EP2796668A2 - Casing section of a turbo engine compressor or turbo engine turbine stage - Google Patents

Casing section of a turbo engine compressor or turbo engine turbine stage Download PDF

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Publication number
EP2796668A2
EP2796668A2 EP14164186.0A EP14164186A EP2796668A2 EP 2796668 A2 EP2796668 A2 EP 2796668A2 EP 14164186 A EP14164186 A EP 14164186A EP 2796668 A2 EP2796668 A2 EP 2796668A2
Authority
EP
European Patent Office
Prior art keywords
webs
housing section
housing
section according
turbomachine
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.)
Granted
Application number
EP14164186.0A
Other languages
German (de)
French (fr)
Other versions
EP2796668B1 (en
EP2796668A3 (en
Inventor
Karl Maar
Thomas Hess
Petra Kufner
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.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2796668A2 publication Critical patent/EP2796668A2/en
Publication of EP2796668A3 publication Critical patent/EP2796668A3/en
Application granted granted Critical
Publication of EP2796668B1 publication Critical patent/EP2796668B1/en
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave

Definitions

  • the invention relates to a housing section of a turbomachine compressor or turbomachine turbine stage according to the preamble of claim 1 and to a turbomachine, in particular gas turbine, with such a housing section.
  • a housing portion encloses a flow space in which rotating blades are disposed.
  • the wall thickness of the housing portion can be increased, but this has the disadvantage that increases the weight of the housing portion.
  • the object of the invention is to provide a turbomachine compressor stage or a turbine engine stage which has sufficient safety with low weight.
  • a turbomachine compressor or turbomachine turbine stage has at least one housing section with a radially outer jacket.
  • the radially outer shell has a plurality of webs, which extend radially inwardly, wherein the webs are inclined to the radius.
  • the radially outer shell is in one embodiment, in particular in cross section, closed and formed like an annular ring.
  • the radially outer shell can be longitudinally divided and composed of two or more parts permanently or detachably.
  • the webs are materially connected to the radially outer jacket, in particular formed integrally therewith, in particular urgeformt.
  • An advantage of radially inwardly extending lands may be that the weight of the housing portion is not significantly increased, but at the same time it is ensured that abutment of blades or parts thereof will not result in excessive deformation the radially outer shell and thus the housing section leads. Additionally or alternatively, an advantage of the housing portion may be that it can be manufactured by an additive manufacturing method, wherein different materials can be used for the production of the housing portion. Additionally or alternatively, an advantage of such webs may be that the stiffness of the housing portion is positively influenced to transmit maximum loads.
  • a housing section of a turbomachine compressor stage or turbine engine stage is understood in particular to be a housing section which encloses one or more rotor blade stages of a turbomachine arranged one after the other in the flow direction.
  • the turbomachine compressor stage and / or turbine engine stage may be preceded by at least one vane stage and / or at least one vane stage downstream.
  • Turbomachinery compressor stage is understood in one embodiment that portion of the turbomachine, which exclusively compresses an air mass flow determined for a combustion chamber of the turbomachine.
  • a fan upstream of the turbomachine compressor stage may promote mass air flow and bypass flow.
  • a diameter ratio of the rotor blades to the stator blades may be greater than or equal to 0.5, in particular 0.75, preferably 0.85.
  • a radius is understood as meaning a direction from a longitudinal axis of the housing section to the radially outer jacket, the direction being perpendicular to the longitudinal axis.
  • the webs may be inclined axially. This means that the webs can extend along the longitudinal axis of the housing portion and perpendicular to this. Additionally or alternatively, the webs in the circumferential direction of the Housing section extend.
  • the webs are connected to an inner shell. Radially inwardly of the inner shell may be arranged a flow channel jacket which limits a flow space of the step. Similarly, the inner shell itself can limit the flow space of the stage and thus act as a flow channel jacket. Additionally or alternatively, the webs may be interconnected.
  • the webs may be formed in a cross section perpendicular to the web longitudinal axis circular or polygonal. In one embodiment, webs can define, in particular enclose, a cavity, which can be axially inclined analogously to the webs and can extend in the longitudinal direction.
  • One or more, defined by webs, in particular enclosed cavities communicate in one embodiment with a coolant, in particular cooling air inlet and / or a coolant, in particular cooling air outlet.
  • the coolant inlet and / or coolant outlet can each be provided in a housing shell, which can be axially upstream or downstream of the housing section of the turbomachine compressor or turbomachine turbine stage.
  • the housing shell may enclose at least one vane stage.
  • a defined by lands cavity communicates in one embodiment only with the coolant inlet and / or the coolant outlet. In one embodiment, the cavity does not communicate with a flow space in which, among other things, the blades and / or vanes are arranged and which is enclosed by the housing portion and the housing shells.
  • the cavities it is preferably possible to reduce or reduce a heat input into the housing section and thus to reduce the temperature of the housing section.
  • the cavity for the transfer of coolant, in particular cooling air, between the upstream and downstream housing shells can be used, which can also have a positive effect on the heat input into the housing section.
  • The, in particular interconnected, webs can form a lattice or honeycomb structure in cross section, in particular in a cross section perpendicular to the web longitudinal axis.
  • Another advantage of such a cavity defined by webs may consist in that a transport of coolant which is virtually free of leakage loss can be achieved between the housing shell arranged upstream and downstream of the housing section. Additionally or alternatively, a reduced number of components and thus a reduction of the possible wear points can be achieved.
