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EP2611992B1 - Housing structure of a turbomachine - Google Patents

Housing structure of a turbomachine Download PDF

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Publication number
EP2611992B1
EP2611992B1 EP11785296.2A EP11785296A EP2611992B1 EP 2611992 B1 EP2611992 B1 EP 2611992B1 EP 11785296 A EP11785296 A EP 11785296A EP 2611992 B1 EP2611992 B1 EP 2611992B1
Authority
EP
European Patent Office
Prior art keywords
housing
casing ring
ring
stator
side structure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP11785296.2A
Other languages
German (de)
French (fr)
Other versions
EP2611992A1 (en
Inventor
Wilfried Weidmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2611992A1 publication Critical patent/EP2611992A1/en
Application granted granted Critical
Publication of EP2611992B1 publication Critical patent/EP2611992B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a housing-side structure of a turbomachine according to the preamble of claim 1.
  • a turbomachine including a stator and a rotor wherein the rotor includes rotor blades and the stator includes a housing and vanes.
  • the rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same.
  • the radially inner housing wall of the housing is also referred to as inner ring or shroud and serves in particular as a carrier for an inlet lining.
  • the inner ring or shroud ring of a compressor or a turbine can be segmented and accordingly composed of a plurality of shroud segments, wherein a shroud segment is also referred to as Shroud.
  • Shroud a shroud segment
  • the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and over all operating conditions to ensure optimum gap position and thus optimum pump marginality and optimum efficiency.
  • an adjusting device is assigned to each shroud segments of the shroud according to this prior art, which are preferably designed as electro-mechanical actuators. In this way, an active Spaltjanskin be provided.
  • the Spaltjanin the gap between the radially outer ends of the blades of a rotor blade ring and the inner ring or shroud of the housing via an active clearance control is structurally complex. It is therefore desirable to realize the Spaltjan with less effort.
  • the present invention is based on the problem to provide a housing-side structure of a turbomachine, which allows a novel, simple Spaltjanskin.
  • This problem is solved by a housing-side structure of a turbomachine according to claim 1.
  • the shroud bearing the inlet lining is connected via at least one constriction to a stator-side housing part radially adjoining the shroud ring and thermally decoupled from the same.
  • the housing-side structure of a turbomachine is due to the thermal decoupling of the shroud or inner ring from the radially outer adjacent housing thermal overshoot, especially in transient operating areas of the turbomachine during acceleration or deceleration of the same, reduced, whereby the Spalt matter between the blade ring and the can be radially outward adjacent to the blade ring adjacent shroud improved.
  • the thermal decoupling takes place via at least one constriction between the outer ring and the radially outer side of the same adjacent housing part.
  • a weight-optimal, compact, inexpensive, reliable and simple design can be provided, with which a Spaltjan between radially outer ends of blades of a blade ring and a radially outside adjacent mantle ring and so an optimal surge margin and optimal efficiency without complex Active Clearance Control can be provided.
  • a flange is formed on the housing part radially outwardly adjoining the stator housing part, wherein a support element is attached to the flange, which bears against at least one section at a downstream end of the casing ring for stabilizing the same.
  • a heat shield prevents a hot gas entering a housing-side recess. Through the heat shield the Spaltjan can be further improved.
  • a shroud 16 which serves as a support for an inlet lining for the radially outer ends of the rotor-side blades 11 of the blade ring 10 and defines a gap 17 with the same.
  • the shroud 16 of the housing-side structure to form at least one constriction 18 with a connected to the shroud 16 radially outwardly adjacent, stator housing part 19 and thermally decoupled from the same and the rest of the housing.
