EP2826962B1 - Turboengine with sealing segments and guide vane segments - Google Patents

Turboengine with sealing segments and guide vane segments Download PDF

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Publication number
EP2826962B1
EP2826962B1 EP13176503.4A EP13176503A EP2826962B1 EP 2826962 B1 EP2826962 B1 EP 2826962B1 EP 13176503 A EP13176503 A EP 13176503A EP 2826962 B1 EP2826962 B1 EP 2826962B1
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EP
European Patent Office
Prior art keywords
sealing
segments
segment
row
vane
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.)
Active
Application number
EP13176503.4A
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German (de)
French (fr)
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EP2826962A1 (en
Inventor
Walter Gieg
Petra Kufner
Rudolf Stanka
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to ES13176503.4T priority Critical patent/ES2581511T3/en
Priority to EP13176503.4A priority patent/EP2826962B1/en
Priority to US14/329,570 priority patent/US9982566B2/en
Publication of EP2826962A1 publication Critical patent/EP2826962A1/en
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Publication of EP2826962B1 publication Critical patent/EP2826962B1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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

Definitions

  • the invention relates to a turbomachine according to the preamble of patent claim 1.
  • a sealing segment ring For sealing a radial gap between blade tips of a blade row and a blade section surrounding a turbine section of a turbomachine such as a gas turbine usually a sealing segment ring is provided, which extends on the housing side between a front blade row and a rear blade row.
  • the sealing segment ring consists of a plurality of identical sealing segments, each having a plurality of slots for positive engagement with an equal number of protrusions of the front guide blade row for circumferential securing at its front edge portion.
  • the vane rows consist of a plurality of identical vane segments, wherein in this type of circumferential securing the number of sealing segments is equal to the number of front vane segments or the front vane segments are an integer multiple of the sealing segments. With 15 vane segments, there are usually 15, 5 or 3 sealing segments. In the US 2005002779 A1 Such a circumferential securing in the region of a rear edge portion of the sealing segments and a rear vane row is shown.
  • the object of the invention is to provide a turbomachine with a circumferential securing a sealing segment ring with an alternative sealing segment number for sealing a radial gap between a housing portion and a blade row.
  • a turbomachine according to the invention has a sealing segment ring between a front row of vanes and a rear row of vanes for sealing a radial gap between a housing portion and a row of blades revolving between the rows of vanes.
  • the sealing segment ring has a plurality of identical sealing segments and at least one of the rows of stator blades has a plurality of identical vane segments.
  • the sealing segments each have a plurality of circumferentially adjacent receptacles for cooperation with securing elements of this guide blade row, wherein the receptacles and securing elements are distributed uniformly over the circumference and the receptacles are a multiple of the securing elements, and each vane segment of this vane row has a securing element.
  • the invention enables circumferential securing and the formation of a sealing segment ring whose sealing segment number is not an integral subset of a number of vane segments. With 15 vane segments, for example, 10 sealing segments can be realized thanks to the invention. The number of sealing segments can thus be determined optimally according to structure-mechanical, manufacturing-technical and / or cost-related aspects. Because the receptacles are a multiple of the securing elements, not all receptacles are in the mounted state in engagement with the securing elements and can thus serve to equalize different thermal expansion behavior of the sealing segments and the vane segments.
  • each sealing segment is merely connected to a vane segment of this vane row by means of a receiving-securing element engagement.
  • a receiving-securing element engagement By only one positive connection per sealing segment and vane segment jamming of the components is prevented during assembly.
  • each sealing segment has a same plurality of receptacles and these and the securing elements are arranged at identical positions of the sealing segments or the guide blade segments.
  • the production of the sealing segments and of the guide blade segments is simplified by the respective same arrangement of the receptacles and securing elements.
  • the securing element of the respective vane segment and the receptacles of the respective sealing segment are arranged symmetrically to the respective segment longitudinal axis.
  • 1.5 times as many vane segments of the vane row as sealing segments and per sealing segment three times as many receptacles as securing elements per vane segment are provided.
  • every second receptacle is in engagement with a securing element or the receptacles are alternately occupied by a respective securing element.
  • the recordings are in alternating engagement with a securing element. The double intervention here must be taken into account when designing tolerances and thermal expansion forces.
  • An inventive sealing segment for a turbomachine according to the invention has a plurality of circumferentially uniformly spaced apart receptacles for cooperation with a corresponding securing element.
  • An inventive vane segment for a turbomachine according to the invention has only one securing element for cooperating with a corresponding receiving a sealing segment.
  • a turbomachine 1 viewed in the direction of a hot gas flowing through a hot gas channel 2, has a front stator-side guide blade row 4 and a rear stator-side stator blade row 6, between which a rotor-side blade row 8 rotates about a rotor axis (not shown).
  • the blade row 8 is encompassed by a housing portion 10 of the turbomachine 1, wherein a sealing segment ring 12 is arranged for sealing a radial gap between the blade row 8 and the housing portion 10 between the guide blade rows 4, 6.
  • the turbomachine is in particular a gas turbine and preferably an aircraft engine.
  • the blade rows 4, 6, 8 and the sealing segment ring 12 are preferably located in the low-pressure turbine of the turbomachine 1.
  • the front vane row 4 has a plurality of identical vane segments 14, each having a plurality of airfoils and by means of a front holding portion 16 and a rear holding portion 18 positively engage in housing grooves 20 and the like of the turbomachine 1.
