EP3587741A1 - Segment ring for mounting in a turbomachine - Google Patents

Segment ring for mounting in a turbomachine Download PDF

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Publication number
EP3587741A1
EP3587741A1 EP19182753.4A EP19182753A EP3587741A1 EP 3587741 A1 EP3587741 A1 EP 3587741A1 EP 19182753 A EP19182753 A EP 19182753A EP 3587741 A1 EP3587741 A1 EP 3587741A1
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EP
European Patent Office
Prior art keywords
segment
ring
segment ring
radially
joint
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
EP19182753.4A
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German (de)
French (fr)
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EP3587741B1 (en
Inventor
Manfred Feldmann
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
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Publication of EP3587741A1 publication Critical patent/EP3587741A1/en
Application granted granted Critical
Publication of EP3587741B1 publication Critical patent/EP3587741B1/en
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005Sealing means between non relatively rotating elements
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12Preventing 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00Components
    • F05D2240/10Stators
    • F05D2240/11Shroud seal segments
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00Components
    • F05D2240/55Seals

Definitions

  • the present invention relates to a segment ring for mounting in a turbomachine.
  • the turbomachine can, for example, be a jet engine, e.g. B. a turbofan engine.
  • the fluid machine is functionally divided into a compressor, combustion chamber and turbine.
  • the air drawn in is compressed by the compressor and burned in the downstream combustion chamber with added kerosene.
  • the resulting hot gas a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process.
  • the turbine is typically subdivided into several modules, so it can have, for example, a high-pressure and a low-pressure turbine module.
  • Each of the turbine modules then generally comprises a number of stages, each stage being composed of a guide vane ring and a rotor blade ring which follows downstream.
  • the segment ring in question is intended for assembly in a turbomachine, for example in a turbine module. It can be attached to a housing part, for example, and then carry a jacket ring segment arranged radially on the inside of the housing part. Such a jacket ring segment limits the gas channel to the outside at the axial height of a rotor blade ring; it can be equipped radially on the inside, for example, with a sealing system or an inlet lining. This is intended to illustrate the present subject matter or a preferred application thereof, but initially not to restrict it in its generality (the segment ring can also perform another assembly function in the turbomachine).
  • the present invention is based on the technical problem of specifying a particularly advantageous segment ring.
  • segment ring according to claim 1.
  • This is designed for assembly or assembly from the radially inside to the outside and is divided into segments all round.
  • a sealing insert is used to reduce leakage at a joint where two circumferentially adjacent segments adjoin each other.
  • a pocket which is open towards the joint is formed in each of the two segments and the sealing insert is located therein. It is held axially in the pockets and bridges the shock, thus blocking gap flows and increasing tightness.
  • One of the mutually facing pockets is also open not only towards the butt, but also in a radial direction.
  • This is advantageous with regard to the radial assembly of the segment ring, in particular complete and / or closed segment ring, namely the corresponding segment can be pushed radially onto the sealing insert, in particular without a simultaneous displacement in a non-radial direction and / or for the sliding on would be required in the axial direction and / or in particular to provide the complete and / or closed segment ring.
  • the segmentation and the assembly from the radially inside on the one hand open up interesting assembly options, on the other hand, by additionally sealing a joint between two segments, any leakage can nevertheless be limited. Due to the inventive design of the pockets, the joint can be closed with a sealing insert, which offers an efficient seal, but assembly from the radially inside remains possible.
  • axially generally relates to the ring axis of the segment ring.
  • the ring axis typically coincides with the longitudinal axis of the turbomachine or the axis of rotation about which the rotor blade rings rotate.
  • “Radial” relates to the radial directions perpendicular to the ring or longitudinal axis, pointing away therefrom, and a “revolution” or “circumferential” or the “revolution direction” concern the rotation about the axis.
  • “Front” and “rear” refer to the axial flow direction component of the hot gas, so this passes “front” parts axially in front of “rear” parts.
  • the segment ring or its segments can be produced from a forged ring, for example, by turning and milling.
  • the segments can also be cast parts (in connection with post-processing of the functional surfaces).
  • additive manufacturing is also possible, ie the segment ring or segments can be constructed additively layer by layer from a previously formless or neutral material.
  • the pockets can already be taken into account in the original design, but they can also be inserted to remove material, e.g. eroded (spark eroding).
  • the corresponding segment can be pushed radially onto the sealing insert.
  • the pocket is aligned in the direction of insertion in which the segment or segments are assembled.
  • the direction of insertion can generally also have an axial component (for example when viewed in an axial section they are not tilted by more than 30 ° to the radial direction), and is preferably perpendicular to the axial direction.
  • the radially open pocket can also be opened radially inwards (and closed radially outwards); during assembly, this segment would then be placed first and then the other segment together with the sealing insert, which would be arranged in its closed pocket and would slide into the pocket which is open radially inwards.
  • the radially open pocket is open radially outwards and closed radially inwards.
  • the segment with this pocket can accordingly be pushed onto the sealing insert from the radial inside, which is already positioned in the pocket of the other segment.
  • the sealing insert in contrast to a pocket that is open radially inwards, is then secured in both pockets against falling out inwards and outwards, since the open pocket is directed against the housing wall.
  • the radially closed pocket is closed radially inwards and radially outwards.
  • the radially open pocket is therefore preferably opened in exactly one radial direction, preferably radially outwards, and the other pocket is closed in both radial directions.
  • the sealing insert is thus kept largely captive even before the segments are assembled in the closed pocket.
  • a grease can generally be used during assembly, which holds the sealing insert like an adhesive.
  • the closed pocket is dimensioned in a preferred embodiment such that its depth taken perpendicular to the joint corresponds to at least 0.1 times its height taken parallel to the joint.
  • the pocket is dimensioned in such a way that the sealing insert cannot unscrew before the segments are assembled.
  • Further preferred lower limits of the Depths are at least 0.2, 0.3 or 0.4 times the height, with possible (independent) upper limits at z. B. at most 2, 1.5, 1 or 0.8 times the height.
  • the sealing insert is a sealing plate.
  • the sealing insert in particular the sealing plate, which is, for example, a planar sealing plate, preferably seals off the joint and / or a segment gap between the circumferentially adjacent segments in the axial direction.
  • the axial direction is preferably normal to or substantially normal to the sheet plane, i.e. with a maximum deviation of 10 °, in particular 5 °, for exactly normal orientation.
  • a securing ring is provided, on which the segments of the segment ring are supported in a radially inward manner.
  • the locking ring can extend uninterrupted in the circumferential direction.
  • the locking ring is preferably pressed axially into a receptacle in the segment ring and held by an interference fit.
  • the segment ring preferably forms a radially protruding projection on the receptacle, behind which the retaining ring is held in an axially positive manner.
  • the projection is dimensioned such that the locking ring can be pressed in axially, but is then secured axially in the opposite direction. This is preferably supported by an inclined flank (sawtooth profile), along which the locking ring slides when pressed in.
  • one of two adjoining segments has abutting edges which are parallel to one another and thus to an insertion direction of this segment (viewed in the axial direction).
  • Such a segment can be pushed in radially outwards, even if the two adjacent segments are already positioned.
  • the mutually parallel abutting edges are preferably oriented in such a way that they or their extensions border the ring axis in the center towards the opposite side of the segment ring.
  • such a segment with abutting edges parallel to one another, has a pocket on both circumferential sides, each with a sealing insert therein.
  • These two pockets are preferably each open radially outwards and closed radially inwards.
  • every second segment has mutually parallel abutting edges in the circumferential direction.
  • the segments are or are set up in such a way that the segment ring can ideally be constructed from only a single segment ring type.
  • one of the segments adjoining the joint has an abutting edge oblique to the radial direction.
  • the oblique butt edge forms an angle ⁇ of at least 85 ° and at most 110 ° with a connecting line that extends diagonally through the segment to the outer corner of the oblique butt edge.
  • Further preferred upper limits are at most 100 ° or 95 °, further preferred lower limits are (irrespective of this) at least 88 ° or 90 ° (in the order in which they are mentioned increasingly preferred).
  • the segment can also be used when the circumferentially next-adjacent segments are already arranged in their assembly position.
  • the segment can first be brought into position with the opposite butt edge and then, as it were, turned into a system with the oblique butt edge, cf. Figure 4 for illustration.
  • the segment on this oblique abutting edge is equipped with the pocket which is open radially outwards (and closed radially inwards).
  • Such a segment can, as described in the previous paragraph, first be hooked in with the opposite abutting edge and then screwed into its mounting position, the sealing insert sliding into the radially open pocket of the segment.
  • All segments are preferably of identical construction, that is to say rotationally symmetrical about the ring or longitudinal axis. Handling only a single segment ring type can simplify assembly and storage.
  • the invention also relates to a segment ring arrangement with a segment ring disclosed here and a mounting part, preferably a housing part.
  • the segment ring is or is axially positively mounted on the mounting part, specifically a form-locking element thereof.
  • the individual segments are each assembled radially outward with the form-locking element.
  • a jacket ring segment is preferably mounted radially on the inside of the housing part, see also the comments at the beginning.
  • the segment ring is used for the assembly of the jacket ring segment; the segment ring is mounted on the housing part, and the jacket ring segment is then supported on it radially inwards.
  • This structure can be advantageous with regard to the thermal gradients (in particular in the housing area), and assembly and disassembly from the front axially is also possible.
  • the invention also relates to a turbine module with such a segment ring arrangement, a rotor blade ring being arranged radially within the jacket ring segment.
  • the segment ring arrangement is preferably provided at the axially front end of the turbine module.
  • the modules can be separated from one another comparatively easily on the one hand, so that they are then also accessible from the front axially; on the other hand, the components arranged axially at the front can also be particularly stressed and therefore need to be overhauled.
  • the invention also relates to the use of a turbine module or a segment ring or a corresponding segment ring arrangement in a turbomachine, in particular in a jet engine, for example a turbofan engine.
  • Fig. 1 shows a turbomachine 1, specifically a turbofan engine, in an axial section.
  • the flow machine 1 is functionally divided into a compressor 1a, a combustion chamber 1b and a turbine 1c.
  • Both the compressor 1a and the turbine 1c are each made up of several stages, each stage being composed of a guide vane ring and a subsequent rotor blade ring.
  • the rotor blades rotate during operation about the longitudinal axis 2 of the turbomachine 1.
  • the air sucked in is compressed in the compressor 1a and then burned in the downstream combustion chamber 1b with added kerosene.
  • the hot gas flows through the hot gas duct 3 and drives the rotor blades, which rotate about the longitudinal axis 2.
  • Fig. 2 shows a jacket ring arrangement 20, which is provided as part of a module of the turbine 1c. It has a housing part 21 and a jacket ring segment 22 a seal 23 is arranged radially on the inside, in the present case a honeycomb seal.
  • the jacket ring segment 22 surrounds the blades 24 radially outward.
  • a segment ring 25 is provided, which is divided into a plurality of segments in the circumferential direction (cf. Fig. 3 and 4 ).
  • the individual segments of the segment ring 25 are assembled from the inside radially with a form-locking element 26 of the housing part 21.
  • the form-locking element 26 is provided in the present case as a radially inwardly projecting housing web onto which the segments of the segment ring 25 are pushed and are then held in an axially positive manner.
  • the segment ring 25 forms a support 27 which supports the jacket ring segment 22 radially inward at its axially front end.
  • a locking ring 28 is used to hold the segments of the segment ring 25 radially in position. This extends circumferentially without interruption and is pressed axially into a receptacle 29 of the segment ring 25. In the receptacle 29, it is held axially positively behind a projection 30.
  • a bore 31 is provided in the form-locking element 26 or the housing web of the housing part 21, which can be used (and is optional) for supplying a cooling fluid.
  • the shielding plates 32 arranged radially between the housing part 21 and the casing ring segment 22 are optional; the approach according to the invention could also be realized with an insulating material or the like between the housing part 21 and the casing ring segment 22.
  • Fig. 3 shows the segment ring 25 in a section perpendicular to the longitudinal axis 2 (for the sake of clarity without hatching), namely a section of the segment ring 25 with segments 35, 36 Butt 45, a sealing insert 46 is provided, namely a sealing plate. A pocket 50, 51 is formed on the joint 45 in each of the segments 35, 36 for receiving it. (The sealing insert 46 is also in accordance with the section Fig. 2 recognizable.)
  • the pocket 51 in the segment 36 is closed radially inwards and outwards Sealing insert 46 is inserted in the direction of rotation.
  • the pocket 50 in the segment 35 is only closed radially inwardly, but is open radially outwards.
  • the segment 36 with the sealing insert 46 is first positioned, then the segment 35 with its mutually parallel abutting edges 35a can be inserted from the radially inside, the sealing insert 46 sliding into the pocket 50 which is open radially outwards.
  • the segment 35 is constructed symmetrically, that is to say has a further pocket which is open radially at the other end on the circumferential side.
  • Fig. 4 shows one too Fig. 3 alternative design of segments 40, in which case the entire segment ring 25 can be constructed from a single segment ring type.
  • an abutting edge 40a of the segment 40 lies at an angle to a connecting line 41 such that the angle ⁇ is approximately 90 °.
  • a sealing insert 46 is arranged in a segment 40 in a pocket 50 that is open radially outwards and in the other segment 40 in a radially closed pocket 51 on a respective joint 45 at which two segments 40 adjoin one another the sealing insert 46 is positioned, then the other segment 40, as in FIG Fig. 4 shown, rotated into its mounting position.