  • the bottleneck 18 is in FIG. 1 arranged centrally to the shroud 16, wherein preferably the constriction 18 can be arranged up to the first third upstream of the shroud 16.
  • a flange 20 is formed on which in the embodiment of Fig. 1 a support member 21 is fixed, which in Fig. 1 with a portion 22 at the downstream end of the shroud 16 for stabilizing and in particular sealing the same rests.
  • a tilting of the shroud 16 can be avoided.
  • the portion 22 of the support member 21, with which it rests on the shroud 16 for stabilizing and in particular sealing the same extends substantially in the horizontal or axial direction, said portion 22 extending in a substantially horizontal or axial direction Surface at a likewise substantially in the horizontal or axial direction extending surface of the shroud 16 to form a sealing area and thus abuts sealing function.
  • the support member 21 is fixed to the flange 20 of the housing part 19 via fasteners 34 designed in particular as screw elements. Over the circumference of the support member 21 a plurality of fasteners 34 are distributed.
  • the support element 21 is preferably formed as a segmented ring.
  • the housing-side structure of the turbomachine further has a heat shield or heat shield 24, wherein the heat shield 24 with a first end 25 in a recess 26 of the at Shroud 16 downstream downstream, the stator side member engages, namely according to Fig. 1 in the recess 26 of a vane 15, and wherein the heat shield 24 rests with a second end 27 on the support member 21, which serves to stabilize and in particular seal the shroud 16.
  • the heat shield 24 is preferably formed as a metallic ring.
  • FIG. 2 A second embodiment of a housing-side structure of a turbomachine according to the invention shows Fig. 2 , wherein the embodiment of the Fig. 2 essentially the embodiment of Fig. 1 corresponds so that the same reference numerals are used to avoid unnecessary repetition for the same components and will be discussed below only from such details, through which the embodiment of the Fig. 2 from the embodiment of Fig. 1 different.
  • Fig. 2 In the embodiment of Fig. 2 are two bottlenecks 18A and 18B present, via which the inlet lining bearing shroud 16 is connected to the radially outwardly adjacent to the shroud 16, stator housing part 19 and thermally decoupled from the same. Seen in the axial direction, the bottlenecks 18A and 18B are therefore positioned off-center to the shroud 16, whereas in the embodiment of the Fig. 2 the constriction 18 is positioned centrally in the axial direction to the shroud 16 seen in the axial direction.
  • Fig. 2 can in the embodiment of the Fig. 2 are dispensed with the support member 21, in particular, when the downstream constriction 18 B, which has a stabilizing effect, is present. In this case can then be dispensed with the fasteners 34.
  • the heat shield 24 rests with the second end 27 not on the support member 21, but rather on the flange 20 of the housing part 19th
  • a third embodiment of a housing-side structure of a turbomachine according to the invention shows Fig. 3 , wherein in the embodiment of the Fig. 2 in turn, a support member 21 'is present, which serves to stabilize and in particular seal the shroud 16, and which is fixed to the flange 20 which is formed on the housing part 19, which is connected via the constriction 18 with the shroud 16.
  • the constriction 18 in turn serves the thermal decoupling of the shroud 16 from the housing part 19th
  • the support element 21 ' With two sections 28 and 29 at a downstream end of the shroud 16, namely with a substantially in the horizontal or axial direction extending first portion 28 and a substantially vertically or radially extending portion 29th
  • the section 28 of the support element 21 ' which extends essentially in the horizontal or in the axial direction, bears against a surface of the shroud 16 which likewise extends substantially in the horizontal or axial direction, whereas the section 29 adjoins a substantially vertical one or radial direction extending portion of the shroud 16 abuts.
  • These sections 28, 29 are used in particular for stabilizing the outer ring 16 and sealing it.