  • the rear vane row 6 has a plurality of identical vane segments 22, which cooperate in a form-fitting manner via front holder sections 24 and rear holding sections, not shown, with housing grooves 26 and the like of the turbomachine 1.
  • the sealing segment ring 12 has a plurality of identical sealing segments 28, each having a multi-angled base body 30, on whose the hot gas channel 2 facing inner surface sealing honeycomb 32 for running in opposite sealing webs 34, 36 of the blade row 8 are arranged.
  • the sealing segment ring 12 and the sealing webs 34, 36 form the so-called Outer Air Seal (OAS).
  • OAS Outer Air Seal
  • each base body 30 With its front edge portion 38 and its rear edge portion 40, each base body 30 is in axial overlap with platform overhangs 42, 44 of the vane segments 14, 22.
  • Die Platform overhangs 40, 42 are guided over the respective edge section 38, 40 or the edge sections 38, 40 are guided under the respective platform overhang 42, 44.
  • the edge sections 38, 40 are thus arranged radially outside the platform overhangs 40, 42.
  • the front guide blade segments 14 each have a securing element, which in the embodiment shown here is a securing web 46, with which the sealing segments 28 cooperate positively.
  • the securing webs 46 each extend at a distance from the platform along a rear side 48 of the rear holder section 18 of the respective guide blade segment 14 radially outward.
  • the sealing segments 28 each have a plurality of receptacles, which are formed in the embodiment shown here as slots 50.
  • the slots 50 are opened upstream and respectively pass through the front edge portion 38 of the base body 30.
  • Each vane segment 14a, 14b, 14c, 14d has a single securing leg 46a, 46b, 46c, 46d positioned circumferentially centrally on the back 48 of the rear retaining sections 18 in the embodiment shown here.
  • the position of the securing bar 46a, 46b is not limited to a center position.
  • the securing webs 46a, 46b, 46c, 46d are located at identical positions of the vane segments 14a, 14b, 14c, 14d. A circumferential distance to both side edges 52, 54 of the holding portion 18 is thus equal.
  • the respective single securing web 46a, 46b, 46c, 46d per vane segment 14a, 14b, 14c, 14d lies on a longitudinal axis of the respective vane segment 14a, 14b, 14c, 14d which extends approximately in the flow direction of the hot gas and is therefore symmetrical in the circumferential direction to the longitudinal axis oriented. Viewed over the circumference of the guide blade row 4, the securing webs 46a, 46b, 46c, 46d are uniformly spaced from one another.
  • the sealing segments 28a, 28b, 28c each have three slots 50a, 56a, 58a and 50b, 56b, 58b and 50c, respectively FIG. 2 for distinguishing dividing lines 60, 62, 64, 66 between adjacent sealing segments 28a, 28b, 28c and adjacent vane segments 14a, 14b, 14c, 14d are shown as dots. Due to the detail in FIG. 2 Of the three slots of the sealing segment 28c, only the slot 50c is visible.
  • the slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are at identical positions of the sealing segments 28a, 28b, 28c.
  • the number of slots 50a, 56a, 58a or 50b, 56b, 58b and 50c per sealing segment 28a, 28b, 28c (here three slots 50, 56, 58 per sealing segment 28) is thus an integer multiple of the number of securing webs 46a, 46b, 46c, 46d per vane segment 14a, 14b, 14c, 14d (here one securing ridge 46 per vane segment 14).
  • the slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are circumferentially symmetrical to the longitudinal axis of the sealing segments 28a, 28b, 28c extending approximately in the direction of flow of the hot gas.
  • a slot 56a, 56b lies directly on the longitudinal axis and is located at the same circumferential distance from side edges 68, 70 of the respective sealing segment 28a, 28b, 28c.
  • the two other slots 50a, 58a and 50b, 58b and 50c is located on both sides of the respective central slot 56a, 56b.
  • lateral slots 50a, 58a and 50b, 58b and 50c are located at an equal circumferential distance from the central slot 56a, 56b and thus at an equal circumferential distance to the respective adjacent side edge 68, 70.
  • the lateral slots 50a, 58a or 50b, 58b and 50c are also at an equal circumferential distance from the respective side edge 70, 68.
  • the slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are equally spaced from each other.
  • the circumferential distance of the lateral slots 50a, 58a or 50b, 58b and 50c to the central slot 56a, 56b is twice as large in the embodiment shown here as the circumferential distance to the respective adjacent side edge 68, 70th
  • the sealing segments 28a, 28b, 28c have a greater extent in the circumferential direction than the vane segments 14a, 14b, 14c, 14d, so that the parting lines 60, 62 between the sealing segments 28a, 28b, 28c are circumferentially offset from the parting lines 64, 66 of the vane segments 14a , 14b, 14c, 14d are arranged.
  • a sealing segment 28a, 28b, 28c has 1.5 times the circumferential extent as a Leitschaufelsegment14a, 14b, 14c, 14d.
  • each second slot 50a, 58a, 56b, 50c of the sealing segment ring 12 is in engagement with a securing web 46a, 46b, 46c, 46d.
  • every second slot 56a, 50b, 58b is free.
  • the securing web 46a engages in the slot 50a, the securing web 46b in the slot 58a, the securing web 46c in the slot 56b and the securing web 46d in the slot 50c.
  • the slots 56a, 50b and 58b are not occupied.
  • each vane segment 14a, 14b, 14c, 14d has only one securing web 46a, 46b, 46c, 46d, each vane segment 14a, 14b, 14c, 14d forms only a form-locking connection with a sealing segment 28a, 28b, 28c or only one circumferential securing device for a sealing segment 28a, 28b, 28c.
  • sealing segments 28a with multiple vane segments 14a, 14b are in positive engagement at the same time.
  • the securing webs 46a, 46b of the guide blade segments 14a, 14b engage in a form-fitting manner in the slots 50a, 58a of the sealing segment 28a.
  • a turbomachine having a sealing segment ring between a front row of vanes and a rear row of vanes for sealing a radial gap between a housing portion and a row of blades revolving between the rows of vanes, the sealing segment ring having a plurality of like sealing segments and at least one of the plurality of vanes having a plurality of like vane segments, wherein the sealing segments each have a plurality of circumferentially adjacent receptacles for interacting with securing elements of this guide vane row, wherein the receptacles and securing elements are distributed uniformly over the circumference and the receptacles are a multiple of the securing elements, a sealing segment and a vane segment.

Description

Die Erfindung betrifft eine Strömungsmaschine nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a turbomachine according to the preamble of patent claim 1.