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

Abstract

Die vorliegende Erfindung betrifft einen Segmentring (25) zur Montage in einer Strömungsmaschine (1), der bezogen auf eine Ringachse des Segmentrings (25) umlaufend in Segmente (35, 36, 40) unterteilt ist, wobei der Segmentring (25) für eine Montage von radial innen ausgelegt ist, die Segmente (35, 36, 40) also nach radial außen zu dem Segmentring (25) zusammensetzbar sind, wobei zumindest zwei umlaufend nächstbenachbarte Segmente (35, 36, 40) in einem Stoß (45) aneinandergrenzen, an dem ein Dichteinsatz (46) vorgesehen ist, wozu in den zumindest zwei umlaufend nächstbenachbarten Segmenten (35, 36, 40) jeweils eine zu dem Stoß (45) hin offene Tasche (50, 51) ausgebildet ist, an dem Stoß (45) also zwei umlaufend einander zugewandte Taschen (50, 51) vorgesehen sind, wobei der Dichteinsatz (46) in den zwei einander zugewandten Taschen (50, 51) angeordnet und darin axial gehalten ist und sich dabei umlaufend über den Stoß (45) hinweg erstreckt, und wobei eine (50) der zwei einander zugewandten Taschen (50, 51) zusätzlich auch in einer Radialrichtung derart offen ist, dass dieses Segment (35, 40) radial auf den Dichteinsatz (46) aufgeschoben werden kann.The invention relates to a segment ring (25) for assembly in a turbomachine (1), which is divided into segments (35, 36, 40) all around in relation to an annular axis of the segment ring (25), the segment ring (25) for assembly is designed from the radially inside, the segments (35, 36, 40) can thus be assembled radially outwards to form the segment ring (25), with at least two circumferentially adjacent segments (35, 36, 40) adjoining each other in one joint (45) A sealing insert (46) is provided, for which purpose a pocket (50, 51) which is open towards the joint (45) is formed in the at least two circumferentially next adjacent segments (35, 36, 40), i.e. on the joint (45) two circumferentially facing pockets (50, 51) are provided, the sealing insert (46) being arranged in the two facing pockets (50, 51) and being held axially therein and extending circumferentially over the joint (45), and with one (50) of the two together he facing pockets (50, 51) is also open in a radial direction such that this segment (35, 40) can be pushed radially onto the sealing insert (46).

Description

Technisches GebietTechnical field

Die vorliegende Erfindung betrifft einen Segmentring zur Montage in einer Strömungsmaschine.The present invention relates to a segment ring for mounting in a turbomachine.

Stand der TechnikState of the art

Bei der Strömungsmaschine kann es sich bspw. um ein Strahltriebwerk handeln, z. B. um ein Mantelstromtriebwerk. Funktional gliedert sich die Strömungsmaschine in Verdichter, Brennkammer und Turbine. Etwa im Falle des Strahltriebwerks wird angesaugte Luft vom Verdichter komprimiert und in der nachgelagerten Brennkammer mit hinzugemischtem Kerosin verbrannt. Das entstehende Heißgas, eine Mischung aus Verbrennungsgas und Luft, durchströmt die nachgelagerte Turbine und wird dabei expandiert. Die Turbine ist typischerweise in mehrere Module untergliedert, kann also bspw. ein Hochdruck- und ein Niederdruckturbinenmodul aufweisen. Jedes der Turbinenmodule umfasst dann in der Regel mehrere Stufen, wobei jede Stufe aus einem Leitschaufelkranz und einem stromab darauffolgenden Laufschaufelkranz aufgebaut ist.The turbomachine can, for example, be a jet engine, e.g. B. a turbofan engine. The fluid machine is functionally divided into a compressor, combustion chamber and turbine. In the case of the jet engine, for example, the air drawn in is compressed by the compressor and burned in the downstream combustion chamber with added kerosene. The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process. The turbine is typically subdivided into several modules, so it can have, for example, a high-pressure and a low-pressure turbine module. Each of the turbine modules then generally comprises a number of stages, each stage being composed of a guide vane ring and a rotor blade ring which follows downstream.

Der vorliegend in Rede stehende Segmentring ist zur Montage in einer Strömungsmaschine vorgesehen, bspw. in einem Turbinenmodul. Er kann bspw. an einem Gehäuseteil befestigt werden und dann ein radial innen an dem Gehäuseteil angeordnetes Mantelringsegment tragen. Ein solches Mantelringsegment begrenzt den Gaskanal auf axialer Höhe eines Laufschaufelkranzes nach außen, es kann radial innen bspw. mit einem Dichtsystem bzw. einem Einlaufbelag ausgestattet sein. Dies soll den vorliegenden Gegenstand bzw. eine bevorzugte Anwendung davon illustrieren, ihn aber zunächst nicht in seiner Allgemeinheit beschränken (der Segmentring kann in der Strömungsmaschine auch eine anderweitige Montagefunktion übernehmen).The segment ring in question is intended for assembly in a turbomachine, for example in a turbine module. It can be attached to a housing part, for example, and then carry a jacket ring segment arranged radially on the inside of the housing part. Such a jacket ring segment limits the gas channel to the outside at the axial height of a rotor blade ring; it can be equipped radially on the inside, for example, with a sealing system or an inlet lining. This is intended to illustrate the present subject matter or a preferred application thereof, but initially not to restrict it in its generality (the segment ring can also perform another assembly function in the turbomachine).

Darstellung der ErfindungPresentation of the invention

Der vorliegenden Erfindung liegt das technische Problem zugrunde, einen besonders vorteilhaften Segmentring anzugeben.The present invention is based on the technical problem of specifying a particularly advantageous segment ring.

Dies wird erfindungsgemäß mit dem Segmentring gemäß Anspruch 1 gelöst. Dieser ist für eine Montage bzw. ein Zusammensetzen von radial innen nach außen ausgelegt und dazu umlaufend in Segmente unterteilt. An einem Stoß, an dem zwei umlaufend nächstbenachbarte Segmente aneinandergrenzen ist dabei zur Verringerung einer Leckage ein Dichteinsatz eingesetzt. Hierfür ist in den zwei Segmenten jeweils eine zu dem Stoß hin offene Tasche ausgebildet, darin sitzt der Dichteinsatz. Er ist in den Taschen axial gehalten und überbrückt den Stoß, blockiert also Spaltströmungen und erhöht die Dichtigkeit.This is achieved according to the invention with the segment ring according to claim 1. This is designed for assembly or assembly from the radially inside to the outside and is divided into segments all round. A sealing insert is used to reduce leakage at a joint where two circumferentially adjacent segments adjoin each other. For this purpose, a pocket which is open towards the joint is formed in each of the two segments and the sealing insert is located therein. It is held axially in the pockets and bridges the shock, thus blocking gap flows and increasing tightness.