  • the webs may be prefolded.
  • the webs may be prefolded such that they fold under load loading, such as due to abutment of a broken blade or part thereof, according to a predetermined folding characteristic.
  • Individual webs can be separated from each other by a cavity and / or not connected to each other.
  • individual webs in particular with an end remote from the radially outer jacket, can be connected to an inner jacket.
  • the webs can be pre-folded several times, in particular zigzag-like, convex and / or concave.
  • Prefolded webs may in particular have at least two sections which, preferably in one edge, merge into one another and are inclined in opposite directions axially and / or in the circumferential direction against the radius.
  • a stiffener In a cavity between webs, a stiffener may be arranged.
  • the stiffener may have a grid or honeycomb structure in cross-section. The stiffener may improve the stiffness of the housing portion upon impact of the blades or parts of these against the housing portion and counteract deformation of the housing portion.
  • the housing section described above may be part of a turbomachine, in particular a gas turbine. It is clear that the turbomachine can also have a plurality of housing sections described above.
  • housing portion 1 has a radially outer shell 10 and an inner shell 11.
  • the radially outer shell 10 is separated from the inner shell 11 by a cavity 13.
  • From the radially outer jacket 10 extend in the cavity 13, a plurality of webs 12 radially inwardly.
  • the webs 12 are connected at one end to the radially outer shell 10 and at the other end to the inner shell 11.
  • a flow channel jacket 16 is arranged, which defines a flow space 2.
  • blades 4 are arranged.
  • the housing portion 1 a plurality of axially offset from one another arranged guides 14 for (in Fig. 1 not shown) adjustable vanes.
  • the guides 14 are connected to the radially outer shell 10 and the inner shell 11 respectively integrally formed and with the flow channel jacket 16 form, material and / or frictionally connected.
  • the webs 12 are repeatedly prefolded and thus inclined to the radius, so that at a load stress on the housing portion 1, the webs 12 are folded according to a predetermined folding characteristic. In particular, a folding of the webs 12 takes place in the radial direction.
  • the webs 12 are arranged in the axial direction within the cavity 13 adjacent to each other and pre-folded several times zigzag.
  • FIG. 2 Fig. 3 shows a longitudinal section of a housing section 100 according to another embodiment of the present invention.
  • the housing portion 100 has a radially outer shell 10 from which a plurality of webs 120 extend radially inwardly, wherein the webs 120 are interconnected.
  • the webs 120 are inclined axially, wherein the webs 120 in the illustrated case obliquely to a longitudinal axis, not shown, of the housing portion 100 (horizontally in Fig. 2 ).
  • the interconnected webs 120 form a grid or honeycomb structure in a cross section perpendicular to the web longitudinal axis.
  • the in FIG. 3 shown housing section 100 has in addition to the in FIG. 2 shown housing portion 100 on an inner shell 11.
  • the webs 120 are connected to the radially outer shell 10.
  • FIG. 3 shown webs 120 enclose analogous to those in FIG. 2 illustrated webs 120 cavities, through the cooling air from a cooling air inlet (left in Fig. 3 ) to a cooling air outlet (right in Fig. 3 ), as in Fig. 3 indicated by flow arrows.
  • an inlet means 3 is provided, which extends radially inwardly.
  • the inlet means 3 can come into contact with a blade 4 and serves in particular to reduce an undesirable leakage flow between the blade 4 and the inner shell 11 of the housing portion 100.
  • the housing portion 100 is at its upstream side (left in FIG Fig. 3 ) is connected in the connecting portion 14 via a screw with a housing shell 200. Further, the housing portion 100 is at the downstream side thereof (right in FIG Fig. 3 ) connected via a further connecting portion 15 with a further housing shell 201.
  • the two housing shells 200, 201 may each enclose a stator vane not shown. In the connection of the further housing shell 201 with the housing portion 100 may be a positive connection.
  • the in FIG. 4 illustrated housing portion 100 ' differs from that in FIG. 3 illustrated housing portion 100 characterized in that no inner shell 10 is provided in this.
  • the inlet means 3 ' is formed integrally with the webs 120'. It is ensured that the inlet means is positioned so that it can come into contact with the blades 4 '.
  • the cooling air inlet opening is in the connecting section 14 and the cooling air outlet opening is provided in the further connecting section 15.
  • the cooling air inlet opening and the cooling air outlet opening communicate with a cooling air channel provided in the respective housing shell 200, 201.
  • cooling air flows through the cooling air inlet opening into the cavities of the webs and flows through them to the cooling air outlet opening.
  • cooling air can flow via the housing section 100 between two housing shells 200, 201 adjacent to the turbomachine in the longitudinal axis direction, the flow direction of the cooling air being illustrated by the arrows P in the figures.
  • the webs and the cooling air inlet opening and the cooling air outlet opening are formed such that the cooling air does not communicate with the flow space 2 of the turbomachine.

Abstract

Die Erfindung betrifft einen Gehäuseabschnitt einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe, der einen, insbesondere geschlossenen und kreisringartigen, radial äußeren Mantel aufweist. Der radial äußere Mantel weist radial nach innen erstreckende Stege auf, die gegen den Radius geneigt sind. Gasturbine mit einem zugehörigen Gehäuseabschnitt.The invention relates to a housing section of a turbomachinery compressor or turbomachine turbine stage, which has a, in particular closed and annular, radially outer jacket. The radially outer shell has radially inwardly extending webs which are inclined to the radius. Gas turbine with an associated housing section.

Description

Die Erfindung betrifft einen Gehäuseabschnitt einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe nach dem Oberbegriff des Anspruchs 1 sowie eine Turbomaschine, insbesondere Gasturbine, mit einem solchen Gehäuseabschnitt.The invention relates to a housing section of a turbomachine compressor or turbomachine turbine stage according to the preamble of claim 1 and to a turbomachine, in particular gas turbine, with such a housing section.

