EP3587741A1 - Segment ring for mounting in a turbomachine - Google Patents
Segment ring for mounting in a turbomachine Download PDFInfo
- 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
- Authority
- 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
Links
- 238000007789 sealing Methods 0.000 claims abstract description 43
- 238000009434 installation Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 230000000295 complement effect Effects 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000009760 electrical discharge machining Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000004519 grease Substances 0.000 description 1
- 230000012447 hatching Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 238000012805 post-processing Methods 0.000 description 1
- 230000011218 segmentation Effects 0.000 description 1
Images
Classifications
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- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
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- 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
-
- 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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- 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
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- 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
- F05D2240/00—Components
- F05D2240/55—Seals
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
Die vorliegende Erfindung betrifft einen Segmentring zur Montage in einer Strömungsmaschine.The present invention relates to a segment ring for mounting in a turbomachine.
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).
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.
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.
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.
- 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.
Zur Montage des Mantelringsegments 22 an dem Gehäuseteil 21 ist ein Segmentring 25 vorgesehen, der in Umlaufrichtung in eine Mehrzahl Segmente untergliedert ist (vgl.
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
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
Claims (15)
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).
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).
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DE102018210601.0A DE102018210601A1 (en) | 2018-06-28 | 2018-06-28 | SEGMENT RING FOR ASSEMBLY IN A FLOWING MACHINE |
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US (1) | US11125097B2 (en) |
EP (1) | EP3587741B1 (en) |
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---|---|---|---|---|
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)
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 |
-
2018
- 2018-06-28 DE DE102018210601.0A patent/DE102018210601A1/en active Pending
-
2019
- 2019-06-26 US US16/453,093 patent/US11125097B2/en active Active
- 2019-06-27 ES ES19182753T patent/ES2887231T3/en active Active
- 2019-06-27 EP EP19182753.4A patent/EP3587741B1/en active Active
Patent Citations (4)
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 |
Also Published As
Publication number | Publication date |
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EP3587741B1 (en) | 2021-08-11 |
ES2887231T3 (en) | 2021-12-22 |
US20200003067A1 (en) | 2020-01-02 |
DE102018210601A1 (en) | 2020-01-02 |
US11125097B2 (en) | 2021-09-21 |
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