Eine der einander zugewandten Taschen ist dabei ferner nicht nur zum Stoß hin, sondern auch in einer Radialrichtung offen. Dies ist hinsichtlich des radialen Zusammensetzens des Segmentrings, insbesondere vollständigen und/oder geschlossenen Segmentrings, von Vorteil, das entsprechende Segment lässt sich nämlich radial auf den Dichteinsatz aufschieben, insbesondere ohne dass für das Aufschieben eine gleichzeitige Verschiebung in einer nicht-radialen Richtung und/oder in axialer Richtung erforderlich wäre und/oder insbesondere zum Bereitstellen des vollständigen und/oder geschlossenen Segmentrings. Die Segmentierung und der Zusammenbau von radial innen eröffnen einerseits interessante Montagemöglichkeiten, indem dabei andererseits ein sich zwischen zwei Segmenten ergebender Stoß zusätzlich abgedichtet wird, kann eine etwaige Leckage gleichwohl begrenzt werden. Durch die erfindungsgemäße Ausgestaltung der Taschen lässt sich der Stoß mit einem Dichteinsatz verschließen, was eine effiziente Abdichtung bietet, es bleibt jedoch die Montage von radial innen möglich.One of the mutually facing pockets is also open not only towards the butt, but also in a radial direction. This is advantageous with regard to the radial assembly of the segment ring, in particular complete and / or closed segment ring, namely the corresponding segment can be pushed radially onto the sealing insert, in particular without a simultaneous displacement in a non-radial direction and / or for the sliding on would be required in the axial direction and / or in particular to provide the complete and / or closed segment ring. The segmentation and the assembly from the radially inside on the one hand open up interesting assembly options, on the other hand, by additionally sealing a joint between two segments, any leakage can nevertheless be limited. Due to the inventive design of the pockets, the joint can be closed with a sealing insert, which offers an efficient seal, but assembly from the radially inside remains possible.

Bevorzugte Ausgestaltungen finden sich in den abhängigen Ansprüchen und der gesamten Offenbarung, wobei in der Darstellung der Merkmale nicht immer im Einzelnen zwischen Vorrichtungs- und Verfahrens- bzw. Verwendungsaspekten unterschieden wird; jedenfalls implizit ist die Offenbarung hinsichtlich sämtlicher Anspruchskategorien zu lesen. Sie ist insbesondere stets auf sowohl den Segmentring als auch eine Anordnung bzw. ein Modul mit einem solchen Segmentring zu lesen, sowie auch auf entsprechende Verwendungen.Preferred embodiments can be found in the dependent claims and the entire disclosure, with the features not always always making a distinction in detail between device and method or use aspects becomes; in any case, the disclosure is to be read implicitly with regard to all claim categories. In particular, it is always to be read both on the segment ring and on an arrangement or a module with such a segment ring, and also on corresponding uses.

Generell bezieht sich im Rahmen dieser Offenbarung "axial" auf die Ringachse des Segmentrings. In montiertem Zustand, also in der Strömungsmaschine bzw. einem Modul davon, fällt die Ringachse typischerweise mit der Längsachse der Strömungsmaschine bzw. der Drehachse zusammen, um welche die Laufschaufelkränze rotieren. "Radial" betrifft die zu der Ring- bzw. Längsachse senkrechten, davon wegweisenden Radialrichtungen, und ein "Umlauf" bzw. "umlaufend" oder die "Umlaufrichtung" betreffen die Drehung um die Achse. "Vorne" und "hinten" beziehen sich auf die axiale Strömungsrichtungskomponente des Heißgases, dieses passiert also "vordere" Teile axial vor "hinteren" Teilen. "Ein" und "eine" sind im Rahmen dieser Offenbarung ohne ausdrücklich gegenteilige Angabe als unbestimmte Artikel und damit immer auch als "mindestens ein" bzw. "mindestens eine" zu lesen. Es wird vorrangig auf "einen" Stoß und die dort radial geöffnete Tasche Bezug genommen. Insgesamt gibt es umlaufend eine Mehr- bzw. Vielzahl Stöße, wobei bevorzugt an jedem davon ein Dichteinsatz angeordnet ist. Dies ließe sich prinzipiell auch mit Taschen erreichen, die an den übrigen Stößen nur umlaufend geöffnet sind (das Segment mit der radial geöffneten Tasche wird zuletzt platziert), bevorzugt sind jedoch sämtliche Dichteinsätze des Segmentrings jeweils in einer radial geöffneten Tasche angeordnet.In the context of this disclosure, “axially” generally relates to the ring axis of the segment ring. In the assembled state, that is to say in the turbomachine or a module thereof, the ring axis typically coincides with the longitudinal axis of the turbomachine or the axis of rotation about which the rotor blade rings rotate. "Radial" relates to the radial directions perpendicular to the ring or longitudinal axis, pointing away therefrom, and a "revolution" or "circumferential" or the "revolution direction" concern the rotation about the axis. "Front" and "rear" refer to the axial flow direction component of the hot gas, so this passes "front" parts axially in front of "rear" parts. In the context of this disclosure, "one" and "one" are to be read as indefinite articles without expressly stated otherwise and therefore always as "at least one" or "at least one". It is primarily referred to "one" impact and the pocket which is radially opened there. Overall, there are multiple or multiple joints all around, preferably a sealing insert being arranged on each of them. In principle, this could also be achieved with pockets that are only open all around at the other joints (the segment with the radially open pocket is placed last), but preferably all sealing inserts of the segment ring are each arranged in a radially open pocket.

Der Segmentring bzw. dessen Segmente können bspw. durch Drehen und Fräsen aus einem Schmiedering hergestellt werden. Die Segmente können aber auch Gussteile sein (in Verbindung mit einer Nachbearbeitung der Funktionsflächen). Schließlich ist auch eine generative Herstellung möglich, kann der Segmentring bzw. können die Segmente also additiv Schicht für Schicht aus einem zuvor formlosen bzw. -neutralen Werkstoff aufgebaut werden. Die Taschen können bereits bei der originären Formgebung berücksichtigt werden, sie lassen sich aber ebenso materialabtragend einbringen, bspw. erodieren (Funkenerodieren).The segment ring or its segments can be produced from a forged ring, for example, by turning and milling. The segments can also be cast parts (in connection with post-processing of the functional surfaces). Finally, additive manufacturing is also possible, ie the segment ring or segments can be constructed additively layer by layer from a previously formless or neutral material. The pockets can already be taken into account in the original design, but they can also be inserted to remove material, e.g. eroded (spark eroding).

Aufgrund der radial geöffneten Tasche lässt sich das entsprechende Segment radial auf den Dichteinsatz aufschieben. Die Tasche ist hierfür in der Einsetzrichtung ausgerichtet, in welcher das bzw. die Segmente zusammengesetzt werden. Die Einsetzrichtung kann im Allgemeinen auch einen axialen Anteil haben (bspw. in einem Axialschnitt betrachtet um nicht mehr als 30° zur Radialrichtung verkippt liegen), bevorzugt liegt sie senkrecht zur Axialrichtung. Die radial offene Tasche kann prinzipiell auch nach radial innen geöffnet sein (und nach radial außen geschlossen); bei der Montage würde dann dieses Segment zuerst und anschließend das andere Segment zusammen mit dem Dichteinsatz platziert werden, der hierbei in dessen geschlossener Tasche angeordnet wäre und in die nach radial innen offene Tasche rutschen würde.Due to the radially open pocket, the corresponding segment can be pushed radially onto the sealing insert. For this purpose, the pocket is aligned in the direction of insertion in which the segment or segments are assembled. The direction of insertion can generally also have an axial component (for example when viewed in an axial section they are not tilted by more than 30 ° to the radial direction), and is preferably perpendicular to the axial direction. In principle, the radially open pocket can also be opened radially inwards (and closed radially outwards); during assembly, this segment would then be placed first and then the other segment together with the sealing insert, which would be arranged in its closed pocket and would slide into the pocket which is open radially inwards.

In bevorzugter Ausgestaltung ist die radial offene Tasche jedoch nach radial außen offen und nach radial innen geschlossen. Das Segment mit dieser Tasche kann entsprechend von radial innen auf den Dichteinsatz aufgeschoben werden, der hierbei bereits in der Tasche des anderen Segments positioniert ist. Im montierten Zustand ist der Dichteinsatz dann, im Unterschied zu einer nach radial innen offenen Tasche, in beiden Taschen gegen ein Herausfallen nach innen und außen gesichert, da die offene Tasche gegen die Gehäusewand gerichtet ist.In a preferred embodiment, however, the radially open pocket is open radially outwards and closed radially inwards. The segment with this pocket can accordingly be pushed onto the sealing insert from the radial inside, which is already positioned in the pocket of the other segment. In the assembled state, the sealing insert, in contrast to a pocket that is open radially inwards, is then secured in both pockets against falling out inwards and outwards, since the open pocket is directed against the housing wall.

Die radial geschlossene Tasche ist in bevorzugter Ausgestaltung nach radial innen und nach radial außen geschlossen. Vorzugsweise ist also die radial offene Tasche in genau einer Radialrichtung geöffnet, bevorzugt nach radial außen, und ist die andere Tasche in beiden Radialrichtungen geschlossen. Der Dichteinsatz ist somit bereits vor dem Zusammensetzen der Segmente in der geschlossenen Tasche weitgehend verliersicher gehalten. Zum Schutz gegen ein Herausfallen kann bei der Montage auch generell ein Fett verwendet werden, das den Dichteinsatz wie ein Klebstoff hält.In a preferred embodiment, the radially closed pocket is closed radially inwards and radially outwards. The radially open pocket is therefore preferably opened in exactly one radial direction, preferably radially outwards, and the other pocket is closed in both radial directions. The sealing insert is thus kept largely captive even before the segments are assembled in the closed pocket. To protect against falling out, a grease can generally be used during assembly, which holds the sealing insert like an adhesive.