Bei einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe umschließt ein Gehäuseabschnitt einen Strömungsraum, in dem rotierende Laufschaufeln angeordnet sind. Im Betrieb der Turbomaschine besteht die Gefahr, dass die Laufschaufeln oder ein Teil von diesen bricht und mit hoher kinetischer Energie auf den Gehäuseabschnitt trifft. Aus Sicherheitsgründen ist es notwendig, dass eine Verformung des Gehäuseabschnitts minimiert wird. Hierzu kann die Wandstärke des Gehäuseabschnitts erhöht werden, was jedoch den Nachteil aufweist, dass sich das Gewicht des Gehäuseabschnitts erhöht.In a turbomachine compressor or turbomachine turbine stage, a housing portion encloses a flow space in which rotating blades are disposed. During operation of the turbomachine, there is a risk that the blades or a part of them breaks and hits the housing section with high kinetic energy. For safety reasons, it is necessary that deformation of the housing portion is minimized. For this purpose, the wall thickness of the housing portion can be increased, but this has the disadvantage that increases the weight of the housing portion.

Die Aufgabe der Erfindung besteht darin, eine Turbomaschinenverdichterstufe oder eine Turbomaschinenturbinenstufe bereitzustellen, die eine ausreichende Sicherheit bei geringem Gewicht aufweist.The object of the invention is to provide a turbomachine compressor stage or a turbine engine stage which has sufficient safety with low weight.

Die Aufgabe wird durch den Gegenstand des Anspruchs 1 gelöst. Vorteilhafte Ausgestaltungen der Erfindung sind Gegenstand der abhängigen Ansprüche.The object is solved by the subject matter of claim 1. Advantageous embodiments of the invention are the subject of the dependent claims.

Erfindungsgemäß weist eine Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe wenigstens einen Gehäuseabschnitt mit einem radial äußeren Mantel auf. Der radial äußere Mantel weist mehrere Stege auf, die sich radial nach innen erstrecken, wobei die Stege gegen den Radius geneigt sind. Der radial äußere Mantel ist in einer Ausführung, insbesondere im Querschnitt, geschlossen und kreisringartig ausgebildet. In einer Weiterbildung kann der radial äußere Mantel längsgeteilt und aus zwei oder mehreren Teilen dauerhaft oder lösbar zusammengesetzt sein. Die Stege sind in einer Ausführung stoffschlüssig mit dem radial äußeren Mantel verbunden, insbesondere integral mit diesem ausgebildet, insbesondere urgeformt.According to the invention, a turbomachine compressor or turbomachine turbine stage has at least one housing section with a radially outer jacket. The radially outer shell has a plurality of webs, which extend radially inwardly, wherein the webs are inclined to the radius. The radially outer shell is in one embodiment, in particular in cross section, closed and formed like an annular ring. In a further development, the radially outer shell can be longitudinally divided and composed of two or more parts permanently or detachably. In one embodiment, the webs are materially connected to the radially outer jacket, in particular formed integrally therewith, in particular urgeformt.

Ein Vorteil sich radial nach innen erstreckenden Stege kann darin bestehen, dass das Gewicht des Gehäuseabschnitts nicht signifikant erhöht, gleichzeitig jedoch sichergestellt wird, dass ein Anstoßen von Laufschaufeln oder Teilen von diesen zu keiner übermäßigen Verformung des radial äußeren Mantels und damit des Gehäuseabschnitts führt. Zusätzlich oder alternativ kann ein Vorteil des Gehäuseabschnitts darin bestehen, dass dieser durch ein Additive Manufacturing-Verfahren hergestellt werden kann, wobei zur Herstellung des Gehäuseabschnitts verschiedene Werkstoffe eingesetzt werden können. Zusätzlich oder alternativ kann ein Vorteil solcher Stege darin bestehen, dass die Steifigkeit des Gehäuseabschnitts zur Übertragung von Maximallasten positiv beeinflusst wird.An advantage of radially inwardly extending lands may be that the weight of the housing portion is not significantly increased, but at the same time it is ensured that abutment of blades or parts thereof will not result in excessive deformation the radially outer shell and thus the housing section leads. Additionally or alternatively, an advantage of the housing portion may be that it can be manufactured by an additive manufacturing method, wherein different materials can be used for the production of the housing portion. Additionally or alternatively, an advantage of such webs may be that the stiffness of the housing portion is positively influenced to transmit maximum loads.

Im Sinne der Erfindung wird als Gehäuseabschnitt einer Turbomaschinenverdichterstufe- oder Turbomaschinenturbinenstufe insbesondere ein Gehäuseabschnitt verstanden, der eine oder mehrere, in Strömungsrichtung nacheinander angeordnete Laufschaufelstufen einer Turbomaschine umschließt. Der Turbomaschinenverdichterstufe und/oder Turbomaschinenturbinenstufe kann wenigstens eine Leitschaufelstufe vorgeschaltet und/oder wenigstens eine Leitschaufelstufe nachgeschaltet sein.For the purposes of the invention, a housing section of a turbomachine compressor stage or turbine engine stage is understood in particular to be a housing section which encloses one or more rotor blade stages of a turbomachine arranged one after the other in the flow direction. The turbomachine compressor stage and / or turbine engine stage may be preceded by at least one vane stage and / or at least one vane stage downstream.