Zur Abdichtung eines Radialspaltes zwischen Schaufelspitzen einer Laufschaufelreihe und einem die Laufschaufelreihe umgebenden Gehäuseabschnittes einer Strömungsmaschine wie eine Gasturbine ist gewöhnlich ein Dichtsegmentenring vorgesehen, der sich gehäuseseitig zwischen einer vorderen Laufschaufelreihe und einer hinteren Laufschaufelreihe erstreckt. Bei einer bekannten Abdichtung besteht der Dichtsegmentenring aus einer Vielzahl von gleichen Dichtsegmenten, die zur Umfangssicherung an ihrem vorderen Randabschnitt jeweils eine Vielzahl von Schlitzen zum formschlüssigen Zusammenwirken mit einer gleichen Anzahl von Vorsprüngen der vorderen Leitschaufelreihe aufweist. Die Leitschaufelreihen bestehen aus einer Vielzahl von gleichen Leitschaufelsegmenten, wobei bei dieser Art der Umfangssicherung die Anzahl der Dichtsegmente gleich der Anzahl der vorderen Leitschaufelsegmente ist bzw. die vorderen Leitschaufelsegmente ein ganzzahliges Vielfaches der Dichtsegmente sind. Bei 15 Leitschaufelsegmenten liegen also gewöhnlich 15, 5 oder 3 Dichtsegmente vor. In der US 2005002779 A1 ist eine derartige Umfangssicherung im Bereich eines hinteren Randabschnitts der Dichtsegmente und einer hinteren Leitschaufelreihe gezeigt.For sealing a radial gap between blade tips of a blade row and a blade section surrounding a turbine section of a turbomachine such as a gas turbine usually a sealing segment ring is provided, which extends on the housing side between a front blade row and a rear blade row. In a known seal, the sealing segment ring consists of a plurality of identical sealing segments, each having a plurality of slots for positive engagement with an equal number of protrusions of the front guide blade row for circumferential securing at its front edge portion. The vane rows consist of a plurality of identical vane segments, wherein in this type of circumferential securing the number of sealing segments is equal to the number of front vane segments or the front vane segments are an integer multiple of the sealing segments. With 15 vane segments, there are usually 15, 5 or 3 sealing segments. In the US 2005002779 A1 Such a circumferential securing in the region of a rear edge portion of the sealing segments and a rear vane row is shown.

Aufgabe der Erfindung ist es, eine Strömungsmaschine mit einer Umfangssicherung eines Dichtsegmentenrings mit einer alternativen Dichtsegmentenanzahl zum Abdichten eines Radialspaltes zwischen einem Gehäuseabschnitt und einer Laufschaufelreihe zu schaffen.The object of the invention is to provide a turbomachine with a circumferential securing a sealing segment ring with an alternative sealing segment number for sealing a radial gap between a housing portion and a blade row.

Diese Aufgabe wird gelöst durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 1.This object is achieved by a turbomachine having the features of patent claim 1.

Eine erfindungsgemäße Strömungsmaschine hat einen Dichtsegmentenring zwischen einer vorderen Leitschaufelreihe und einer hinteren Leitschaufelreihe zum Abdichten eines Radialspaltes zwischen einem Gehäuseabschnitt und einer zwischen den Leitschaufelreihen umlaufenden Laufschaufelreihe. Der Dichtsegmentenring weist eine Vielzahl von gleichen Dichtsegmenten auf und zumindest eine der Leitschaufelreihen hat eine Vielzahl von gleichen Leitschaufelsegmenten. Erfindungsgemäß haben die Dichtsegmente jeweils mehrere in Umfangsrichtung nebeneinanderliegende Aufnahmen zum Zusammenwirken mit Sicherungselementen dieser Leitschaufelreihe, wobei die Aufnahmen und Sicherungselemente gleichmäßig über den Umfang verteilt sind und die Aufnahmen ein Vielfaches der Sicherungselemente sind, und jedes Leitschaufelsegment dieser Leitschaufelreihe mit ein Sicherungselement hat.A turbomachine according to the invention has a sealing segment ring between a front row of vanes and a rear row of vanes for sealing a radial gap between a housing portion and a row of blades revolving between the rows of vanes. The sealing segment ring has a plurality of identical sealing segments and at least one of the rows of stator blades has a plurality of identical vane segments. According to the invention, the sealing segments each have a plurality of circumferentially adjacent receptacles for cooperation with securing elements of this guide blade row, wherein the receptacles and securing elements are distributed uniformly over the circumference and the receptacles are a multiple of the securing elements, and each vane segment of this vane row has a securing element.

Die Erfindung ermöglicht die Umfangssicherung und die Bildung eines Dichtsegmentenringes, dessen Dichtsegmentenanzahl keine ganzzahlige Teilmenge einer Leitschaufelsegmentenanzahl ist. Bei 15 Leitschaufelsegmenten können dank der Erfindung beispielsweise 10 Dichtsegmente realisiert werden. Die Anzahl der Dichtsegmente kann somit optimal nach strukturmechanischen, fertigungstechnischen und/oder kostenbezogenen Aspekten bestimmt werden. Dadurch, dass die Aufnahmen ein Vielfaches der Sicherungselemente sind, befinden sich im montierten Zustand nicht alle Aufnahmen im Eingriff mit den Sicherungselementen und können so zur Vergleichmäßigung von unterschiedlichen Wärmeausdehnungsverhalten der Dichtsegmente und der Leitschaufelsegmente dienen.The invention enables circumferential securing and the formation of a sealing segment ring whose sealing segment number is not an integral subset of a number of vane segments. With 15 vane segments, for example, 10 sealing segments can be realized thanks to the invention. The number of sealing segments can thus be determined optimally according to structure-mechanical, manufacturing-technical and / or cost-related aspects. Because the receptacles are a multiple of the securing elements, not all receptacles are in the mounted state in engagement with the securing elements and can thus serve to equalize different thermal expansion behavior of the sealing segments and the vane segments.

Die Leitschaufelsegmente der relevanten Leitschaufelreihe haben nur ein Sicherungselement. Hierdurch ist jedes Dichtsegment lediglich mittels eines Aufnahme-Sicherungselementen-Eingriffs mit einem Leitschaufelsegment dieser Leitschaufelreihe verbunden. Durch lediglich eine Formschlussverbindung pro Dichtsegment und Leitschaufelsegment wird ein Verklemmen der Bauteile bei der Montage verhindert. Ebenso können durch die Einfachverbindung pro Dichtsegment und Leitschaufelsegment unterschiedliche Wärmeausdehnungen der Bauteile noch besser berücksichtig.The vane segments of the relevant vane row have only one fuse element. As a result, each sealing segment is merely connected to a vane segment of this vane row by means of a receiving-securing element engagement. By only one positive connection per sealing segment and vane segment jamming of the components is prevented during assembly. Likewise, due to the single connection per sealing segment and guide blade segment, different thermal expansions of the components can be taken into account even better.

