Gehäuse (1) angegossen ist.3. Device according to claim 2, characterized in that it is cast on the housing ( 1 ). 4. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Ringe (6) und (7) und die Knautschzone (8) miteinander verschweißt sind.4. The device according to claim 1, characterized in that the rings ( 6 ) and ( 7 ) and the crumple zone ( 8 ) are welded together. 5. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß zusätzlich Abstützungen (3) an der Vorrichtung selbst oder am Gehäuse (1) angebracht sind.5. The device according to claim 1, characterized in that additional supports ( 3 ) on the device itself or on the housing ( 1 ) are attached. 6. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß zusätzlich an der Nabe der rotierenden Teile seitliche Bremselemente (4) angebracht sind.6. The device according to claim 1, characterized in that lateral braking elements ( 4 ) are additionally attached to the hub of the rotating parts.
DE19924223496 1992-07-17 1992-07-17 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 Withdrawn DE4223496A1 (en)

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DE19924223496 DE4223496A1 (en) 1992-07-17 1992-07-17 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

Applications Claiming Priority (1)

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DE19924223496 DE4223496A1 (en) 1992-07-17 1992-07-17 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

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Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0718471A1 (en) * 1994-12-21 1996-06-26 Hispano-Suiza Containment ring for a turbomachine
EP0834646A1 (en) 1996-10-02 1998-04-08 Asea Brown Boveri AG Containment device for the radial turbine of a turbocharger
US5868553A (en) * 1996-05-08 1999-02-09 Asea Brown Boveri Ag Exhaust gas turbine of an exhaust gas turbocharger
US5934868A (en) * 1996-05-08 1999-08-10 Asea Brown Boveri Ag Axial turbine of an exhaust-gas turbocharger
EP1233190A1 (en) * 2001-02-20 2002-08-21 MAN B&W Diesel AG Turbomachine with radial-flow compressor impeller
EP1586745A1 (en) * 2004-04-13 2005-10-19 ABB Turbo Systems AG Compressor casing
DE102004027594A1 (en) * 2004-06-05 2005-12-29 Man B & W Diesel Ag Turbomachine with radially flowing compressor wheel
GB2447036A (en) * 2007-02-28 2008-09-03 Rolls Royce Plc A containment casing
FR2915511A1 (en) * 2007-04-27 2008-10-31 Snecma Sa Low pressure turbine for e.g. turbojet engine, of aircraft, has braking unit comprising upstream and downstream conical surfaces that are inclined at specific angle with respect to plane perpendicular to longitudinal axis of turbine
WO2009030197A1 (en) * 2007-09-07 2009-03-12 Mtu Aero Engines Gmbh Multilayer shielding ring for a flight driving mechanism
WO2015132616A1 (en) * 2014-03-07 2015-09-11 Cummins Ltd A turbine
US9200567B2 (en) 2009-07-23 2015-12-01 Cummins Turbo Technologies Limited Compressor, turbine and turbocharger
DE102018101066A1 (en) 2018-01-18 2019-07-18 Man Energy Solutions Se Bursting device for a gas turbine machine
EP1783343B1 (en) * 2005-11-07 2019-10-09 Garrett Transportation I Inc. Turbocharger containment shield
CN110410340A (en) * 2018-04-27 2019-11-05 曼恩能源方案有限公司 Turbocharger
DE102018114093A1 (en) 2018-06-13 2019-12-19 Man Energy Solutions Se Burst protection device for a gas turbine engine
DE102018129128A1 (en) 2018-11-20 2020-05-20 Man Energy Solutions Se Insert for a turbocharger
US10830050B2 (en) 2019-01-31 2020-11-10 General Electric Company Unitary body turbine shrouds including structural breakdown and collapsible features
US10927693B2 (en) 2019-01-31 2021-02-23 General Electric Company Unitary body turbine shroud for turbine systems
DE102011086452C5 (en) 2010-12-15 2023-03-16 Schaeffler Technologies AG & Co. KG Torque transmission device with burst protection

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Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0718471A1 (en) * 1994-12-21 1996-06-26 Hispano-Suiza Containment ring for a turbomachine
WO1996019641A1 (en) * 1994-12-21 1996-06-27 Societe Hispano Suiza Protective shield for a turbomachine
US5868553A (en) * 1996-05-08 1999-02-09 Asea Brown Boveri Ag Exhaust gas turbine of an exhaust gas turbocharger
US5934868A (en) * 1996-05-08 1999-08-10 Asea Brown Boveri Ag Axial turbine of an exhaust-gas turbocharger
EP0834646A1 (en) 1996-10-02 1998-04-08 Asea Brown Boveri AG Containment device for the radial turbine of a turbocharger
DE19640654A1 (en) * 1996-10-02 1998-04-09 Asea Brown Boveri Burst protection device for radial turbines of turbochargers
EP1233190A1 (en) * 2001-02-20 2002-08-21 MAN B&W Diesel AG Turbomachine with radial-flow compressor impeller
US6638007B2 (en) 2001-02-20 2003-10-28 Man B&W Diesel Aktiengesellschaft Turbomachine with radial-flow compressor impeller
KR100794974B1 (en) * 2001-02-20 2008-01-15 만 디젤 에스이 Turbomachine with radial-flow compressor impeller
EP1586745A1 (en) * 2004-04-13 2005-10-19 ABB Turbo Systems AG Compressor casing
CN100363595C (en) * 2004-04-13 2008-01-23 Abb涡轮***有限公司 Compressor casing
DE102004027594A1 (en) * 2004-06-05 2005-12-29 Man B & W Diesel Ag Turbomachine with radially flowing compressor wheel
DE102004027594B4 (en) * 2004-06-05 2006-06-29 Man B & W Diesel Ag Turbomachine with radially flowing compressor wheel
EP1783343B1 (en) * 2005-11-07 2019-10-09 Garrett Transportation I Inc. Turbocharger containment shield
GB2447036A (en) * 2007-02-28 2008-09-03 Rolls Royce Plc A containment casing
FR2915511A1 (en) * 2007-04-27 2008-10-31 Snecma Sa Low pressure turbine for e.g. turbojet engine, of aircraft, has braking unit comprising upstream and downstream conical surfaces that are inclined at specific angle with respect to plane perpendicular to longitudinal axis of turbine
WO2009030197A1 (en) * 2007-09-07 2009-03-12 Mtu Aero Engines Gmbh Multilayer shielding ring for a flight driving mechanism
US9200567B2 (en) 2009-07-23 2015-12-01 Cummins Turbo Technologies Limited Compressor, turbine and turbocharger
US10662806B2 (en) 2009-07-23 2020-05-26 Cummins Turbo Technologies Limited Compressor, turbine and turbocharger
DE102011086452C5 (en) 2010-12-15 2023-03-16 Schaeffler Technologies AG & Co. KG Torque transmission device with burst protection
WO2015132616A1 (en) * 2014-03-07 2015-09-11 Cummins Ltd A turbine
DE102018101066A1 (en) 2018-01-18 2019-07-18 Man Energy Solutions Se Bursting device for a gas turbine machine
US10738647B2 (en) 2018-01-18 2020-08-11 Man Energy Solutions Se Burst protection device for a gas turbo engine
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DE102018114093A1 (en) 2018-06-13 2019-12-19 Man Energy Solutions Se Burst protection device for a gas turbine engine
DE102018129128A1 (en) 2018-11-20 2020-05-20 Man Energy Solutions Se Insert for a turbocharger
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