Als Turbomaschinenverdichterstufe wird in einer Ausführung derjenige Abschnitt der Turbomaschine verstanden, der ausschließlich einen für eine Brennkammer der Turbomaschine bestimmten Luftmassenstrom verdichtet. Im Gegensatz dazu kann ein der Turbomaschinenverdichterstufe vorgeschalteter Fan den Luftmassenstrom und einen Bypasstrom fördern. Alternativ oder zusätzlich kann in einer Turbomaschinenverdichterstufe ein Durchmesserverhältnis der Laufschaufeln zu den Leitschaufeln größer oder gleich 0,5, insbesondere 0,75, vorzugsweise 0,85 sein.Turbomachinery compressor stage is understood in one embodiment that portion of the turbomachine, which exclusively compresses an air mass flow determined for a combustion chamber of the turbomachine. In contrast, a fan upstream of the turbomachine compressor stage may promote mass air flow and bypass flow. Alternatively or additionally, in a turbomachine compressor stage, a diameter ratio of the rotor blades to the stator blades may be greater than or equal to 0.5, in particular 0.75, preferably 0.85.

Im Sinne der Erfindung wird als Radius eine Richtung von einer Längsachse des Gehäuseabschnitts zu dem radial äußeren Mantel verstanden, wobei die Richtung senkrecht zu der Längsachse steht.For the purposes of the invention, a radius is understood as meaning a direction from a longitudinal axis of the housing section to the radially outer jacket, the direction being perpendicular to the longitudinal axis.

Durch die Neigung der Stege gegen den Radius kann im Gegensatz zu rein radialen Stegen eine vorteilhaftere Verformungscharakteristik der Stege bzw. des Gehäuseabschnitts dargestellt werden. Zusätzlich oder alternativ können gegen den Radius geneigte Stege, wie nachfolgend erläutert, zur Definition von Kühlpassagen dienen.Due to the inclination of the webs against the radius, in contrast to purely radial webs, a more advantageous deformation characteristic of the webs or of the housing section can be represented. Additionally or alternatively, webs inclined towards the radius, as explained below, can serve to define cooling passages.

In einer bevorzugten Ausführung können die Stege axial geneigt sein. Dies bedeutet, dass sich die Stege entlang der Längsachse des Gehäuseabschnitts und senkrecht zu dieser erstrecken können. Zusätzlich oder alternativ können die Stege sich in Umfangsrichtung des Gehäuseabschnitts erstrecken. In einer Ausführung sind die Stege mit einem Innenmantel verbunden. Radial innen von dem Innenmantel kann ein Strömungskanalmantel angeordnet sein, der einen Strömungsraum der Stufe begrenzt. Gleichermaßen kann der Innenmantel selbst den Strömungsraum der Stufe begrenzen und somit als Strömungskanalmantel fungieren. Zusätzlich oder alternativ können die Stege miteinander verbunden sein. Die Stege können in einem Querschnitt senkrecht zur Steglängsachse kreisförmig oder mehrkantig ausgebildet sein. Stege können in einer Ausführung jeweils einen Hohlraum definieren, insbesondere umschließen, der analog zu den Stegen axial geneigt sein und sich in Längsrichtung erstrecken kann.In a preferred embodiment, the webs may be inclined axially. This means that the webs can extend along the longitudinal axis of the housing portion and perpendicular to this. Additionally or alternatively, the webs in the circumferential direction of the Housing section extend. In one embodiment, the webs are connected to an inner shell. Radially inwardly of the inner shell may be arranged a flow channel jacket which limits a flow space of the step. Similarly, the inner shell itself can limit the flow space of the stage and thus act as a flow channel jacket. Additionally or alternatively, the webs may be interconnected. The webs may be formed in a cross section perpendicular to the web longitudinal axis circular or polygonal. In one embodiment, webs can define, in particular enclose, a cavity, which can be axially inclined analogously to the webs and can extend in the longitudinal direction.

Ein oder mehrere durch Stege definierte, insbesondere umschlossene Hohlräume kommunizieren in einer Ausführung mit einem Kühlmittel-, insbesondere Kühllufteintritt und/oder einem Kühlmittel-, insbesondere Kühlluftaustritt. Der Kühlmitteleintritt und/oder Kühlmittelaustritt kann jeweils in einer Gehäuseschale vorgesehen sein, die dem Gehäuseabschnitt der Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe axial vor- bzw. nachgeschaltet sein kann.One or more, defined by webs, in particular enclosed cavities communicate in one embodiment with a coolant, in particular cooling air inlet and / or a coolant, in particular cooling air outlet. The coolant inlet and / or coolant outlet can each be provided in a housing shell, which can be axially upstream or downstream of the housing section of the turbomachine compressor or turbomachine turbine stage.

Die Gehäuseschale kann wenigstens eine Leitschaufelstufe umschließen. Ein durch Stege definierter Hohlraum kommuniziert in einer Ausführung ausschließlich mit dem Kühlmitteleintritt und/oder dem Kühlmittelaustritt. In einer Ausführung kommuniziert der Hohlraum nicht mit einem Strömungsraum, in dem unter anderem die Laufschaufeln und/oder Leitschaufeln angeordnet sind und der durch den Gehäuseabschnitt und die Gehäuseschalen umschlossen wird.The housing shell may enclose at least one vane stage. A defined by lands cavity communicates in one embodiment only with the coolant inlet and / or the coolant outlet. In one embodiment, the cavity does not communicate with a flow space in which, among other things, the blades and / or vanes are arranged and which is enclosed by the housing portion and the housing shells.