Um die Leitschaufelsegmente dieser Leitschaufelreihe und die Dichtsegmente an einer beliebigen Umfangsposition montieren zu können ist es vorteilhaft, wenn jedes Dichtsegment eine gleiche Vielzahl von Aufnahmen aufweist und diese sowie die Sicherungselemente an identischen Positionen der Dichtsegmente bzw. der Leitschaufelsegmente angeordnet sind. Gleichzeitig wird durch die jeweilige gleiche Anordnung der Aufnahmen und Sicherungselemente die Herstellung der Dichtsegmente und die der Leitschaufelsegmente vereinfacht.In order to mount the guide blade segments of this guide blade row and the sealing segments at any circumferential position, it is advantageous if each sealing segment has a same plurality of receptacles and these and the securing elements are arranged at identical positions of the sealing segments or the guide blade segments. At the same time, the production of the sealing segments and of the guide blade segments is simplified by the respective same arrangement of the receptacles and securing elements.

Bei einem Ausführungsbeispiel sind das Sicherungselement des jeweiligen Leitschaufelsegmentes und die Aufnahmen des jeweiligen Dichtsegmentes symmetrisch zur jeweiligen Segmentenlängsachse angeordnet.In one embodiment, the securing element of the respective vane segment and the receptacles of the respective sealing segment are arranged symmetrically to the respective segment longitudinal axis.

Bei einem bevorzugten Ausführungsbeispiel sind 1,5mal so viele Leitschaufelsegmente der Leitschaufelreihe wie Dichtsegmente und pro Dichtsegment dreimal so viele Aufnahmen wie Sicherungselemente pro Leitschaufelsegment vorgesehen. Hierdurch befindet sich jede zweite Aufnahme im Eingriff mit einem Sicherungselement bzw. die Aufnahmen sind abwechselnd mit jeweils einem Sicherungselement belegt. Über den Umfang betrachtet befinden sich die Aufnahmen in alternierendem Eingriff mit einem Sicherungselement. Der hier doppelte Eingriff ist bei der Auslegung von Toleranzen und Wärmedehngen zu berücksichtigen.In a preferred embodiment, 1.5 times as many vane segments of the vane row as sealing segments and per sealing segment three times as many receptacles as securing elements per vane segment are provided. As a result, every second receptacle is in engagement with a securing element or the receptacles are alternately occupied by a respective securing element. Viewed over the circumference, the recordings are in alternating engagement with a securing element. The double intervention here must be taken into account when designing tolerances and thermal expansion forces.

Ein erfindungsgemäßes Dichtsegment für eine erfindungsgemäße Strömungsmaschine hat eine Vielzahl von in Umfangsrichtung gleichmäßig voneinander beabstandeten Aufnahmen zum Zusammenwirken mit einer korrespondierenden Sicherungselement.An inventive sealing segment for a turbomachine according to the invention has a plurality of circumferentially uniformly spaced apart receptacles for cooperation with a corresponding securing element.

Ein erfindungsgemäßes Leitschaufelsegment für eine erfindungsgemäße Strömungsmaschine hat nur ein Sicherungselement zum Zusammenwirken mit einer korrespondierenden Aufnahme eines Dichtsegmentes.An inventive vane segment for a turbomachine according to the invention has only one securing element for cooperating with a corresponding receiving a sealing segment.

Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the invention are the subject of further subclaims.

Im Folgenden wird ein bevorzugtes Ausführungsbeispiel der Erfindung anhand schematischer Darstellungen näher erläutert. Es zeigen

Figur 1
einen Längsschnitt durch einen radial äußeren Bereich einer Strömungsmaschine, und
Figur 2
ein formschlüssiges Zusammenwirken von Leitschaufelsegmenten und Dichtsegmenten basierend auf Figur 1.
In the following, a preferred embodiment of the invention is explained in more detail with reference to schematic representations. Show it
FIG. 1
a longitudinal section through a radially outer region of a turbomachine, and
FIG. 2
a positive interaction of vane segments and sealing segments based on FIG. 1 ,

Wie in Figur 1 gezeigt, hat eine erfindungsgemäße Strömungsmaschine 1 in Richtung eines einen Heißgaskanal 2 durchströmenden Heißgases betrachtet eine vordere statorseitige Leitschaufelreihe 4 und eine hintere statorseitige Leitschaufelreihe 6, zwischen denen eine rotorseitige Laufschaufelreihe 8 um eine nicht gezeigte Rotorachse umläuft. Die Laufschaufelreihe 8 ist von einem Gehäuseabschnitt 10 der Strömungsmaschine 1 umgriffen, wobei zum Abdichten eines Radialspaltes zwischen der Laufschaufelreihe 8 und dem Gehäuseabschnitt 10 zwischen den Leitschaufelreihen 4, 6 ein Dichtsegmentenring 12 angeordnet ist. Die Strömungsmaschine ist insbesondere eine Gasturbine und bevorzugterweise ein Flugtriebwerk. Die Schaufelreihen 4, 6, 8 sowie der Dichtsegmentenring 12 befinden sich bevorzugterweise in der Niederdruckturbine der Strömungsmaschine 1.As in FIG. 1 A turbomachine 1 according to the invention, viewed in the direction of a hot gas flowing through a hot gas channel 2, has a front stator-side guide blade row 4 and a rear stator-side stator blade row 6, between which a rotor-side blade row 8 rotates about a rotor axis (not shown). The blade row 8 is encompassed by a housing portion 10 of the turbomachine 1, wherein a sealing segment ring 12 is arranged for sealing a radial gap between the blade row 8 and the housing portion 10 between the guide blade rows 4, 6. The turbomachine is in particular a gas turbine and preferably an aircraft engine. The blade rows 4, 6, 8 and the sealing segment ring 12 are preferably located in the low-pressure turbine of the turbomachine 1.