  • a further portion 30 is formed, which also extends substantially in the axial or horizontal direction and projecting in the downstream direction relative to the shroud 16 and radially outside a downstream of the shroud 16 subsequent, stator-side member 31 partially overlapped.
  • This component 31 may be a section of a stator vane ring or a stator-side flow channel section.
  • a radially inner contour 35 of the portion 29 of the support element 21 ' which limits a flow channel radially outwardly in sections, namely in the transition region to the component 31, is configured or contoured such that it directs a gas flow radially inward and thus a hot gas inlet via the gap 32 prevented in the housing-side recess 23 and significantly reduced.
  • a heat shield or heat shield 33 is present, however, in contrast to the embodiment of Fig. 1 is attached to the flange 20 together with the support member 21 '. Also, the heat shield 33 of Fig. 3 prevents a hot gas entering a housing-side recess.
  • the heat shield 33 is preferably formed as a metallic ring.
  • an effective and reliable Spaltjanin between radially outer ends of blades of a blade ring and a radially outer adjoining shroud 16 can be ensured in a structurally simple manner.
  • the shroud 16 is thermally decoupled from the housing via at least one constriction 18, 18A, 18B.
  • a tilting of the shroud 16 is preferably prevented by a support member 21 and 21 ', which mechanically stabilizes the shroud 16 and seals in particular against hot gas inlet.
  • the Spaltjan can be further improved.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft eine gehäuseseitige Struktur einer Turbomaschine gemäß dem Oberbegriff des Anspruchs 1. Aus der DE 10 2004 037 955 A1 ist eine Turbomaschine mit einem Stator und einem Rotor bekannt, wobei der Rotor Laufschaufeln und der Stator ein Gehäuse und Leitschaufeln aufweist. Die rotorseitigen Laufschaufeln bilden mindestens einen Laufschaufelkranz, der an einem radial außen liegenden Ende an eine radial innen liegende Gehäusewand des Gehäuses angrenzt, von derselben umgeben ist und mit derselben einen radialen Spalt begrenzt. Die radial innen liegende Gehäusewand des Gehäuses wird auch als Innenring bzw. Mantelring bezeichnet und dient insbesondere als Träger für einen Einlaufbelag. Der Innenring bzw. Mantelring eines Verdichters bzw. einer Turbine kann segmentiert und demnach aus mehreren Mantelringsegmenten zusammengesetzt sein, wobei ein Mantelringsegment auch als Shroud bezeichnet wird. Aus der DE 10 2004 037 955 A1 ist weiterhin bekannt, dass der Spalt zwischen dem Mantelring des Gehäuses und dem radial außen liegenden Ende des oder jedes Laufschaufelkranzes zur Bereitstellung eines sogenannten Active Clearance Control über Stelleinrichtungen in seinem Spaltmaß eingestellt bzw. angepasst werden kann, um so automatisch den Spalt zu beeinflussen und über alle Betriebsbedingungen eine optimale Spalthaltung und so einen optimalen Pumpgrenzanstand und optimalen Wirkungsgrad zu gewährleisten. Dabei ist nach diesem Stand der Technik jedem Mantelringsegmenten des Mantelrings eine Stelleinrichtung zugeordnet ist, die vorzugsweise als elektro-mechanische Aktuatoren ausgeführt sind. Auf diese Art und weise kann ein aktives Spaltmaßhaltungsprinzip bereitgestellt werden.The invention relates to a housing-side structure of a turbomachine according to the preamble of claim 1. From the DE 10 2004 037 955 A1 For example, a turbomachine including a stator and a rotor is known, wherein the rotor includes rotor blades and the stator includes a housing and vanes. The rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same. The radially inner housing wall of the housing is also referred to as inner ring or shroud and serves in particular as a carrier for an inlet lining. The inner ring or shroud ring of a compressor or a turbine can be segmented and accordingly composed of a plurality of shroud segments, wherein a shroud segment is also referred to as Shroud. From the DE 10 2004 037 955 A1 It is also known that the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and over all operating conditions to ensure optimum gap position and thus optimum pump marginality and optimum efficiency. In this case, an adjusting device is assigned to each shroud segments of the shroud according to this prior art, which are preferably designed as electro-mechanical actuators. In this way, an active Spaltmaßhaltungsprinzip be provided.