Durch die Hohlräume ist es vorzugsweise möglich, einen Wärmeeintrag in den Gehäuseabschnitt zu verringern bzw. zu reduzieren und damit die Temperatur des Gehäuseabschnitts zu verringern. Dadurch ist es in einer Ausführung möglich, andere Werkstoffe für die Herstellung des Gehäuseabschnitts zu verwenden, die zu einer Gewichtsreduzierung des Gehäuseabschnitts führen können. Ferner kann der Hohlraum zum Transfer von Kühlmittel, insbesondere Kühlluft, zwischen den vor- und nachgeschalteten Gehäuseschalen genutzt werden, was sich ebenfalls positiv auf den Wärmeeintrag in den Gehäuseabschnitt auswirken kann. Die, insbesondere miteinander verbundenen, Stege können im Querschnitt, insbesondere in einem Querschnitt senkrecht zur Steglängsachse, eine Gitter-oder Wabenstruktur bilden. Dadurch lässt sich der zuvor erwähnte Wärmeeintrag auf besonders einfache Weise reduzieren und/oder der Transfer von Kühlmittel zwischen den Gehäuseschalen verbessern.Through the cavities, it is preferably possible to reduce or reduce a heat input into the housing section and thus to reduce the temperature of the housing section. This makes it possible in one embodiment to use other materials for the production of the housing portion, which can lead to a reduction in weight of the housing portion. Furthermore, the cavity for the transfer of coolant, in particular cooling air, between the upstream and downstream housing shells can be used, which can also have a positive effect on the heat input into the housing section. The, in particular interconnected, webs can form a lattice or honeycomb structure in cross section, in particular in a cross section perpendicular to the web longitudinal axis. As a result, the aforementioned heat input can be on reduce particularly simple way and / or improve the transfer of coolant between the housing shells.

Ein weiterer Vorteil eines solchen durch Stege definierten Hohlraums kann darin bestehen, dass ein nahezu leckageverlustfreier Transport von Kühlmittel zwischen der dem Gehäuseabschnitt vor- und nachgeschalteten Gehäuseschale erreicht werden kann. Zusätzlich oder alternativ kann eine verringerte Bauteilanzahl und damit eine Verringerung der möglichen Verschleißstellen erreicht werden.Another advantage of such a cavity defined by webs may consist in that a transport of coolant which is virtually free of leakage loss can be achieved between the housing shell arranged upstream and downstream of the housing section. Additionally or alternatively, a reduced number of components and thus a reduction of the possible wear points can be achieved.

Gemäß einem Aspekt der Erfindung können die Stege vorgefaltet sein. Die Stege können derart vorgefaltet sein, dass sich diese bei einer Lastbeanspruchung, wie beispielsweise aufgrund eines Anstoßens einer abgebrochenen Laufschaufel oder eines Teils davon, entsprechend einer vorgegebenen Faltungscharakteristik falten. Durch eine derartige Ausbildung der Stege kann sichergestellt werden, dass das Gewicht des Gehäuseabschnitts gering ist und dieser bei einem Anstoßen von Laufschaufeln oder Teilen gegen diesen nicht verformt. Die Stege dämpfen durch den Faltvorgang den Stoß und verhindern somit eine Beschädigung des Gehäuseabschnitts.According to one aspect of the invention, the webs may be prefolded. The webs may be prefolded such that they fold under load loading, such as due to abutment of a broken blade or part thereof, according to a predetermined folding characteristic. By such a design of the webs can be ensured that the weight of the housing portion is low and this does not deform at a bumping of blades or parts against this. The webs dampen the impact by the folding process and thus prevent damage to the housing section.

Einzelne Stege können durch einen Hohlraum voneinander getrennt und/oder nicht miteinander verbunden sein. Gleichermaßen können einzelne Stege, insbesondere mit einem von dem radial äußeren Mantel entfernten Ende, mit einem Innenmantel verbunden sein.Individual webs can be separated from each other by a cavity and / or not connected to each other. Likewise, individual webs, in particular with an end remote from the radially outer jacket, can be connected to an inner jacket.

In einer Ausführung können die Stege mehrfach, insbesondere zickzackartig, konvex und/oder konkav, vorgefaltet sein. Dadurch kann bei einem Anstoßen der Laufschaufeln oder Teilen von diesen gegen den Gehäuseabschnitt eine vorteilhafte Faltungscharakteristik des Gehäuseabschnitts dargestellt werden. Vorgefaltete Stege können insbesondere wenigstens zwei Abschnitte aufweisen, die, vorzugsweise in einer Kante, ineinander übergehen und gegensinnig axial und/oder in Umfangsrichtung gegen den Radius geneigt sind.In one embodiment, the webs can be pre-folded several times, in particular zigzag-like, convex and / or concave. As a result, when the blades or parts of them are abutted against the housing portion, an advantageous folding characteristic of the housing portion can be represented. Prefolded webs may in particular have at least two sections which, preferably in one edge, merge into one another and are inclined in opposite directions axially and / or in the circumferential direction against the radius.

In einem Hohlraum zwischen Stegen kann eine Versteifung angeordnet sein. Die Versteifung kann im Querschnitt eine Gitter- oder Wabenstruktur aufweisen. Die Versteifung kann bei einem Anstoßen der Laufschaufeln oder Teilen von diesen gegen den Gehäuseabschnitt die Steifigkeit des Gehäuseabschnitts verbessern und einer Verformung des Gehäuseabschnitts entgegenwirken.In a cavity between webs, a stiffener may be arranged. The stiffener may have a grid or honeycomb structure in cross-section. The stiffener may improve the stiffness of the housing portion upon impact of the blades or parts of these against the housing portion and counteract deformation of the housing portion.

Der oben beschriebene Gehäuseabschnitt kann Bestandteil einer Turbomaschine, insbesondere Gasturbine, sein. Es ist klar, dass die Turbomaschine auch mehrere oben beschriebene Gehäuseabschnitte aufweisen kann.The housing section described above may be part of a turbomachine, in particular a gas turbine. It is clear that the turbomachine can also have a plurality of housing sections described above.