Die vordere Leitschaufelreihe 4 weist eine Vielzahl von gleichen Leitschaufelsegmenten 14 auf, die jeweils mehrere Schaufelblätter haben und mittels eines vorderen Halteabschnittes 16 und eines hinteren Halteabschnittes 18 formschlüssig in Gehäusenuten 20 und dergleichen der Strömungsmaschine 1 eingreifen. Ebenso weist die hintere Leitschaufelreihe 6 eine Vielzahl von gleichen Leitschaufelsegmenten 22 auf, die entsprechend über vorderen Halterabschnitte 24 und nicht gezeigte hintere Halteabschnitte mit Gehäusenuten 26 und dergleichen der Strömungsmaschine 1 formschlüssig zusammenwirken.The front vane row 4 has a plurality of identical vane segments 14, each having a plurality of airfoils and by means of a front holding portion 16 and a rear holding portion 18 positively engage in housing grooves 20 and the like of the turbomachine 1. Likewise, the rear vane row 6 has a plurality of identical vane segments 22, which cooperate in a form-fitting manner via front holder sections 24 and rear holding sections, not shown, with housing grooves 26 and the like of the turbomachine 1.

Der Dichtsegmentenring 12 hat eine Vielzahl von gleichen Dichtsegmenten 28, die jeweils einen mehrwinkeligen Grundkörper 30 aufweisen, an dessen dem Heißgaskanal 2 zugewandten Innenfläche Dichtwaben 32 zum Einlaufen von gegenüberliegenden Dichtstegen 34, 36 der Laufschaufelreihe 8 angeordnet sind. Der Dichtsegmentenring 12 und die Dichtstege 34, 36 bilden die sogenannte Outer Air Seal (OAS). Mit seinem vorderen Randabschnitt 38 und seinem hinteren Randabschnitt 40 befindet sich jeder Grundkörper 30 in axialer Überlappung mit Plattformüberhängen 42, 44 der Leitschaufelsegmente 14, 22. Die Plattformüberhänge 40, 42 sind über den jeweiligen Randabschnitt 38, 40 geführt bzw. die Randabschnitte 38, 40 sind unter den jeweiligen Plattformüberhang 42, 44 geführt. Die Randabschnitte 38, 40 sind somit radial außen zu den Plattformüberhängen 40, 42 angeordnet.The sealing segment ring 12 has a plurality of identical sealing segments 28, each having a multi-angled base body 30, on whose the hot gas channel 2 facing inner surface sealing honeycomb 32 for running in opposite sealing webs 34, 36 of the blade row 8 are arranged. The sealing segment ring 12 and the sealing webs 34, 36 form the so-called Outer Air Seal (OAS). With its front edge portion 38 and its rear edge portion 40, each base body 30 is in axial overlap with platform overhangs 42, 44 of the vane segments 14, 22. Die Platform overhangs 40, 42 are guided over the respective edge section 38, 40 or the edge sections 38, 40 are guided under the respective platform overhang 42, 44. The edge sections 38, 40 are thus arranged radially outside the platform overhangs 40, 42.

Zur Sicherung des Dichtsegmentenrings 12 in Umfangsrichtung zwischen den Leitschaufelreihen 4, 6 weisen die vorderen Leitschaufelsegmente 14 jeweils ein Sicherungselement auf, das in dem hier gezeigten Ausführungsbeispiel ein Sicherungssteg 46 ist, mit denen die Dichtsegmente 28 formschlüssig zusammenwirken. Die Sicherungsstege 46 erstrecken sich jeweils in einem Abstand zur Plattform entlang einer Rückseite 48 des hinteren Halterabschnittes 18 des jeweiligen Leitschaufelsegments 14 radial nach außen. Zum formschlüssigen Zusammenwirken mit den Sicherungsstegen 46 weisen die Dichtsegmente 28 jeweils mehrere Aufnahmen auf, die in dem hier gezeigten Ausführungsbeispiel als Schlitze 50 ausgebildet sind. Die Schlitze 50 sind stromaufwärts geöffnet und durchsetzen jeweils den vorderen Randabschnitt 38 der Grundkörper 30. Eine detaillierte Erläuterung der Umfangssicherung erfolgt in Figur 2 anhand von vier Leitschaufelsegmenten 14a, 14b, 14c, 14d und drei Dichtsegmenten 28a, 28b, 28c im Bereich der hinteren Halteabschnitte 18 und der vorderen Randabschnitte 38.To secure the sealing segment ring 12 in the circumferential direction between the guide blade rows 4, 6, the front guide blade segments 14 each have a securing element, which in the embodiment shown here is a securing web 46, with which the sealing segments 28 cooperate positively. The securing webs 46 each extend at a distance from the platform along a rear side 48 of the rear holder section 18 of the respective guide blade segment 14 radially outward. For positive engagement with the securing webs 46, the sealing segments 28 each have a plurality of receptacles, which are formed in the embodiment shown here as slots 50. The slots 50 are opened upstream and respectively pass through the front edge portion 38 of the base body 30. A detailed explanation of the circumferential securing takes place in FIG. 2 on the basis of four guide blade segments 14a, 14b, 14c, 14d and three sealing segments 28a, 28b, 28c in the region of the rear holding sections 18 and the front edge sections 38.

Jedes Leitschaufelsegment 14a, 14b, 14c, 14d weist einen einzigen Sicherungssteg 46a, 46b, 46c, 46d auf, der in dem hier gezeigten Ausführungsbeispiel in Umfangsrichtung mittig auf der Rückseite 48 der hinteren Halteabschnitte 18 positioniert ist. Die Position des Sicherungsstegs 46a, 46b ist natürlich nicht auf eine Mittenlage beschränkt. Die Sicherungsstege 46a, 46b, 46c, 46d liegen an identischen Positionen der Leitschaufelsegmente 14a, 14b, 14c, 14d. Ein Umfangabstand zu beiden Seitenkanten 52, 54 des Halteabschnittes 18 ist somit gleich. Der jeweils einzige Sicherungssteg 46a, 46b, 46c, 46d pro Leitschaufelsegment 14a, 14b, 14c, 14d liegt auf einer sich in etwa in Strömungsrichtung des Heißgases erstreckenden Längsachse des jeweiligen Leitschaufelsegmentes 14a, 14b, 14c, 14d und ist somit in Umfangsrichtung symmetrisch zur Längsachse orientiert. Über den Umfang der Leitschaufelreihe 4 betrachtet sind die Sicherungsstege 46a, 46b, 46c, 46d gleichmäßig voneinander beabstandet.Each vane segment 14a, 14b, 14c, 14d has a single securing leg 46a, 46b, 46c, 46d positioned circumferentially centrally on the back 48 of the rear retaining sections 18 in the embodiment shown here. Of course, the position of the securing bar 46a, 46b is not limited to a center position. The securing webs 46a, 46b, 46c, 46d are located at identical positions of the vane segments 14a, 14b, 14c, 14d. A circumferential distance to both side edges 52, 54 of the holding portion 18 is thus equal. The respective single securing web 46a, 46b, 46c, 46d per vane segment 14a, 14b, 14c, 14d lies on a longitudinal axis of the respective vane segment 14a, 14b, 14c, 14d which extends approximately in the flow direction of the hot gas and is therefore symmetrical in the circumferential direction to the longitudinal axis oriented. Viewed over the circumference of the guide blade row 4, the securing webs 46a, 46b, 46c, 46d are uniformly spaced from one another.