Auch mit Blick hierauf ist die geschlossene Tasche bei einer bevorzugten Ausführungsform derart bemessen, dass ihre senkrecht zu dem Stoß genommene Tiefe mindestens dem 0,1-fachen ihrer parallel zu dem Stoß genommenen Höhe entspricht. Die Tasche ist dahingehend bemessen, dass sich der Dichteinsatz vor dem Zusammensetzen der Segmente nicht herausdrehen kann. Weitere bevorzugte Untergrenzen der Tiefe liegen bei mindestens dem 0,2-, 0,3- bzw. 0,4-fachen der Höhe, mit möglichen (davon unabhängigen) Obergrenzen bei z. B. höchstens dem 2-, 1,5-, 1- bzw. 0,8-fachen der Höhe.With a view to this, the closed pocket is dimensioned in a preferred embodiment such that its depth taken perpendicular to the joint corresponds to at least 0.1 times its height taken parallel to the joint. The pocket is dimensioned in such a way that the sealing insert cannot unscrew before the segments are assembled. Further preferred lower limits of the Depths are at least 0.2, 0.3 or 0.4 times the height, with possible (independent) upper limits at z. B. at most 2, 1.5, 1 or 0.8 times the height.

In bevorzugter Ausgestaltung ist der Dichteinsatz ein Dichtblech.In a preferred embodiment, the sealing insert is a sealing plate.

Vorzugsweise dichter der Dichteinsatz, insbesondere das Dichtblech, das beispielsweise ein planares Dichtblech ist, den Stoß und/oder einen Segmentspalt zwischen den umlaufend nächstbenachbarten Segmenten in axialer Richtung ab. Im Falle eines planaren Dichtblechs liegt die axialer Richtung vorzugsweise normal zur Blechebene oder im Wesentlichen normal zu dieser, d.h. mit einer maximalen Abweichung von 10°, insbesondere 5°, zur exakt normalen Orientierung.The sealing insert, in particular the sealing plate, which is, for example, a planar sealing plate, preferably seals off the joint and / or a segment gap between the circumferentially adjacent segments in the axial direction. In the case of a planar sealing sheet, the axial direction is preferably normal to or substantially normal to the sheet plane, i.e. with a maximum deviation of 10 °, in particular 5 °, for exactly normal orientation.

Bei einer bevorzugten Ausführungsform ist ein Sicherungsring vorgesehen, an dem die Segmente des Segmentrings nach radial innen abgestützt aufsitzen. Dazu kann sich der Sicherungsring in Umlaufrichtung unterbrechungsfrei erstrecken. Bevorzugt ist der Sicherungsring axial in eine Aufnahme in dem Segmentring eingepresst und durch einen Presssitz gehalten. Vorzugsweise bildet der Segmentring an der Aufnahme einen radial hervortretenden Vorsprung, hinter dem der Sicherungsring axial formschlüssig gehalten ist. Der Vorsprung ist derart bemessen, dass der Sicherungsring axial eingepresst werden kann, dann aber axial entgegengesetzt gesichert ist. Bevorzugt wird dies durch eine schräg angestellte Flanke (Sägezahnprofil) unterstützt, entlang welcher der Sicherungsring beim Einpressen rutscht.In a preferred embodiment, a securing ring is provided, on which the segments of the segment ring are supported in a radially inward manner. For this purpose, the locking ring can extend uninterrupted in the circumferential direction. The locking ring is preferably pressed axially into a receptacle in the segment ring and held by an interference fit. The segment ring preferably forms a radially protruding projection on the receptacle, behind which the retaining ring is held in an axially positive manner. The projection is dimensioned such that the locking ring can be pressed in axially, but is then secured axially in the opposite direction. This is preferably supported by an inclined flank (sawtooth profile), along which the locking ring slides when pressed in.

Die im Folgenden geschilderten Ausführungsformen betreffen die Orientierung bzw. Erstreckung der Stoßkanten, mit welchen die Segmente des Segmentrings in einem jeweiligen Stoß aneinandergrenzen. Zwei umlaufend nächstbenachbarte Segmente haben an dem jeweiligen Stoß zueinander komplementäre Stoßkanten.The embodiments described below relate to the orientation or extent of the abutting edges with which the segments of the segment ring adjoin one another in a respective abutment. Two circumferentially next adjacent segments have mutually complementary butt edges at the respective butt.

Bei einer bevorzugten Ausführungsform hat jeweils eines von zwei aneinandergrenzenden Segmenten Stoßkanten, die zueinander und damit zu einer Einsetzrichtung dieses Segments parallel sind (in axialer Richtung gesehen). Ein solches Segment lässt sich nach radial außen einschieben, auch wenn die beiden umlaufend nächstbenachbarten Segmente bereits positioniert sind. Bezogen auf den Segmentring im Gesamten sind die zueinander parallelen Stoßkanten bevorzugt derart orientiert, dass sie bzw. ihre Verlängerungen zur gegenüberliegenden Seite des Segmentrings hin dessen Ringachse mittig einfassen.In a preferred embodiment, one of two adjoining segments has abutting edges which are parallel to one another and thus to an insertion direction of this segment (viewed in the axial direction). Such a segment can be pushed in radially outwards, even if the two adjacent segments are already positioned. With respect to the segment ring as a whole, the mutually parallel abutting edges are preferably oriented in such a way that they or their extensions border the ring axis in the center towards the opposite side of the segment ring.

In bevorzugter Ausgestaltung weist ein solches Segment mit zueinander parallelen Stoßkanten an beiden Umlaufseiten jeweils eine Tasche mit jeweils einem Dichteinsatz darin auf. Bevorzugt sind diese beiden Taschen jeweils nach radial außen offen und nach radial innen geschlossen. Vorzugsweise hat in Umlaufrichtung jedes zweite Segment jeweils für sich zueinander parallele Stoßkanten. Bevorzugt sind diese Segmente untereinander baugleich und sind auch die dazwischen angeordneten, komplementären Segmente untereinander baugleich, sodass der gesamte Segmentring mit nur zwei unterschiedlichen Segmenttypen aufgebaut werden kann.In a preferred embodiment, such a segment, with abutting edges parallel to one another, has a pocket on both circumferential sides, each with a sealing insert therein. These two pockets are preferably each open radially outwards and closed radially inwards. Preferably, every second segment has mutually parallel abutting edges in the circumferential direction. These segments are preferably identical to one another and the complementary segments arranged between them are also identical to one another, so that the entire segment ring can be constructed using only two different segment types.

Bei einer anderen bevorzugten Ausführungsform ist bzw. sind die Segmente derart gefasst, dass der Segmentring im Idealfall aus sogar nur einem einzigen Segmentringtyp aufgebaut werden kann. Dazu hat eines der an dem Stoß aneinandergrenzenden Segmente dort eine zur Radialrichtung schräge Stoßkante. Konkret schließt die schräge Stoßkante mit einer Verbindungslinie, die sich diagonal durch das Segment zur äußeren Ecke der schrägen Stoßkante erstreckt, einen Winkel α von mindestens 85° und höchstens 110° ein. Weitere bevorzugte Obergrenzen liegen bei höchstens 100° bzw. 95°, weitere bevorzugte Untergrenzen liegen (davon unabhängig) bei mindestens 88° bzw. 90° (jeweils in der Reihenfolge der Nennung zunehmend bevorzugt). Durch eine entsprechende Begrenzung des Winkels α lässt sich das Segment auch dann einsetzen, wenn die umlaufend nächstbenachbarten Segmente bereits in ihrer Montageposition angeordnet sind. Das Segment kann hierbei zunächst mit der entgegengesetzten Stoßkante in Position gebracht und dann gewissermaßen in eine Anlage mit der schrägen Stoßkante hineingedreht werden, vgl. Figur 4 zur Illustration.In another preferred embodiment, the segments are or are set up in such a way that the segment ring can ideally be constructed from only a single segment ring type. For this purpose, one of the segments adjoining the joint has an abutting edge oblique to the radial direction. Specifically, the oblique butt edge forms an angle α of at least 85 ° and at most 110 ° with a connecting line that extends diagonally through the segment to the outer corner of the oblique butt edge. Further preferred upper limits are at most 100 ° or 95 °, further preferred lower limits are (irrespective of this) at least 88 ° or 90 ° (in the order in which they are mentioned increasingly preferred). By appropriately limiting the angle α, the segment can also be used when the circumferentially next-adjacent segments are already arranged in their assembly position. The segment can first be brought into position with the opposite butt edge and then, as it were, turned into a system with the oblique butt edge, cf. Figure 4 for illustration.

In bevorzugter Ausgestaltung ist das Segment an dieser schrägen Stoßkante mit der nach radial außen offenen (und nach radial innen geschlossenen) Tasche ausgestattet.In a preferred embodiment, the segment on this oblique abutting edge is equipped with the pocket which is open radially outwards (and closed radially inwards).

Ein solches Segment kann, wie im vorherigen Absatz geschildert, zunächst mit der entgegengesetzten Stoßkante eingehängt und dann in seine Montageposition hineingedreht werden, wobei der Dichteinsatz in die nach radial außen offene Tasche des Segments rutscht. Vorzugsweise sind sämtliche Segmente baugleich, also drehsymmetrisch um die Ring- bzw. Längsachse. Die Handhabung von nur einem einzigen Segmentringtyp kann die Montage und die Lagerhaltung vereinfachen.Such a segment can, as described in the previous paragraph, first be hooked in with the opposite abutting edge and then screwed into its mounting position, the sealing insert sliding into the radially open pocket of the segment. All segments are preferably of identical construction, that is to say rotationally symmetrical about the ring or longitudinal axis. Handling only a single segment ring type can simplify assembly and storage.