Weitere Merkmale und Vorteile ergeben sich aus den Unteransprüchen und dem Ausführungsbeispiel. Hierzu zeigen:

  • Fig. 1: einen Längsschnitt eines Gehäuseabschnitts gemäß einer Ausführung der vorliegenden Erfindung,
  • Fig. 2: einen Längsschnitt eines Gehäuseabschnitts gemäß einer weiteren Ausführung der vorliegenden Erfindung,
  • Fig. 3: einen Längsschnitt eines Gehäuseabschnitts gemäß einer weiteren Ausführung der vorliegenden Erfindung mit Innenmantel und separatem Einlaufmittel,
  • Fig. 4: einen Längsschnitt eines Gehäuseabschnitts gemäß einer weiteren der vorliegenden Erfindung Ausführung ohne Innenmantel und mit integriertem Einlaufmittel.
Further features and advantages emerge from the subclaims and the exemplary embodiment. Show:
  • Fig. 1 FIG. 4 is a longitudinal section of a housing section according to an embodiment of the present invention. FIG.
  • Fig. 2 FIG. 4 is a longitudinal section of a housing section according to another embodiment of the present invention. FIG.
  • Fig. 3 FIG. 4 is a longitudinal section of a housing section according to another embodiment of the present invention with inner jacket and separate inlet means. FIG.
  • Fig. 4 a longitudinal section of a housing section according to another of the present invention embodiment without inner jacket and with integrated inlet means.

Im Folgenden werden gleich aufgebaute Bauteile der jeweiligen Ausführungen mit gleichen Bezugszeichen versehen und gleich bezeichnet.In the following, identical components of the respective embodiments are provided with the same reference numerals and referred to the same.

Der in Figur 1 gezeigte Gehäuseabschnitt 1 gemäß einer ersten Ausführung weist einen radial äußeren Mantel 10 und einen Innenmantel 11 auf. Der radial äußere Mantel 10 wird von dem Innenmantel 11 durch einen Hohlraum 13 getrennt. Von dem radial äußeren Mantel 10 erstrecken sich im Hohlraum 13 eine Vielzahl von Stegen 12 radial nach innen. Die Stege 12 sind an einem Ende mit dem radial äußeren Mantel 10 und an dem anderen Ende mit dem Innenmantel 11 verbunden. Radial innen von dem Innenmantel 11 ist ein Strömungskanalmantel 16 angeordnet, der einen Strömungsraum 2 definiert. In dem Strömungsraum 2 sind Laufschaufeln 4 angeordnet.The in FIG. 1 shown housing portion 1 according to a first embodiment has a radially outer shell 10 and an inner shell 11. The radially outer shell 10 is separated from the inner shell 11 by a cavity 13. From the radially outer jacket 10 extend in the cavity 13, a plurality of webs 12 radially inwardly. The webs 12 are connected at one end to the radially outer shell 10 and at the other end to the inner shell 11. Radially inside of the inner shell 11, a flow channel jacket 16 is arranged, which defines a flow space 2. In the flow space 2 blades 4 are arranged.

Ferner weist der Gehäuseabschnitt 1 mehrere in axialer Richtung voneinander versetzt angeordnete Führungen 14 für (in Fig. 1 nicht dargestellte) verstellbare Leitschaufeln auf. Die Führungen 14 sind mit dem radial äußeren Mantel 10 und dem Innenmantel 11 jeweils integral ausgebildet und mit dem Strömungskanalmantel 16 form-, stoff- und/oder reibschlüssig verbunden.Further, the housing portion 1 a plurality of axially offset from one another arranged guides 14 for (in Fig. 1 not shown) adjustable vanes. The guides 14 are connected to the radially outer shell 10 and the inner shell 11 respectively integrally formed and with the flow channel jacket 16 form, material and / or frictionally connected.

Die Stege 12 sind mehrfach vorgefaltet und somit gegen den Radius geneigt, so dass bei einer Lastbeanspruchung auf den Gehäuseabschnitt 1 die Stege 12 gemäß einer vorgegebenen Faltcharakteristik gefaltet werden. Insbesondere erfolgt eine Faltung der Stege 12 in radialer Richtung. Die Stege 12 sind in axialer Richtung innerhalb des Hohlraums 13 benachbart zueinander angeordnet und mehrfach zickzackartig vorgefaltet.The webs 12 are repeatedly prefolded and thus inclined to the radius, so that at a load stress on the housing portion 1, the webs 12 are folded according to a predetermined folding characteristic. In particular, a folding of the webs 12 takes place in the radial direction. The webs 12 are arranged in the axial direction within the cavity 13 adjacent to each other and pre-folded several times zigzag.

In Figur 2 wird ein Längsschnitt eines Gehäuseabschnitts 100 gemäß einer weiteren Ausführung der vorliegenden Erfindung gezeigt. Der Gehäuseabschnitt 100 weist einen radial äußeren Mantel 10 auf, von dem sich eine Vielzahl von Stegen 120 radial nach innen erstrecken, wobei die Stege 120 miteinander verbunden sind. Die Stege 120 sind axial geneigt, wobei sich die Stege 120 im dargestellten Fall schräg zu einer nicht dargestellten Längsachse des Gehäuseabschnitts 100 (horizontal in Fig. 2) erstrecken.In FIG. 2 Fig. 3 shows a longitudinal section of a housing section 100 according to another embodiment of the present invention. The housing portion 100 has a radially outer shell 10 from which a plurality of webs 120 extend radially inwardly, wherein the webs 120 are interconnected. The webs 120 are inclined axially, wherein the webs 120 in the illustrated case obliquely to a longitudinal axis, not shown, of the housing portion 100 (horizontally in Fig. 2 ).