Die Dichtsegmente 28a, 28b, 28c haben jeweils drei Schlitze 50a, 56a, 58a bzw. 50b, 56b, 58b bzw. 50c, die in Figur 2 zur Unterscheidung von Trennfugen 60, 62, 64, 66 zwischen benachbarten Dichtsegmenten 28a, 28b, 28c und benachbarten Leitschaufelsegmenten 14a, 14b, 14c, 14d als Punkte dargestellt sind. Aufgrund des Ausschnitts in Figur 2 ist von den drei Schlitzen des Dichtsegments 28c lediglich der Schlitz 50c sichtbar. Die Schlitze 50a, 56a, 58a bzw. 50b, 56b, 58b bzw. 50c liegen an identischen Positionen der Dichtsegmente 28a, 28b, 28c. Die Anzahl der Schlitze 50a, 56a, 58a bzw. 50b, 56b, 58b bzw. 50c pro Dichtsegment 28a, 28b, 28c (hier drei Schlitze 50, 56, 58 pro Dichtsegment 28) beträgt somit ein ganzzahliges Vielfaches der Anzahl der Sicherungsstege 46a, 46b, 46c, 46d pro Leitschaufelsegment 14a, 14b, 14c, 14d (hier ein Sicherungssteg 46 pro Leitschaufelsegment 14).The sealing segments 28a, 28b, 28c each have three slots 50a, 56a, 58a and 50b, 56b, 58b and 50c, respectively FIG. 2 for distinguishing dividing lines 60, 62, 64, 66 between adjacent sealing segments 28a, 28b, 28c and adjacent vane segments 14a, 14b, 14c, 14d are shown as dots. Due to the detail in FIG. 2 Of the three slots of the sealing segment 28c, only the slot 50c is visible. The slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are at identical positions of the sealing segments 28a, 28b, 28c. The number of slots 50a, 56a, 58a or 50b, 56b, 58b and 50c per sealing segment 28a, 28b, 28c (here three slots 50, 56, 58 per sealing segment 28) is thus an integer multiple of the number of securing webs 46a, 46b, 46c, 46d per vane segment 14a, 14b, 14c, 14d (here one securing ridge 46 per vane segment 14).

Die Schlitze 50a, 56a, 58a bzw. 50b, 56b, 58b bzw. 50c liegen in Umfangsrichtung symmetrisch zur sich in etwa in Strömungsrichtung des Heißgases erstreckenden Längsachse der Dichtsegmente 28a, 28b, 28c. Ein Schlitz 56a, 56b liegt unmittelbar auf der Längsachse und befindet sich im gleichen Umfangsabstand zu Seitenkanten 68, 70 des jeweiligen Dichtsegmentes 28a, 28b, 28c. Die beiden anderen Schlitze 50a, 58a bzw. 50b, 58b bzw. 50c befindet sich beidseits des jeweils mittleren Schlitzes 56a, 56b. Diese seitlichen Schlitze 50a, 58a bzw. 50b, 58b bzw. 50c befinden sich in einem gleichen Umfangsabstand zum mittleren Schlitz 56a, 56b und somit in einem gleichen Umfangsabstand zur jeweils naheliegenden Seitenkante 68, 70. Selbstverständlich liegen die seitlichen Schlitze 50a, 58a bzw. 50b, 58b bzw. 50c auch in einem gleichen Umfangsabstand zur jeweils entfernten Seitenkante 70, 68. Über den Umfang des Dichtsegmentenrings 12 betrachtet sind die Schlitze 50a, 56a, 58a bzw. 50b, 56b, 58b bzw. 50c gleichmäßig voneinander beabstandet. Der Umfangsabstand der seitlichen Schlitze 50a, 58a bzw. 50b, 58b bzw. 50c zum mittleren Schlitz 56a, 56b ist in dem hier gezeigten Ausführungsbeispiel doppelt so groß wie der Umfangsabstand zur jeweils naheliegenden Seitenkante 68, 70.The slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are circumferentially symmetrical to the longitudinal axis of the sealing segments 28a, 28b, 28c extending approximately in the direction of flow of the hot gas. A slot 56a, 56b lies directly on the longitudinal axis and is located at the same circumferential distance from side edges 68, 70 of the respective sealing segment 28a, 28b, 28c. The two other slots 50a, 58a and 50b, 58b and 50c is located on both sides of the respective central slot 56a, 56b. These lateral slots 50a, 58a and 50b, 58b and 50c are located at an equal circumferential distance from the central slot 56a, 56b and thus at an equal circumferential distance to the respective adjacent side edge 68, 70. Of course, the lateral slots 50a, 58a or 50b, 58b and 50c are also at an equal circumferential distance from the respective side edge 70, 68. When viewed over the circumference of the sealing segment ring 12, the slots 50a, 56a, 58a and 50b, 56b, 58b and 50c are equally spaced from each other. The circumferential distance of the lateral slots 50a, 58a or 50b, 58b and 50c to the central slot 56a, 56b is twice as large in the embodiment shown here as the circumferential distance to the respective adjacent side edge 68, 70th