Die Erfindung betrifft auch eine Segmentringanordnung mit einem vorliegend offenbarten Segmentring und einem Montageteil, vorzugsweise einem Gehäuseteil. Der Segmentring wird bzw. ist an dem Montageteil, konkret einem Formschlusselement davon, axial formschlüssig montiert. Dazu sind die einzelnen Segmente jeweils nach radial außen mit dem Formschlusselement zusammengesetzt. Vorzugsweise ist radial innen an dem Gehäuseteil ein Mantelringsegment montiert, vergleiche auch die Anmerkungen eingangs. Der Segmentring dient hierbei der Montage des Mantelringsegments; der Segmentring wird an dem Gehäuseteil montiert, und das Mantelringsegment liegt dann nach radial innen abgestützt darauf. Dieser Aufbau kann hinsichtlich der Thermalgradienten von Vorteil sein (insbesondere im Gehäusebereich), und zudem ist eine Montage bzw. Demontage von axial vorne möglich.The invention also relates to a segment ring arrangement with a segment ring disclosed here and a mounting part, preferably a housing part. The segment ring is or is axially positively mounted on the mounting part, specifically a form-locking element thereof. For this purpose, the individual segments are each assembled radially outward with the form-locking element. A jacket ring segment is preferably mounted radially on the inside of the housing part, see also the comments at the beginning. The segment ring is used for the assembly of the jacket ring segment; the segment ring is mounted on the housing part, and the jacket ring segment is then supported on it radially inwards. This structure can be advantageous with regard to the thermal gradients (in particular in the housing area), and assembly and disassembly from the front axially is also possible.

Die Erfindung betrifft auch ein Turbinenmodul mit einer solchen Segmentringanordnung, wobei radial innerhalb des Mantelringsegments ein Laufschaufelkranz angeordnet ist. Bevorzugt ist die Segmentringanordnung am axial vorderen Ende des Turbinenmoduls vorgesehen. Im Zuge einer Überholung lassen sich die Module einerseits vergleichsweise einfach voneinander trennen, sie sind dann also jeweils auch von axial vorne zugänglich; anderseits können die axial vorne angeordneten Bauteile auch besonders belastet und damit überholungsbedürftig sein.The invention also relates to a turbine module with such a segment ring arrangement, a rotor blade ring being arranged radially within the jacket ring segment. The segment ring arrangement is preferably provided at the axially front end of the turbine module. In the course of an overhaul, the modules can be separated from one another comparatively easily on the one hand, so that they are then also accessible from the front axially; on the other hand, the components arranged axially at the front can also be particularly stressed and therefore need to be overhauled.

Die Erfindung betrifft auch die Verwendung eines Turbinenmoduls bzw. eines Segmentrings oder einer entsprechenden Segmentringanordnung in einer Strömungsmaschine, insbesondere in einem Strahltriebwerk, bspw. einem Mantelstromtriebwerk.The invention also relates to the use of a turbine module or a segment ring or a corresponding segment ring arrangement in a turbomachine, in particular in a jet engine, for example a turbofan engine.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels näher erläutert, wobei die einzelnen Merkmale im Rahmen der nebengeordneten Ansprüche auch in anderer Kombination erfindungswesentlich sein können und auch weiterhin nicht im Einzelnen zwischen den unterschiedlichen Anspruchskategorien unterschieden wird.The invention is explained in more detail below on the basis of an exemplary embodiment, the individual features within the framework of the subordinate claims also being essential to the invention in a different combination and furthermore not being distinguished in detail between the different claim categories.

Im Einzelnen zeigt

Figur 1
ein Mantelstromtriebwerk in einem Axialschnitt;
Figur 2
eine erfindungsgemäße Mantelringanordnung als Teil des Mantelstromtriebwerks gemäß Figur 1 in einem Axialschnitt;
Figur 3
einen Ausschnitt eines Segmentrings der Anordnung gemäß Figur 2 in einem Schnitt senkrecht zur axialen Richtung;
Figur 4
als Alternative zu Figur 3 eine weitere Möglichkeit zur Orientierung der Stoßkanten der einzelnen Segmente.
In detail shows
Figure 1
a turbofan engine in an axial section;
Figure 2
a jacket ring arrangement according to the invention as part of the turbofan engine according to Figure 1 in an axial section;
Figure 3
a section of a segment ring according to the arrangement Figure 2 in a section perpendicular to the axial direction;
Figure 4
as an alternative to Figure 3 another way of orienting the abutting edges of the individual segments.

Bevorzugte Ausführung der ErfindungPreferred embodiment of the invention

Fig. 1 zeigt eine Strömungsmaschine 1, konkret ein Mantelstromtriebwerk, in einem Axialschnitt. Die Strömungsmaschine 1 gliedert sich funktional in Verdichter 1a, Brennkammer 1b und Turbine 1c. Sowohl der Verdichter 1a als auch die Turbine 1c sind jeweils aus mehreren Stufen aufgebaut, jede Stufe setzt sich aus einem Leit- und einem darauffolgenden Laufschaufelkranz zusammen. Die Laufschaufelkränze rotieren im Betrieb um die Längsachse 2 der Strömungsmaschine 1. Im Verdichter 1a wird die angesaugte Luft komprimiert, und dann in der nachgelagerten Brennkammer 1b mit hinzugemischtem Kerosin verbrannt. Das Heißgas durchströmt den Heißgaskanal 3 und treibt dabei die Laufschaufelkränze an, die um die Längsachse 2 rotieren. Fig. 1 shows a turbomachine 1, specifically a turbofan engine, in an axial section. The flow machine 1 is functionally divided into a compressor 1a, a combustion chamber 1b and a turbine 1c. Both the compressor 1a and the turbine 1c are each made up of several stages, each stage being composed of a guide vane ring and a subsequent rotor blade ring. The rotor blades rotate during operation about the longitudinal axis 2 of the turbomachine 1. The air sucked in is compressed in the compressor 1a and then burned in the downstream combustion chamber 1b with added kerosene. The hot gas flows through the hot gas duct 3 and drives the rotor blades, which rotate about the longitudinal axis 2.

Fig. 2 zeigt eine Mantelringanordnung 20, die als Teil eines Moduls der Turbine 1c vorgesehen ist. Sie weist ein Gehäuseteil 21 und ein Mantelringsegment 22 auf, an dem radial innen eine Dichtung 23 angeordnet ist, vorliegend eine Honigwabendichtung. Das Mantelringsegment 22 fasst die Laufschaufeln 24 nach radial außen ein. Fig. 2 shows a jacket ring arrangement 20, which is provided as part of a module of the turbine 1c. It has a housing part 21 and a jacket ring segment 22 a seal 23 is arranged radially on the inside, in the present case a honeycomb seal. The jacket ring segment 22 surrounds the blades 24 radially outward.

Zur Montage des Mantelringsegments 22 an dem Gehäuseteil 21 ist ein Segmentring 25 vorgesehen, der in Umlaufrichtung in eine Mehrzahl Segmente untergliedert ist (vgl. Fig. 3 und 4). Die einzelnen Segmente des Segmentrings 25 werden von radial innen mit einem Formschlusselement 26 des Gehäuseteils 21 zusammengesetzt. Das Formschlusselement 26 ist vorliegend als nach radial innen hervortretender Gehäusesteg vorgesehen, auf den die Segmente des Segmentrings 25 aufgeschoben werden und dann axial formschlüssig gehalten sind. Der Segmentring 25 bildet eine Auflage 27, die das Mantelringsegment 22 an seinem axial vorderen Ende nach radial innen abstützt. Um die Segmente des Segmentrings 25 radial in Position zu halten, ist ein Sicherungsring 28 eingesetzt. Dieser erstreckt sich umlaufend unterbrechungsfrei und wird axial in eine Aufnahme 29 des Segmentrings 25 eingepresst. In der Aufnahme 29 ist er hinter einem Vorsprung 30 axial formschlüssig gehalten.To mount the jacket ring segment 22 on the housing part 21, a segment ring 25 is provided, which is divided into a plurality of segments in the circumferential direction (cf. Fig. 3 and 4 ). The individual segments of the segment ring 25 are assembled from the inside radially with a form-locking element 26 of the housing part 21. The form-locking element 26 is provided in the present case as a radially inwardly projecting housing web onto which the segments of the segment ring 25 are pushed and are then held in an axially positive manner. The segment ring 25 forms a support 27 which supports the jacket ring segment 22 radially inward at its axially front end. To hold the segments of the segment ring 25 radially in position, a locking ring 28 is used. This extends circumferentially without interruption and is pressed axially into a receptacle 29 of the segment ring 25. In the receptacle 29, it is held axially positively behind a projection 30.

In dem Formschlusselement 26 bzw. dem Gehäusesteg des Gehäuseteils 21 ist eine Bohrung 31 vorgesehen, die zum Zuführen eines Kühlfluids genutzt werden kann (und optional ist). Ferner sind auch die radial zwischen dem Gehäuseteil 21 und dem Mantelringsegment 22 angeordneten Abschirmbleche 32 optional, der erfindungsgemäße Ansatz ließe sich ebenso mit einem Isoliermaterial oder dergleichen zwischen dem Gehäuseteil 21 und dem Mantelringsegment 22 realisieren.A bore 31 is provided in the form-locking element 26 or the housing web of the housing part 21, which can be used (and is optional) for supplying a cooling fluid. Furthermore, the shielding plates 32 arranged radially between the housing part 21 and the casing ring segment 22 are optional; the approach according to the invention could also be realized with an insulating material or the like between the housing part 21 and the casing ring segment 22.

Fig. 3 zeigt den Segmentring 25 in einem zur Längsachse 2 senkrechten Schnitt (der Übersichtlichkeit halber ohne Schraffur), und zwar einen Ausschnitt des Segmentrings 25 mit Segmenten 35, 36. Die zwei umlaufend nächstbenachbarten Segmente 35, 36 grenzen in einem Stoß 45 aneinander, zur Abdichtung des Stoßes 45 ist ein Dichteinsatz 46 vorgesehen, nämlich ein Dichtblech. Für dessen Aufnahme ist in jedem der Segmente 35, 36 an dem Stoß 45 jeweils eine Tasche 50,51 ausgebildet. (Der Dichteinsatz 46 ist auch in dem Schnitt gemäß Fig. 2 zu erkennen.) Fig. 3 shows the segment ring 25 in a section perpendicular to the longitudinal axis 2 (for the sake of clarity without hatching), namely a section of the segment ring 25 with segments 35, 36 Butt 45, a sealing insert 46 is provided, namely a sealing plate. A pocket 50, 51 is formed on the joint 45 in each of the segments 35, 36 for receiving it. (The sealing insert 46 is also in accordance with the section Fig. 2 recognizable.)