Die miteinander verbundenen Stege 120 bilden in einem Querschnitt senkrecht zur Steglängsachse eine Gitter- oder Wabenstruktur.The interconnected webs 120 form a grid or honeycomb structure in a cross section perpendicular to the web longitudinal axis.

Der in Figur 3 dargestellte Gehäuseabschnitt 100 weist zusätzlich zu dem in Figur 2 dargestellten Gehäuseabschnitt 100 einen Innenmantel 11 auf. Die Stege 120 sind mit dem radial äußeren Mantel 10 verbunden. Die in Figur 3 dargestellten Stege 120 umschließen analog zu den in Figur 2 dargestellten Stegen 120 Hohlräume, durch die Kühlluft von einem Kühllufteintritt (links in Fig. 3) zu einem Kühlluftaustritt (rechts in Fig. 3) geleitet wird, wie in Fig. 3 durch Strömungspfeile angedeutet.The in FIG. 3 shown housing section 100 has in addition to the in FIG. 2 shown housing portion 100 on an inner shell 11. The webs 120 are connected to the radially outer shell 10. In the FIG. 3 shown webs 120 enclose analogous to those in FIG. 2 illustrated webs 120 cavities, through the cooling air from a cooling air inlet (left in Fig. 3 ) to a cooling air outlet (right in Fig. 3 ), as in Fig. 3 indicated by flow arrows.

An der von den Stegen 120 abgewandten Seite des Innenmantels 11 ist ein Einlaufmittel 3 vorgesehen, das sich radial nach innen erstreckt. Das Einlaufmittel 3 kann in Kontakt mit einer Laufschaufel 4 gelangen und dient insbesondere dazu, einen unerwünschten Leckagestrom zwischen der Laufschaufel 4 und dem Innenmantel 11 des Gehäuseabschnitts 100 zu reduzieren.On the side facing away from the webs 120 of the inner shell 11, an inlet means 3 is provided, which extends radially inwardly. The inlet means 3 can come into contact with a blade 4 and serves in particular to reduce an undesirable leakage flow between the blade 4 and the inner shell 11 of the housing portion 100.

Der Gehäuseabschnitt 100 ist an dessen stromaufwärtiger Seite (links in Fig. 3) in dem Verbindungsabschnitt 14 über eine Schraubverbindung mit einer Gehäuseschale 200 verbunden. Ferner ist der Gehäuseabschnitt 100 an dessen stromabwärtiger Seite (rechts in Fig. 3) über einen weiteren Verbindungsabschnitt 15 mit einer weiteren Gehäuseschale 201 verbunden. Die beiden Gehäuseschalen 200, 201 können jeweils eine nicht dargestellte Leitschaufelstufe umschließen. Bei der Verbindung der weiteren Gehäuseschale 201 mit dem Gehäuseabschnitt 100 kann es sich um eine formschlüssige Verbindung handeln.The housing portion 100 is at its upstream side (left in FIG Fig. 3 ) is connected in the connecting portion 14 via a screw with a housing shell 200. Further, the housing portion 100 is at the downstream side thereof (right in FIG Fig. 3 ) connected via a further connecting portion 15 with a further housing shell 201. The two housing shells 200, 201 may each enclose a stator vane not shown. In the connection of the further housing shell 201 with the housing portion 100 may be a positive connection.

Der in Figur 4 dargestellte Gehäuseabschnitt 100' unterscheidet sich von dem in Figur 3 dargestellten Gehäuseabschnitt 100 dadurch, dass in diesem kein Innenmantel 10 vorgesehen ist. Das Einlaufmittel 3' ist einstückig mit den Stegen 120' ausgebildet. Dabei ist sichergestellt, dass das Einlaufmittel derart positioniert ist, dass es mit den Laufschaufeln 4' in Kontakt gelangen kann.The in FIG. 4 illustrated housing portion 100 'differs from that in FIG. 3 illustrated housing portion 100 characterized in that no inner shell 10 is provided in this. The inlet means 3 'is formed integrally with the webs 120'. It is ensured that the inlet means is positioned so that it can come into contact with the blades 4 '.

Die in den Figuren 2 bis 4 dargestellten Stege 120, 120' sind derart ausgebildet und ausgerichtet, dass wenigstens ein Teil der durch die Stege jeweils umschlossenen Hohlräume mit einer Kühllufteintrittsöffnung und/oder einer Kühlluftaustrittsöffnung kommuniziert. Die Kühllufteintrittsöffnung ist im Verbindungsabschnitt 14 und die Kühlluftaustrittsöffnung ist in dem weiteren Verbindungsabschnitt 15 vorgesehen. Die Kühllufteintrittsöffnung und die Kühlluftaustrittsöffnung kommunizieren mit einem in der jeweiligen Gehäuseschale 200, 201 vorgesehenen Kühlluftkanal.The in the FIGS. 2 to 4 illustrated webs 120, 120 'are formed and aligned such that at least a part of the webs respectively enclosed by the cavities communicates with a cooling air inlet opening and / or a cooling air outlet opening. The cooling air inlet opening is in the connecting section 14 and the cooling air outlet opening is provided in the further connecting section 15. The cooling air inlet opening and the cooling air outlet opening communicate with a cooling air channel provided in the respective housing shell 200, 201.