Die Dichtsegmente 28a, 28b, 28c haben eine größere Erstreckung in Umfangsrichtung als die Leitschaufelsegmente 14a, 14b, 14c, 14d, sodass die Trennfugen 60, 62 zwischen den Dichtsegmenten 28a, 28b, 28c in Umfangsrichtung versetzt zu den Trennfugen 64, 66 der Leitschaufelsegmente 14a, 14b, 14c, 14d angeordnet sind. In dem gezeigten Ausführungsbeispiel hat ein Dichtsegment 28a, 28b, 28c die 1,5fache Umfangserstreckung wie eine Leitschaufelsegment14a, 14b, 14c, 14d. Hierdurch sind bei beispielsweise 15 Leitschaufelsegmenten 14a, 14b, 14c, 14d zur Bildung der Leitschaufelreihe 4 und lediglich 10 Dichtsegmente 28a, 28b, 28c zur Bildung des Dichtsegmentenrings 12 erforderlich. Beziehungsweise es liegen in dem hier gezeigten Ausführungsbeispiel 1,5mal so viele Leitschaufelsegmente 14a, 14b, 14c, 14d wie Dichtsegmente 28a, 28b, 28c vor.The sealing segments 28a, 28b, 28c have a greater extent in the circumferential direction than the vane segments 14a, 14b, 14c, 14d, so that the parting lines 60, 62 between the sealing segments 28a, 28b, 28c are circumferentially offset from the parting lines 64, 66 of the vane segments 14a , 14b, 14c, 14d are arranged. In the embodiment shown, a sealing segment 28a, 28b, 28c has 1.5 times the circumferential extent as a Leitschaufelsegment14a, 14b, 14c, 14d. As a result, for example, 15 vane segments 14a, 14b, 14c, 14d to form the guide vane 4 and only 10 sealing segments 28a, 28b, 28c to form the sealing segment ring 12 is required. Respectively, in the exemplary embodiment shown here, there are 1.5 times as many guide blade segments 14a, 14b, 14c, 14d as sealing segments 28a, 28b, 28c.

In dem gezeigten Ausführungsbeispiel befindet sich jeweils jeder zweite Schlitz 50a, 58a, 56b, 50c des Dichtsegmentenrings 12 im Eingriff mit einem Sicherungssteg 46a, 46b, 46c, 46d. Mit anderen Worten, jeder zweite Schlitz 56a, 50b, 58b ist frei. In dem hier gezeigten Ausführungsbeispiel greift der Sicherungssteg 46a in den Schlitz 50a, der Sicherungssteg 46b in den Schlitz 58a, der Sicherungssteg 46c in den Schlitz 56b und der Sicherungssteg 46d in den Schlitz 50c ein. Die Schlitze 56a, 50b und 58b sind nicht belegt. In Umfangsrichtung betrachtet "wandern" die Sicherungsstege 46a, 46b, 46c, 46d quasi immer einen Schlitz 50a, 56a, 58a bzw. 50b, 56b, 58b bzw. 50c weiter. Da jedes Leitschaufelsegment 14a, 14b, 14c, 14d über lediglich einen Sicherungssteg 46a, 46b, 46c, 46d verfügt, bildet dabei jedes Leitschaufelsegment 14a, 14b, 14c, 14d nur eine Formschlussverbindung mit einem Dichtsegment 28a, 28b, 28c bzw. nur eine Umfangssicherung für ein Dichtsegment 28a, 28b, 28c. Aufgrund des in Umfangsrichtung "wandernden Eingriffs" befinden sich jedoch einige Dichtsegmente 28a mit mehreren Leitschaufelsegmenten 14a, 14b gleichzeitig im Formschluss. So greifen hier die Sicherungsstege 46a, 46b der Leitschaufelsegmenten 14a, 14b formschlüssig in die Schlitze 50a, 58a des Dichtsegmentes 28a ein.In the exemplary embodiment shown, each second slot 50a, 58a, 56b, 50c of the sealing segment ring 12 is in engagement with a securing web 46a, 46b, 46c, 46d. In other words, every second slot 56a, 50b, 58b is free. In the embodiment shown here, the securing web 46a engages in the slot 50a, the securing web 46b in the slot 58a, the securing web 46c in the slot 56b and the securing web 46d in the slot 50c. The slots 56a, 50b and 58b are not occupied. As viewed in the circumferential direction, the securing webs 46a, 46b, 46c, 46d virtually always "wander" through a slot 50a, 56a, 58a or 50b, 56b, 58b and 50c. Since each vane segment 14a, 14b, 14c, 14d has only one securing web 46a, 46b, 46c, 46d, each vane segment 14a, 14b, 14c, 14d forms only a form-locking connection with a sealing segment 28a, 28b, 28c or only one circumferential securing device for a sealing segment 28a, 28b, 28c. Due to the "wandering in the circumferential direction", however, some sealing segments 28a with multiple vane segments 14a, 14b are in positive engagement at the same time. In this case, the securing webs 46a, 46b of the guide blade segments 14a, 14b engage in a form-fitting manner in the slots 50a, 58a of the sealing segment 28a.