Die Tasche 51 in dem Segment 36 ist nach radial innen und außen geschlossen, der Dichteinsatz 46 wird in Umlaufrichtung eingeschoben. Die Tasche 50 in dem Segment 35 ist hingegen nur nach radial innen geschlossen, nach radial außen jedoch offen. Bei der Montage wird zunächst das Segment 36 mit dem Dichteinsatz 46 positioniert, anschließend kann das Segment 35 mit seinen zueinander parallelen Stoßkanten 35a von radial innen eingeschoben werden, wobei der Dichteinsatz 46 in die nach radial außen offene Tasche 50 rutscht. Das Segment 35 ist symmetrisch aufgebaut, weist also am anderen umlaufseitigen Ende eine weitere nach radial außen offene Tasche auf.The pocket 51 in the segment 36 is closed radially inwards and outwards Sealing insert 46 is inserted in the direction of rotation. The pocket 50 in the segment 35, on the other hand, is only closed radially inwardly, but is open radially outwards. During assembly, the segment 36 with the sealing insert 46 is first positioned, then the segment 35 with its mutually parallel abutting edges 35a can be inserted from the radially inside, the sealing insert 46 sliding into the pocket 50 which is open radially outwards. The segment 35 is constructed symmetrically, that is to say has a further pocket which is open radially at the other end on the circumferential side.

Fig. 4 zeigt eine zu Fig. 3 alternative Gestaltung von Segmenten 40, wobei in diesem Fall der gesamte Segmentring 25 aus einem einzigen Segmentringtyp aufgebaut werden kann. Dazu liegt eine Stoßkante 40a des Segments 40 derart schräg zu einer Verbindungslinie 41, dass der Winkel α rund 90° beträgt. Auch in diesem Fall ist an einem jeweiligen Stoß 45, an dem zwei Segmente 40 aneinandergrenzen, ein Dichteinsatz 46 in dem einen Segment 40 in einer nach radial außen offenen Tasche 50 angeordnet und in dem anderen Segment 40 in einer radial geschlossenen Tasche 51. In letzterer wird der Dichteinsatz 46 positioniert, anschließend wird das andere Segment 40, wie in Fig. 4 dargestellt, in seine Montageposition hineingedreht. BEZUGSZEICHENLISTE Strömungsmaschine 1  Verdichter 1a  Brennkammer 1b  Turbine 1c Längsachse 2 Heißgaskanal 3 Mantelringanordnung 20 Gehäuseteil 21 Mantelringsegment 22 Dichtung 23 Laufschaufeln 24 Segmentring 25 Formschlusselement 26 Auflage 27 Sicherungsring 28 Aufnahme 29 Vorsprung 30 Bohrung 31 Abschirmbleche 32 Segment 35  Stoßkante 35a Segment 36  Stoßkante 36a Segment 40  Stoßkante 40a Verbindungslinie 41 Stoß 45 Dichteinsatz 46 Taschen 50, 51 Fig. 4 shows one too Fig. 3 alternative design of segments 40, in which case the entire segment ring 25 can be constructed from a single segment ring type. For this purpose, an abutting edge 40a of the segment 40 lies at an angle to a connecting line 41 such that the angle α is approximately 90 °. In this case too, a sealing insert 46 is arranged in a segment 40 in a pocket 50 that is open radially outwards and in the other segment 40 in a radially closed pocket 51 on a respective joint 45 at which two segments 40 adjoin one another the sealing insert 46 is positioned, then the other segment 40, as in FIG Fig. 4 shown, rotated into its mounting position. <B> LIST OF REFERENCES </ b> flow machine 1 compressor 1a combustion chamber 1b turbine 1c longitudinal axis 2 Hot gas duct 3 Shroud assembly 20 housing part 21 Shroud segment 22 poetry 23 blades 24 segment ring 25 Form-fitting element 26 edition 27 circlip 28 admission 29 head Start 30 drilling 31 shielding 32 segment 35 impact edge 35a segment 36 impact edge 36a segment 40 impact edge 40a connecting line 41 shock 45 sealing insert 46 Bags 50, 51

Claims (15)

Segmentring (25) zur Montage in einer Strömungsmaschine (1),
der, bezogen auf eine Ringachse des Segmentrings (25), umlaufend in Segmente (35, 36, 40) unterteilt ist,
wobei der Segmentring (25) für eine Montage von radial innen ausgelegt ist, die Segmente (35, 36, 40) also nach radial außen zu dem Segmentring (25) zusammensetzbar sind,
wobei zumindest zwei umlaufend nächstbenachbarte Segmente (35, 36, 40) in einem Stoß (45) aneinandergrenzen, an dem ein Dichteinsatz (46) vorgesehen ist,
wozu in den zumindest zwei umlaufend nächstbenachbarten Segmenten (35, 36, 40) jeweils eine zu dem Stoß (45) hin offene Tasche (50, 51) ausgebildet ist, an dem Stoß (45) also zwei umlaufend einander zugewandte Taschen (50, 51) vorgesehen sind,
wobei der Dichteinsatz (46) in den zwei einander zugewandten Taschen (50, 51) angeordnet und darin axial gehalten ist und sich dabei umlaufend über den Stoß (45) hinweg erstreckt,
und wobei eine (50) der zwei einander zugewandten Taschen (50, 51) zusätzlich auch in einer Radialrichtung derart offen ist, dass dieses Segment (35, 40) radial auf den Dichteinsatz (46) aufgeschoben werden kann.
Segment ring (25) for mounting in a turbomachine (1),
which, based on a ring axis of the segment ring (25), is divided all the way into segments (35, 36, 40),
the segment ring (25) being designed for installation from the radially inside, the segments (35, 36, 40) thus being able to be assembled radially outwards to form the segment ring (25),
wherein at least two circumferentially next adjacent segments (35, 36, 40) adjoin each other in a joint (45) on which a sealing insert (46) is provided,
for which purpose a pocket (50, 51) which is open towards the joint (45) is formed in each of the at least two circumferentially next adjacent segments (35, 36, 40), that is to say on the joint (45) two circumferentially facing pockets (50, 51 ) are provided
wherein the sealing insert (46) is arranged in the two mutually facing pockets (50, 51) and is held axially therein and extends circumferentially over the joint (45),
and one (50) of the two mutually facing pockets (50, 51) is also open in a radial direction such that this segment (35, 40) can be pushed radially onto the sealing insert (46).
Segmentring (25) nach Anspruch 1, bei welchem die radial offene Tasche (50) nach radial innen geschlossen und nach radial außen offen ist, dieses Segment (35, 40) also von radial innen auf den Dichteinsatz (46) aufgeschoben werden kann.Segment ring (25) according to claim 1, in which the radially open pocket (50) is closed radially inwards and is open radially outwards, this segment (35, 40) can therefore be pushed onto the sealing insert (46) from the radially inside. Segmentring (25) nach Anspruch 1 oder 2, bei welchem die andere (51) der zwei einander zugewandten Taschen (50, 51) nach radial innen und radial außen geschlossen ist.Segment ring (25) according to Claim 1 or 2, in which the other (51) of the two mutually facing pockets (50, 51) is closed radially inwards and radially outwards. Segmentring (25) nach Anspruch 3, bei welchem die nach radial innen und radial außen geschlossene Tasche (51) eine senkrecht zu dem Stoß (45) genommene Tiefe hat, die mindestens dem 0,1-fachen ihrer parallel zu dem Stoß (45) genommen Höhe entspricht.A segment ring (25) according to claim 3, wherein the radially inward and radially outward closed pocket (51) has a depth taken perpendicular to the joint (45) which is at least 0.1 times its parallel to the joint (45) taken height corresponds. Segmentring (25) nach einem der vorstehenden Ansprüche, bei welchem der Dichteinsatz (46) ein Dichtblech ist und/oder bei welchem der Dichteinsatz (46) den Stoß (45) in axialer Richtung abdichtet.Segment ring (25) according to one of the preceding claims, in which the sealing insert (46) is a sealing plate and / or in which the sealing insert (46) seals the joint (45) in the axial direction. Segmentring (25) nach einem der vorstehenden Ansprüche mit einem Sicherungsring (28), an dem die Segmente (35, 36, 40) nach radial innen abgestützt aufsitzen.Segment ring (25) according to one of the preceding claims with a locking ring (28) on which the segments (35, 36, 40) are supported in a radially inward manner. Segmentring (25) nach einem der vorstehenden Ansprüche, bei welchem eines (35) der zwei aneinandergrenzenden Segmente (35, 36) an dem Stoß (45) und umlaufend entgegengesetzt jeweils eine Stoßkante (35a) hat und diese Stoßkanten (35a) in axialer Richtung gesehen parallel zueinander liegen.Segment ring (25) according to one of the preceding claims, in which one (35) of the two adjacent segments (35, 36) on the joint (45) and circumferentially opposite each have a joint edge (35a) and these joint edges (35a) in the axial direction seen parallel to each other. Segmentring (25) nach den Ansprüchen 2 und 7, bei welchem die nach radial innen geschlossene und nach radial außen offene Tasche (50) in dem Segment (35) mit den zueinander parallelen Stoßkanten (35a) vorgesehen ist, wobei in diesem Segment (35) auch umlaufend entgegengesetzt eine nach radial innen geschlossene und nach radial außen offene Tasche vorgesehen ist, in welcher ein weiterer Dichteinsatz (46) angeordnet ist.Segment ring (25) according to claims 2 and 7, in which the radially inwardly closed and radially outwardly open pocket (50) is provided in the segment (35) with the mutually parallel abutting edges (35a), in which segment (35 ) there is also a circumferentially opposite pocket which is closed radially inwards and is open to the radially outside and in which a further sealing insert (46) is arranged. Segmentring (25) nach einem der Ansprüche 1 bis 6, bei welchem eines der zwei aneinandergrenzenden Segmente (40) an dem Stoß (45) eine schräge Stoßkante (40a) hat, die in axialer Richtung gesehen mit einer Verbindungslinie (41), die sich zwischen einem Schnittpunkt der schrägen Stoßkante (40a) mit einer Außenumfangslinie des Segmentrings (25) und einem Schnittpunkt einer entgegengesetzten Stoßkante dieses Segments mit einer Innenumfangslinie des Segmentrings (25) erstreckt, einen Winkel α einschließt, der mindestens 85° und höchstens 110° beträgt.Segment ring (25) according to one of Claims 1 to 6, in which one of the two adjoining segments (40) on the joint (45) has an oblique joint edge (40a) which, viewed in the axial direction, has a connecting line (41) which extends between an intersection of the oblique abutting edge (40a) with an outer circumferential line of the segment ring (25) and an intersection an opposite abutting edge of this segment with an inner circumferential line of the segment ring (25), includes an angle α which is at least 85 ° and at most 110 °. Segmentring (25) nach den Ansprüchen 2 und 9, bei welchem die Tasche (50), die an dem Stoß (45) der zwei aneinandergrenzenden Segmente (40) nach radial innen geschlossen und nach radial außen offen ist, an der schrägen Stoßkante (40a) angeordnet ist, also in dem Segment (40) mit der an dem Stoß (45) schrägen Stoßkante (40a).Segment ring (25) according to claims 2 and 9, in which the pocket (50), which is closed radially inwards at the joint (45) of the two adjoining segments (40) and is open towards the radially outwards, on the oblique joint edge (40a ) is arranged, that is in the segment (40) with the abutting edge (40a) on the joint (45). Segmentring (25) nach Anspruch 9 oder 10, bei welchem sämtliche Segmente (40) des Segmentrings (25) zueinander baugleich sind.Segment ring (25) according to claim 9 or 10, in which all segments (40) of the segment ring (25) are identical to one another. Segmentringanordnung für eine Strömungsmaschine (1), mit
einem Segmentring (25) nach einem der vorstehenden Ansprüche und einem Montageteil mit einem Formschlusselement (26), an dem der Segmentring (25) axial formschlüssig angeordnet ist,
wozu die Segmente (35, 36, 40) des Segmentrings (25) jeweils nach radial außen mit dem Formschlusselement (26) zusammengesetzt sind.
Segment ring arrangement for a turbomachine (1), with
a segment ring (25) according to one of the preceding claims and an assembly part with a form-locking element (26) on which the segment ring (25) is arranged in an axially positive manner,
for which the segments (35, 36, 40) of the segment ring (25) are each assembled radially outwards with the form-locking element (26).
Segmentringanordnung nach Anspruch 12 mit einem Mantelringsegment (22), das dazu vorgesehen ist, einen Laufschaufelkranz der Strömungsmaschine (1) nach radial außen einzufassen, wobei das Montageteil, an dem der Segmentring (25) axial formschlüssig montiert ist, ein Gehäuseteil (21) ist, und wobei das Mantelringsegment (22) radial innerhalb des Gehäuseteils (21) montiert ist, indem der Segmentring (25) eine Auflage (27) bildet, auf welcher das Mantelringsegment (22) mit einem axial vorderen Ende nach radial innen abgestützt aufsitzt.Segment ring arrangement according to claim 12 with a jacket ring segment (22) which is provided to surround a rotor blade ring of the turbomachine (1) radially outward, the mounting part on which the segment ring (25) is axially positively mounted is a housing part (21) , and wherein the jacket ring segment (22) is mounted radially inside the housing part (21) in that the segment ring (25) forms a support (27) on which the jacket ring segment (22) is supported with an axially front end supported radially inwards. Turbinenmodul mit einer Segmentringanordnung nach Anspruch 13 und mit einem Laufschaufelkranz, den das Mantelringsegment (22) nach radial außen einfasst, wobei die Segmentringanordnung und damit der Segmentring (25) bevorzugt an einem axial vorderen Ende des Turbinenmoduls angeordnet sind.Turbine module with a segment ring arrangement according to claim 13 and with a rotor blade ring, which surrounds the shroud segment (22) radially outward, the segment ring arrangement and thus the segment ring (25) are preferably arranged at an axially front end of the turbine module. Verwendung eines Segmentrings (25) nach einem der Ansprüche 1 bis 11, einer Segmentringanordnung nach Anspruch 12 oder 13 oder eines Turbinenmoduls gemäß Anspruch 14 in einer Strömungsmaschine (1), insbesondere in einem Strahltriebwerk.Use of a segment ring (25) according to one of claims 1 to 11, a segment ring arrangement according to claim 12 or 13 or a turbine module according to claim 14 in a turbomachine (1), in particular in a jet engine.
EP19182753.4A 2018-06-28 2019-06-27 Segment ring for mounting in a turbomachine Active EP3587741B1 (en)

