EP2796668B1 - Section de carter d'un étage de compresseur ou de turbine d'une turbomachine - Google Patents

Section de carter d'un étage de compresseur ou de turbine d'une turbomachine Download PDF

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Publication number
EP2796668B1
EP2796668B1 EP14164186.0A EP14164186A EP2796668B1 EP 2796668 B1 EP2796668 B1 EP 2796668B1 EP 14164186 A EP14164186 A EP 14164186A EP 2796668 B1 EP2796668 B1 EP 2796668B1
Authority
EP
European Patent Office
Prior art keywords
webs
housing section
turbomachine
section according
housing
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.)
Not-in-force
Application number
EP14164186.0A
Other languages
German (de)
English (en)
Other versions
EP2796668A3 (fr
EP2796668A2 (fr
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
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2796668A2 publication Critical patent/EP2796668A2/fr
Publication of EP2796668A3 publication Critical patent/EP2796668A3/fr
Application granted granted Critical
Publication of EP2796668B1 publication Critical patent/EP2796668B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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 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. According to the invention, the webs each enclose a cavity, which can be inclined axially in analogy to the webs and extend in the longitudinal direction.
  • One or more cavities enclosed by webs communicate in one embodiment with a cooling air inlet and a cooling air outlet.
  • the coolant inlet and 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 portion.
  • The, in particular interconnected, webs can form a grid 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 possible wear 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 in that no inner shell 11 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Section de carter d'un étage de compresseur de turbomachine ou de turbine de turbomachine, qui présente un revêtement externe (10) sur le plan radial, en particulier fermé et circulaire, comportant des traverses s'étendant vers l'intérieur (120) sur le plan radial, dans laquelle les traverses (120) sont inclinées vers le rayon et entourent au moins une cavité qui est inclinée de façon analogue aux traverses (120) et s'étend en direction longitudinale de la turbomachine,
    caractérisée en ce qu'au moins l'une des cavités définies par des traverses communique avec une entrée de fluide de refroidissement et une sortie de fluide de refroidissement, qui sont prévues respectivement dans une coque de carter qui est montrée sur le plan axial an amont ou en aval de la section de carter de l'étage de compresseur de turbomachine ou de turbine de turbomachine.
  2. Section de carter selon la revendication 1, caractérisée en ce que les traverses (120) sont inclinées vers le rayon sur le plan radial et/ou dans la direction périphérique.
  3. Section de carter selon l'une des revendications précédentes, caractérisée en ce que les traverses (120) sont reliées par coopération de matériau au revêtement externe (10) sur le plan radial, en particulier sont conçues, en particulier façonnées, d'un seul tenant avec celui-ci.
  4. Section de carter selon la revendication précédente, caractérisée en ce que celle-ci est fabriquée par un procédé de fabrication additif.
  5. Section de carter selon l'une des revendications précédentes, caractérisée en ce que les traverses (120) forment une section transversale d'une structure réticulaire ou alvéolaire.
  6. Section de carter selon la revendication 1, caractérisée en ce que les traverses (12) sont pré-pliées.
  7. Section de carter selon l'une des revendications précédentes, caractérisée en ce que les traverses (12) sont pré-pliées plusieurs fois, en particulier en zigzag, sur le plan convexe et/ou concave.
  8. Section de carter selon l'une des revendications précédentes, caractérisée en ce que dans une cavité creuse (13) est disposé entre des traverses (12), un renforcement, en particulier un renfoncement qui présente dans la section transversale, une structure réticulaire ou alvéolaire.
  9. Section de carter selon l'une des revendications précédentes, caractérisée par un revêtement intérieur (11) qui est relié aux traverses (12, 120).
  10. Turbomachine, en particulier, turbine à gaz comportant au moins une section de carter selon l'une des revendications précédentes.
EP14164186.0A 2013-04-24 2014-04-10 Section de carter d'un étage de compresseur ou de turbine d'une turbomachine Not-in-force EP2796668B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013207452.2A DE102013207452A1 (de) 2013-04-24 2013-04-24 Gehäuseabschnitt einer Turbomaschinenverdichter- oder Turbomaschinenturbinenstufe

Publications (3)

Publication Number Publication Date
EP2796668A2 EP2796668A2 (fr) 2014-10-29
EP2796668A3 EP2796668A3 (fr) 2015-01-21
EP2796668B1 true EP2796668B1 (fr) 2017-03-01

Family

ID=50478268

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Application Number Title Priority Date Filing Date
EP14164186.0A Not-in-force EP2796668B1 (fr) 2013-04-24 2014-04-10 Section de carter d'un étage de compresseur ou de turbine d'une turbomachine

Country Status (4)

Country Link
US (1) US9771830B2 (fr)
EP (1) EP2796668B1 (fr)
DE (1) DE102013207452A1 (fr)
ES (1) ES2620514T3 (fr)

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Also Published As

Publication number Publication date
US20140321998A1 (en) 2014-10-30
EP2796668A3 (fr) 2015-01-21
ES2620514T3 (es) 2017-06-28
EP2796668A2 (fr) 2014-10-29
US9771830B2 (en) 2017-09-26
DE102013207452A1 (de) 2014-11-13

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