Die Spaltmaßhaltung des Spalts zwischen den radial außen liegenden Enden der Lauf schaufeln eines Laufschaufelkranzes und dem Innenring bzw. Mantelring des Gehäuses über ein Active Clearance Control ist konstruktiv aufwendig. Es ist daher gewünscht, die Spaltmaßhaltung mit geringerem Aufwand zu realisieren.The Spaltmaßhaltung the gap between the radially outer ends of the blades of a rotor blade ring and the inner ring or shroud of the housing via an active clearance control is structurally complex. It is therefore desirable to realize the Spaltmaßhaltung with less effort.

Ferner ist eine Gehäusestruktur mit thermisch entkoppeltem Mantelring aus der GB 2 117 843 A bekannt.Furthermore, a housing structure with thermally decoupled shroud of the GB 2 117 843 A known.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine gehäuseseitige Struktur einer Turbomaschine zu schaffen, die ein neuartiges, einfaches Spaltmaßhaltungsprinzip erlaubt. Dieses Problem wird durch eine gehäuseseitige Struktur einer Turbomaschine gemäß Anspruch 1 gelöst. Erfindungsgemäß ist der den Einlaufbelag tragende Mantelring über mindestens eine Engstelle mit einem an den Mantelring radial außen angrenzenden, statorseitigen Gehäuseteil verbunden und von demselben thermisch entkoppelt.On this basis, the present invention is based on the problem to provide a housing-side structure of a turbomachine, which allows a novel, simple Spaltmaßhaltungsprinzip. This problem is solved by a housing-side structure of a turbomachine according to claim 1. According to the invention, the shroud bearing the inlet lining is connected via at least one constriction to a stator-side housing part radially adjoining the shroud ring and thermally decoupled from the same.

Mit der erfindungsgemäßen gehäuseseitigen Struktur einer Turbomaschine wird in Folge der thermischen Entkopplung des Mantelrings bzw. Innenrings vom radial außen angrenzenden Gehäuse ein thermisches Überschwingen, insbesondere in transienten Betriebsbereichen der Turbomaschine beim Beschleunigen bzw. Abbremsen derselben, reduziert, wodurch die Spaltmaßhaltung zwischen dem Laufschaufelkranz und dem radial außen an den Laufschaufelkranz angrenzenden Mantelring verbessert werden kann. Die thermische Entkopplung erfolgt über mindestens eine Engstelle zwischen dem Mantelring und dem radial außen an denselben angrenzenden Gehäuseteil. Durch das erfindungsgemäße Konstruktionsprinzip einer gehäuseseitigen Struktur einer Turbomaschine, welches insbesondere bei Hochdruckverdichtern zum Einsatz kommt, kann ein gewichtsoptimales, kompaktes, kostengünstiges, zuverlässiges und einfaches Design bereitgestellt werden, mit welchem eine Spaltmaßhaltung zwischen radial außen liegenden Enden von Laufschaufeln eines Laufschaufelkranzes und einem radial außen angrenzenden Mantelring und so ein optimaler Pumpgrenzabstand sowie optimaler Wirkungsgrad ohne aufwendiges Active Clearance Control bereitgestellt werden kann. Weiterhin ist an dem an den Mantelring radial außen angrenzenden, statorseitigen Gehäuseteil ein Flansch ausgebildet, wobei an dem Flansch ein Stützelement befestigt ist, das mit mindestens einem Abschnitt an einem stromabwärtigen Ende des Mantelrings zur Stabilisierung desselben anliegt. Durch das Stützelement ist der Mantelring gegen Verkippen gesichert und wird dadurch stabilisiert. Weiterhin übernimmt das Stützelement, das an einem stromabwärtigen Ende des Mantelrings zur Anlage kommt, eine Abdichtfunktion.With the housing-side structure of a turbomachine according to the invention is due to the thermal decoupling of the shroud or inner ring from the radially outer adjacent housing thermal overshoot, especially in transient operating areas of the turbomachine during acceleration or deceleration of the same, reduced, whereby the Spaltmaßhaltung between the blade ring and the can be radially outward adjacent to the blade ring adjacent shroud improved. The thermal decoupling takes place via at least one constriction between the outer ring and the radially outer side of the same adjacent housing part. Due to the inventive design principle of a housing-side structure of a turbomachine, which is used in particular for high pressure compressors, a weight-optimal, compact, inexpensive, reliable and simple design can be provided, with which a Spaltmaßhaltung between radially outer ends of blades of a blade ring and a radially outside adjacent mantle ring and so an optimal surge margin and optimal efficiency without complex Active Clearance Control can be provided. Furthermore, a flange is formed on the housing part radially outwardly adjoining the stator housing part, wherein a support element is attached to the flange, which bears against at least one section at a downstream end of the casing ring for stabilizing the same. By the support member of the shroud is secured against tilting and is thereby stabilized. Furthermore, the support element, which comes to rest at a downstream end of the shroud, performs a sealing function.

Vorzugsweise verhindert ein Wärmeschild einen Heißgaseintritt in eine gehäuseseitige Ausnehmung. Durch den Wärmeschild kann die Spaltmaßhaltung weiter verbessert werden.Preferably, a heat shield prevents a hot gas entering a housing-side recess. Through the heat shield the Spaltmaßhaltung can be further improved.