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113898420A (en) * 2021-10-10 2022-01-07 中国航发沈阳发动机研究所 Compressor stator inner ring and stator structure thereof

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1431518A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment assembly with a surface-recessed seal bridging adjacent shroud segments
EP1431515A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment and assembly with circumferential seal on a planar segment surface
WO2012041651A1 (en) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Blade ring segment, turbomachine and method for producing same
EP2857639A1 (en) * 2013-10-01 2015-04-08 Siemens Aktiengesellschaft Sealing ring

Family Cites Families (107)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE21272E (en) * 1939-11-21 hallerberg
BE514728A (en) * 1951-10-10
GB750397A (en) * 1951-12-10 1956-06-13 Power Jets Res & Dev Ltd Damped turbine and dynamic compressor blades
US2835515A (en) * 1955-12-05 1958-05-20 Crane Packing Co Rotary mechanical seal with self-locking seat
US3303992A (en) * 1965-03-03 1967-02-14 Gen Motors Corp Variable vane stator ring
US3487879A (en) * 1967-08-02 1970-01-06 Dowty Rotol Ltd Blades,suitable for propellers,compressors,fans and the like
US3728041A (en) * 1971-10-04 1973-04-17 Gen Electric Fluidic seal for segmented nozzle diaphragm
GB1387866A (en) * 1972-06-21 1975-03-19 Rolls Royce Aerofoil members for gas turbine engines
JPS5421900B2 (en) * 1973-02-15 1979-08-02
US3870434A (en) * 1973-12-21 1975-03-11 Gen Electric Gear arrangement for variable pitch fan
US3887297A (en) * 1974-06-25 1975-06-03 United Aircraft Corp Variable leading edge stator vane assembly
US4047840A (en) * 1975-05-29 1977-09-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Impact absorbing blade mounts for variable pitch blades
US3970318A (en) * 1975-09-26 1976-07-20 General Electric Company Sealing means for a segmented ring
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
US4363600A (en) * 1981-04-06 1982-12-14 General Motors Corporation Variable vane mounting
FR2524934B1 (en) * 1982-04-08 1986-12-26 Snecma SAFETY STOP DEVICE FOR VARIABLE SETTING STATOR BLADE PIVOT
US4498790A (en) * 1983-11-21 1985-02-12 United Technologies Corporation Bushing securing apparatus
FR2556410B1 (en) * 1983-12-07 1986-09-12 Snecma DEVICE FOR CENTERING THE INSIDE RING OF A VARIABLE TIMING FINS STATOR
FR2582720B1 (en) * 1985-05-29 1989-06-02 Snecma PROCESS FOR PRODUCING A TURBOMACHINE BLADE PIVOT AND A STATOR BLADE COMPRISING SAME
DE3718678A1 (en) * 1987-06-04 1988-12-22 Mtu Muenchen Gmbh FIBER TECHNICAL COMPRESSOR VAN
GB2210935B (en) * 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US5102302A (en) * 1988-06-02 1992-04-07 General Electric Company Fan blade mount
US5165856A (en) * 1988-06-02 1992-11-24 General Electric Company Fan blade mount
US4897021A (en) * 1988-06-02 1990-01-30 United Technologies Corporation Stator vane asssembly for an axial flow rotary machine
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
US4990056A (en) * 1989-11-16 1991-02-05 General Motors Corporation Stator vane stage in axial flow compressor
US5205714A (en) * 1990-07-30 1993-04-27 General Electric Company Aircraft fan blade damping apparatus
IE67360B1 (en) * 1990-09-25 1996-03-20 United Technologies Corp Apparatus and method for a stator assembly of a rotary machine
US5259728A (en) * 1992-05-08 1993-11-09 General Electric Company Bladed disk assembly
FR2691507B1 (en) * 1992-05-20 1994-07-08 Snecma WATERPROOFING STRUCTURE FOR A PIVOTING VANE OF A TURBOMACHINE.
USD341145S (en) * 1992-09-14 1993-11-09 Esworthy S James Bushing
EP0591565B1 (en) * 1992-10-05 1996-01-24 Asea Brown Boveri Ag Stator blade fastening for axial through-flow turbomachines
US5517817A (en) * 1993-10-28 1996-05-21 General Electric Company Variable area turbine nozzle for turbine engines
FR2723614B1 (en) * 1994-08-10 1996-09-13 Snecma DEVICE FOR ASSEMBLING A CIRCULAR STAGE OF PIVOTING VANES.
US5653580A (en) * 1995-03-06 1997-08-05 Solar Turbines Incorporated Nozzle and shroud assembly mounting structure
FR2742799B1 (en) * 1995-12-20 1998-01-16 Snecma INTERNAL END END OF PIVOTING VANE
US7059827B1 (en) * 1996-05-31 2006-06-13 Watson Cogeneration Company Turbine power plant having minimal-contact brush seal augmented labyrinth seal
US5664536A (en) * 1996-08-14 1997-09-09 Brunswick Corporation Self-locating piston ring for a two-stroke engine
US6318728B1 (en) * 1997-07-11 2001-11-20 Demag Delaval Turbomachinery Corporation Brush-seal designs for elastic fluid turbines
FR2775731B1 (en) * 1998-03-05 2000-04-07 Snecma CIRCULAR STAGE OF BLADES AT INTERIOR ENDS JOINED BY A CONNECTING RING
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane
US6257593B1 (en) * 1999-05-14 2001-07-10 Patrick Michel White Stress induced interposed connector
US6435519B1 (en) * 1999-05-14 2002-08-20 Patrick Michel White Stress-induced gasket
US6550779B2 (en) * 1999-07-27 2003-04-22 Northeast Equipment, Inc. Mechanical split seal
US6637995B1 (en) * 2000-02-09 2003-10-28 Patrick Michel White Super-elastic rivet assembly
US6457721B1 (en) * 2001-01-26 2002-10-01 White Consolidated Industries, Inc. Piston ring locator
US6481960B2 (en) * 2001-03-30 2002-11-19 General Electric Co. Variable gas turbine compressor vane structure with sintered-and-infiltrated bushing and washer bearings
US6682299B2 (en) * 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
DE10161292A1 (en) * 2001-12-13 2003-06-26 Rolls Royce Deutschland Bearing ring for the storage of blade roots of adjustable stator blades in the high pressure compressor of a gas turbine
USD517900S1 (en) * 2002-04-04 2006-03-28 420820 Ontario Limited Bushing
US6733233B2 (en) * 2002-04-26 2004-05-11 Pratt & Whitney Canada Corp. Attachment of a ceramic shroud in a metal housing
US6877952B2 (en) * 2002-09-09 2005-04-12 Florida Turbine Technologies, Inc Passive clearance control
US7360990B2 (en) * 2004-10-13 2008-04-22 General Electric Company Methods and apparatus for assembling gas turbine engines
FR2882578B1 (en) * 2005-02-25 2007-05-25 Snecma Moteurs Sa DEVICE FOR ADJUSTING THE CENTERING OF A SYNCHRONIZATION RING FOR THE CONTROL OF TURBOMACHINE SWIVELING BLADES
US7334980B2 (en) * 2005-03-28 2008-02-26 United Technologies Corporation Split ring retainer for turbine outer air seal
FR2889242B1 (en) * 2005-07-27 2007-11-02 Snecma SOCKET FOR VANE PIVOT WITH VARIABLE SETTING ANGLE FOR TURBOMACHINE