Offenbart sind eine Strömungsmaschine mit einem Dichtsegmentenring zwischen einer vorderen Leitschaufelreihe und einer hinteren Leitschaufelreihe zum Abdichten eines Radialspaltes zwischen einem Gehäuseabschnitt und einer zwischen den Leitschaufelreihen umlaufenden Laufschaufelreihe, wobei der Dichtsegmentenring eine Vielzahl von gleichen Dichtsegmenten und zumindest eine der Leitschaufelreihe eine Vielzahl von gleichen Leitschaufelsegmenten hat, wobei die Dichtsegmente jeweils mehrere in Umfangsrichtung nebeneinanderliegende Aufnahmen zum Zusammenwirken mit Sicherungselementen dieser Leitschaufelreihe haben, wobei die Aufnahmen und Sicherungselemente gleichmäßig über den Umfang verteilt sind und die Aufnahmen ein Vielfaches der Sicherungselemente sind, ein Dichtsegment sowie ein Leitschaufelsegment.Disclosed are a turbomachine having a sealing segment ring between a front row of vanes and a rear row of vanes for sealing a radial gap between a housing portion and a row of blades revolving between the rows of vanes, the sealing segment ring having a plurality of like sealing segments and at least one of the plurality of vanes having a plurality of like vane segments, wherein the sealing segments each have a plurality of circumferentially adjacent receptacles for interacting with securing elements of this guide vane row, wherein the receptacles and securing elements are distributed uniformly over the circumference and the receptacles are a multiple of the securing elements, a sealing segment and a vane segment.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Strömungsmaschineflow machine
22
HeißgaskanalHot gas duct
44
vordere Leitschaufelreihefront guide vane row
66
hinterer Leitschaufelreiherear vane row
88th
LaufschaufelreiheBlade row
1010
Gehäuseabschnitthousing section
1212
DichtsegmentenringSealing ring segment
14, a, b, c, d14, a, b, c, d
Leitschaufelsegmentvane segment
1616
vorderer Halteabschnittfront holding section
1818
hinterer Halteabschnittrear holding section
2020
Gehäusenuthousing groove
2222
Leitschaufelsegmentvane segment
2424
vorderer Halteabschnittfront holding section
2626
Gehäusenuthousing groove
28, a, b, c28, a, b, c
Dichtsegmentsealing segment
3030
Grundkörperbody
3232
Dichtwabensealing honeycomb
3434
Dichtstegsealing land
3636
Dichtstegsealing land
3838
vorderer Randabschnittfront edge section
4040
hinterer Randabschnittrear edge section
4242
PlattformüberhangDeck overhang
4444
PlattformüberhangDeck overhang
46, a, b, c, d46, a, b, c, d
Sicherungsstegsecuring web
4848
Rückseiteback
50, a, b, c50, a, b, c
Schlitzslot
5252
Seitenkanteside edge
5454
Seitenkanteside edge
56, a, b, c56, a, b, c
Schlitzslot
58, a, b, c58, a, b, c
Schlitzslot
6060
Trennfuge DichtsegmentParting line sealing segment
6262
Trennfuge DichtsegmentParting line sealing segment
6464
Trennfuge LeitschaufelsegmentParting line Guide vane segment
6666
Trennfuge LeitschaufelsegmentParting line Guide vane segment
6868
Seitenkanteside edge
7070
Seitenkanteside edge

Claims (4)

  1. A continuous-flow machine (1) having a sealing segment ring (12) between a front row of guide vanes (4) and a back row of guide vanes (6) for sealing a radial gap between a housing section (10) and a row of rotor blades (8) circulating between the rows of guide vanes (4, 6), wherein the sealing segment ring (12) has a plurality of equal sealing segments (28) and at least one row of guide vanes (4) has a plurality of equal guide vane segments (14), wherein the sealing segments (28) each have several receivers (50, 56, 58) adjacent to each other in the circumferential direction in order to interact with safety elements (46) of this row of guide vanes (4), and wherein the receivers (50, 56, 58) and safety elements (46) are evenly distributed across the circumference,
    characterized in that the receivers (50, 56, 58) are a multiple of the safety elements (46), and that each guide vane segment (14) of this row of guide vanes (4) has only one safety element (46).
  2. The continuous-flow machine according to claim 1, wherein each sealing segment (28) has an equal plurality of receivers (50, 56, 58) and the receivers (50, 56, 58) as well as the safety elements (46) are arranged at identical positions of the sealing segments (28) or the guide vane segments (14) of this row of guide vanes (4).
  3. The continuous-flow machine according to claim 1 or 2, wherein the safety element (46) of the respective guide vane segment (14) and the receivers (50, 56, 58) of the respective sealing segment (28) are arranged symmetrically to the respective longitudinal axis of the segment.
  4. The continuous-flow machine according to one of the preceding claims, wherein 1.5 times as many guide vane segments (14) of this row of guide vanes (4) as sealing segments (28) and three times as many receivers (50, 56, 58) per sealing segment (28) as safety elements (46) per guide vane segment (14) are provided.
EP13176503.4A 2013-07-15 2013-07-15 Turboengine with sealing segments and guide vane segments Active EP2826962B1 (en)

Priority Applications (3)

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ES13176503.4T ES2581511T3 (en) 2013-07-15 2013-07-15 Turbomachine, sealing segment and guide blade segment
EP13176503.4A EP2826962B1 (en) 2013-07-15 2013-07-15 Turboengine with sealing segments and guide vane segments
US14/329,570 US9982566B2 (en) 2013-07-15 2014-07-11 Turbomachine, sealing segment, and guide vane segment

Applications Claiming Priority (1)

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EP13176503.4A EP2826962B1 (en) 2013-07-15 2013-07-15 Turboengine with sealing segments and guide vane segments

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Publication number Priority date Publication date Assignee Title
ES2628679T3 (en) * 2013-12-04 2017-08-03 MTU Aero Engines AG Sealing element, sealing device and turbomachine
DE102015224160A1 (en) * 2015-12-03 2017-06-08 MTU Aero Engines AG Inlet lining for an external air seal of a turbomachine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
DE102018210600A1 (en) * 2018-06-28 2020-01-02 MTU Aero Engines AG COAT RING ARRANGEMENT FOR A FLOWING MACHINE

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US3365173A (en) * 1966-02-28 1968-01-23 Gen Electric Stator structure
GB2310255B (en) * 1996-02-13 1999-06-16 Rolls Royce Plc A turbomachine
GB0218060D0 (en) * 2002-08-03 2002-09-11 Alstom Switzerland Ltd Sealing arrangements
GB2395756B (en) * 2002-11-27 2006-02-08 Rolls Royce Plc Cooled turbine assembly
US7186078B2 (en) 2003-07-04 2007-03-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbine shroud segment
JP4269829B2 (en) * 2003-07-04 2009-05-27 株式会社Ｉｈｉ Shroud segment
DE10359730A1 (en) * 2003-12-19 2005-07-14 Mtu Aero Engines Gmbh Turbomachine, in particular gas turbine
SI2137382T1 (en) * 2007-04-19 2012-10-30 Alstom Technology Ltd Stator heat shield
DE102007031711A1 (en) * 2007-07-06 2009-01-08 Rolls-Royce Deutschland Ltd & Co Kg Housing shroud segment suspension
JP5384983B2 (en) * 2009-03-27 2014-01-08 本田技研工業株式会社 Turbine shroud
US20110243725A1 (en) * 2010-03-31 2011-10-06 General Electric Company Turbine shroud mounting apparatus with anti-rotation feature

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US9982566B2 (en) 2018-05-29
US20150016969A1 (en) 2015-01-15
EP2826962A1 (en) 2015-01-21

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