Somit kann durch die Ausbildung und Ausrichtung der Stege sichergestellt werden, dass Kühlluft über die Kühllufteintrittsöffnung in die Hohlräume der Stege einströmt und über diese zu der Kühlluftaustrittsöffnung strömt. Im Ergebnis kann erreicht werden, dass Kühlluft über den Gehäuseabschnitt 100 zwischen zwei in Längsachsrichtung der Turbomaschine benachbarten Gehäuseschalen 200, 201 strömen kann, wobei die Strömungsrichtung der Kühlluft in den Figuren durch die Pfeile P dargestellt ist. Die Stege und die Kühllufteintrittsöffnung und die Kühlluftaustrittsöffnung sind derart ausgebildet, dass die Kühlluft nicht mit dem Strömungsraum 2 der Turbomaschine kommuniziert.Thus, it can be ensured by the formation and orientation of the webs that cooling air flows through the cooling air inlet opening into the cavities of the webs and flows through them to the cooling air outlet opening. As a result, it can be achieved that cooling air can flow via the housing section 100 between two housing shells 200, 201 adjacent to the turbomachine in the longitudinal axis direction, the flow direction of the cooling air being illustrated by the arrows P in the figures. The webs and the cooling air inlet opening and the cooling air outlet opening are formed such that the cooling air does not communicate with the flow space 2 of the turbomachine.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Gehäuseabschnitt gemäß der ersten AusführungHousing section according to the first embodiment
22
Strömungsraumflow chamber
33
Einlaufmittelenemas
44
Laufschaufelblade
1010
radial äußerer Mantelradially outer jacket
1111
Innenmantelinner sheath
1212
Steg gemäß der ersten AusführungBridge according to the first version
1313
Hohlraumcavity
1414
Verbindungsabschnittconnecting portion
1515
weiterer Verbindungsabschnittanother connection section
1616
StrömungskanalmantelFlow channel cover
100100
Gehäuseabschnitt gemäß der zweiten AusführungHousing section according to the second embodiment
100'100 '
Gehäuseabschnitt gemäß der dritten AusführungHousing section according to the third embodiment
120120
Steg gemäß der zweiten AusführungBridge according to the second embodiment
200200
Gehäuseschaleshell
201201
weitere Gehäuseschaleadditional housing shell
PP
Strömungsrichtung der KühlluftFlow direction of the cooling air

Claims (10)

Gehäuseabschnitt einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe, der einen, insbesondere geschlossenen und kreisringartigen, radial äußeren Mantel (10) mit sich radial nach innen erstreckenden Stegen (12, 120) aufweist, dadurch gekennzeichnet, dass die Stege (12, 120) gegen den Radius geneigt sind.Housing portion of a turbomachinery compressor or turbomachine turbine stage having a, in particular closed and annular, radially outer jacket (10) with radially inwardly extending webs (12, 120), characterized in that the webs (12, 120) inclined to the radius are. Gehäuseabschnitt nach Anspruch 1, dadurch gekennzeichnet, dass die Stege (120) axial und/oder in Umfangsrichtung gegen den Radius geneigt sind.Housing section according to claim 1, characterized in that the webs (120) are inclined axially and / or in the circumferential direction against the radius. Gehäuseabschnitt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Stege (120) wenigstens einen Hohlraum definieren, insbesondere umschließen.Housing section according to one of the preceding claims, characterized in that the webs (120) define at least one cavity, in particular enclose. Gehäuseabschnitt nach dem vorhergehenden Anspruch, dadurch gekennzeichnet, dass wenigstens einer der durch Stege definierten Hohlräume mit einem Kühlmitteleintritt und/oder Kühlmittelaustritt kommuniziert.Housing section according to the preceding claim, characterized in that at least one of the cavities defined by webs communicates with a coolant inlet and / or coolant outlet. Gehäuseabschnitt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Stege (120) in einem Querschnitt eine Gitter- oder Wabenstruktur bilden.Housing section according to one of the preceding claims, characterized in that the webs (120) form a grid or honeycomb structure in a cross section. Gehäuseabschnitt nach Anspruch 1, dadurch gekennzeichnet, dass die Stege (12) vorgefaltet sind.Housing section according to claim 1, characterized in that the webs (12) are prefolded. Gehäuseabschnitt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Stege (12) mehrfach, insbesondere zickzackartig, konvex und/oder konkav, vorgefaltet sind.Housing section according to one of the preceding claims, characterized in that the webs (12) are repeatedly, in particular zigzag, convex and / or concave, prefolded. Gehäuseabschnitt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass in einem Hohlraum (13) zwischen Stegen (12) eine Versteifung, insbesondere eine Versteifung, die im Querschnitt eine Gitter- oder Wabenstruktur aufweist, angeordnet ist.Housing section according to one of the preceding claims, characterized in that in a cavity (13) between webs (12) is arranged a stiffening, in particular a stiffening, which has a lattice or honeycomb structure in cross-section. Gehäuseabschnitt nach einem der vorhergehenden Ansprüche, gekennzeichnet durch einen Innenmantel (11), der mit den Stegen (12, 120) verbunden ist.Housing section according to one of the preceding claims, characterized by an inner jacket (11) which is connected to the webs (12, 120). Turbomaschine, insbesondere Gasturbine, mit wenigstens einem Gehäuseabschnitt nach einem der vorhergehenden Ansprüche.Turbomachine, in particular gas turbine, with at least one housing section according to one of the preceding claims.
EP14164186.0A 2013-04-24 2014-04-10 Casing section of a turbo engine compressor or turbo engine turbine stage Not-in-force EP2796668B1 (en)

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Also Published As

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DE102013207452A1 (en) 2014-11-13
EP2796668B1 (en) 2017-03-01
ES2620514T3 (en) 2017-06-28
US9771830B2 (en) 2017-09-26
US20140321998A1 (en) 2014-10-30
EP2796668A3 (en) 2015-01-21

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