US7510369B2 (en) * 2005-09-02 2009-03-31 United Technologies Corporation Sacrificial inner shroud liners for gas turbine engines
FR2890707B1 (en) * 2005-09-14 2007-12-14 Snecma SOCKET FOR VANE PIVOT WITH VARIABLE SETTING ANGLE FOR TURBOMACHINE
US7427187B2 (en) * 2006-01-13 2008-09-23 General Electric Company Welded nozzle assembly for a steam turbine and methods of assembly
FR2902822B1 (en) * 2006-06-21 2008-08-22 Snecma Sa STATOR BEARING FOR STATOR WITH VARIABLE SHAFT
US20080044284A1 (en) * 2006-08-16 2008-02-21 United Technologies Corporation Segmented fluid seal assembly
US9353643B2 (en) * 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
USD681512S1 (en) * 2009-05-19 2013-05-07 Larry John Verbowski Suspension module
US8328512B2 (en) * 2009-06-05 2012-12-11 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
US8448993B2 (en) * 2009-06-12 2013-05-28 Romac Industries, Inc. Pipe coupling
US8740551B2 (en) * 2009-08-18 2014-06-03 Pratt & Whitney Canada Corp. Blade outer air seal cooling
EP2336572B1 (en) * 2009-12-14 2012-07-25 Techspace Aero S.A. Shroud or section of shroud in two parts for a vane diffuser of an axial compressor
US8491267B2 (en) * 2010-08-27 2013-07-23 Pratt & Whitney Canada Corp. Retaining ring arrangement for a rotary assembly
US8770930B2 (en) * 2011-02-09 2014-07-08 Siemens Energy, Inc. Joining mechanism and method for interlocking modular turbine engine component with a split ring
DE102012005771B4 (en) * 2011-03-25 2022-06-30 General Electric Technology Gmbh Sealing device for rotating turbine blades
EP2520769A1 (en) * 2011-05-02 2012-11-07 MTU Aero Engines GmbH Inner ring for forming a guide vane assembly, guide vane assembly and fluid flow engine
US20120319360A1 (en) * 2011-06-20 2012-12-20 Blaney Ken F Plug assembly for blade outer air seal
EP2644833A1 (en) * 2012-03-26 2013-10-02 Alstom Technology Ltd Holder ring
US9874243B2 (en) * 2012-12-11 2018-01-23 Rotacaster Wheel Limited Axel bush
US9932988B2 (en) * 2013-02-15 2018-04-03 United Technologies Corporation Bushing arranged between a body and a shaft, and connected to the shaft
US9500095B2 (en) * 2013-03-13 2016-11-22 Pratt & Whitney Canada Corp. Turbine shroud segment sealing
FR3009335B1 (en) * 2013-07-30 2015-09-04 Snecma TURBOMACHINE VARIABLE ROTATION ANGLE RECTIFIER AUB GUIDING DEVICE
US10385719B2 (en) * 2013-08-28 2019-08-20 United Technologies Corporation Variable vane bushing
EP2846001B1 (en) * 2013-09-06 2023-01-11 MTU Aero Engines AG Assembly and disassembly methods of a rotor of a gas turbine and corresponding tool
US9546559B2 (en) * 2013-10-08 2017-01-17 General Electric Company Lock link mechanism for turbine vanes
EP3071794B8 (en) * 2013-11-19 2021-04-07 Raytheon Technologies Corporation Multi-element inner shroud extension for a turbo-machine
FR3014152B1 (en) * 2013-11-29 2015-12-25 Snecma TURBOMACHINE VARIABLE CALIBRATION ANGLE RECTIFIER AUB GUIDING DEVICE AND METHOD OF ASSEMBLING SUCH A DEVICE
JP6118721B2 (en) * 2013-12-20 2017-04-19 株式会社Ihi Fan case and manufacturing method of fan case
FR3019597B1 (en) * 2014-04-08 2016-03-25 Turbomeca TURBOMACHINE COMPRESSOR WITH VARIABLE SHIFT AUBES
US10088049B2 (en) * 2014-05-06 2018-10-02 United Technologies Corporation Thermally protected seal assembly
DE102014209057A1 (en) * 2014-05-14 2015-11-19 MTU Aero Engines AG Gas turbine casing assembly
GB201419965D0 (en) * 2014-10-06 2014-12-24 Rolls Royce Plc Fan
US10184356B2 (en) * 2014-11-25 2019-01-22 United Technologies Corporation Blade outer air seal support structure
US10370998B2 (en) * 2015-05-26 2019-08-06 Rolls-Royce Corporation Flexibly mounted ceramic matrix composite seal segments
US11156117B2 (en) 2016-04-25 2021-10-26 Raytheon Technologies Corporation Seal arc segment with sloped circumferential sides
FR3051174B1 (en) * 2016-05-10 2018-06-01 Safran Aircraft Engines FRONT ROTATING PART OF AN AIRCRAFT TURBOMACHINE RECEIVER WITH IMPROVED DESIGN FOR RELEASE OF THE CONE TIP
US10415415B2 (en) * 2016-07-22 2019-09-17 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
US9869206B2 (en) * 2016-06-21 2018-01-16 United Technologies Corporation Securing a centering spring to a static structure with mounting tabs
US10626743B2 (en) * 2016-06-30 2020-04-21 General Electric Company Segmented face seal assembly and an associated method thereof
US10344622B2 (en) * 2016-07-22 2019-07-09 United Technologies Corporation Assembly with mistake proof bayoneted lug
US20180045218A1 (en) * 2016-08-11 2018-02-15 United Technologies Corporation Shim for gas turbine engine
US11181002B2 (en) * 2016-09-29 2021-11-23 General Electric Company Turbine systems with sealing components
US10344612B2 (en) * 2017-01-13 2019-07-09 United Technologies Corporation Compact advanced passive tip clearance control
US10428689B2 (en) * 2017-05-17 2019-10-01 Rolls-Royce Deutschland Ltd & Co Kg Heat shield for a gas turbine engine
US10533441B2 (en) * 2017-06-02 2020-01-14 Rolls-Royce Corporation Floating interstage seal assembly
US10954809B2 (en) * 2017-06-26 2021-03-23 Rolls-Royce High Temperature Composites Inc. Ceramic matrix full hoop blade track
US11047481B2 (en) * 2017-09-06 2021-06-29 General Electric Company Seal assembly for a rotary machine
US10989058B2 (en) * 2018-04-19 2021-04-27 General Electric Company Segmented piston seal system
DE102018210600A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG COAT RING ARRANGEMENT FOR A FLOWING MACHINE
US11131204B2 (en) * 2018-08-21 2021-09-28 General Electric Company Additively manufactured nested segment assemblies for turbine engines
US10920618B2 (en) * 2018-11-19 2021-02-16 Raytheon Technologies Corporation Air seal interface with forward engagement features and active clearance control for a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1431518A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment assembly with a surface-recessed seal bridging adjacent shroud segments
EP1431515A2 (en) * 2002-12-20 2004-06-23 General Electric Company Turbine engine shroud segment and assembly with circumferential seal on a planar segment surface
WO2012041651A1 (en) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Blade ring segment, turbomachine and method for producing same
EP2857639A1 (en) * 2013-10-01 2015-04-08 Siemens Aktiengesellschaft Sealing ring

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ES2887231T3 (en) 2021-12-22
US20200003067A1 (en) 2020-01-02
DE102018210601A1 (en) 2020-01-02
US11125097B2 (en) 2021-09-21

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