Die erfindungsgemäße Turbomaschine ist in Anspruch 10 definiert. Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
einen Ausschnitt aus einer Turbomaschine im Bereich einer erfindungsgemäßen, gehäuseseitigen Struktur derselben nach einem ersten Ausführungsbeispiel der Erfindung;
Fig. 2
einen Ausschnitt aus einer Turbomaschine im Bereich einer erfindungsgemäßen, gehäuseseitigen Struktur derselben nach einem zweiten Ausführungsbeispiel der Erfindung; und
Fig. 3
einen Ausschnitt aus einer Turbomaschine im Bereich einer erfindungsgemäßen, gehäuseseitigen Struktur derselben nach einem dritten Ausführungsbeispiel der Erfindung.
Die hier vorliegende Erfindung betrifft eine gehäuseseitige Struktur einer Turbomaschine, insbesondere einer Gasturbine. Die Erfindung kommt insbesondere bei Verdichtern, vorzugsweise bei Hochduckverdichtern, zum Einsatz.
Fig. 1 zeigt einen Ausschnitt aus einer Turbomaschine im Bereich einer gehäuseseitigen Struktur eines Verdichters nach einem ersten Ausführungsbeispiel der Erfindung, wobei in Fig. 1 ein rotorseitiger Laufschaufelkranz 10 mit Laufschaufeln 11 sowie stromaufwärts und stromabwärts des Laufschaufelkranzes 10 statorseitige Leitschaufelkränze 12 bzw. 13 mit Leitschaufeln 14 bzw. 15 gezeigt sind. Eine solcher Verdichter kann längsgeteilt oder quergeteilt ausgeführt sein.The turbomachine according to the invention is defined in claim 10. Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a detail of a turbomachine in the range of an inventive, housing-side structure thereof according to a first embodiment of the invention;
Fig. 2
a detail of a turbomachine in the range of an inventive, housing-side structure thereof according to a second embodiment of the invention; and
Fig. 3
a detail of a turbomachine in the region of a housing-side structure according to the invention thereof according to a third embodiment of the invention.
The present invention relates to a housing-side structure of a turbomachine, in particular a gas turbine. The invention is used in particular for compressors, preferably for high pressure compressors.
Fig. 1 shows a section of a turbomachine in the region of a housing-side structure of a compressor according to a first embodiment of the invention, wherein in Fig. 1 a rotor-side blade ring 10 with blades 11 and upstream and downstream of the blade ring 10 stator vane rings 12 and 13 are shown with vanes 14 and 15, respectively. Such a compressor can be designed longitudinally divided or transversely divided.

Radial außen an den Laufschaufelkranz 10 bzw. die Laufschaufeln 11 desselben grenzt ein Mantelring 16 an, der als Träger für einen Einlaufbelag für die radial außenliegenden Enden der rotorseitigen Laufschaufeln 11 des Laufschaufelkranzes 10 dient und mit denselben einen Spalt 17 definiert.Radially outside of the blade ring 10 and the blades 11 thereof adjacent to a shroud 16 which serves as a support for an inlet lining for the radially outer ends of the rotor-side blades 11 of the blade ring 10 and defines a gap 17 with the same.

Um mit einfachen, konstruktiven Mitteln eine Spaltmaßhaltung des Spalts 17 zwischen den radial außenliegenden Enden der Laufschaufeln 11 des Laufschaufelkranzes 10 und dem Mantelring 16 zu gewährleisten, ist im Sinne der hier vorliegenden Erfindung der Mantelring 16 der gehäuseseitigen Stuktur unter Ausbildung mindestens einer Engstelle 18 mit einem an den Mantelring 16 radial außen angrenzenden, statorseitigen Gehäuseteil 19 verbunden und von demselben sowie übrigen Gehäuse thermisch entkoppelt. Die Engstelle 18 ist in Figur 1 mittig zum Mantelring 16 angeordnet, wobei vorzugsweise die Engstelle 18 bis zum ersten Drittel stromaufwärts des Mantelrings 16 angeordnet sein kann.In order to ensure with simple, constructive means a Spaltmaßhaltung of the gap 17 between the radially outer ends of the blades 11 of the blade ring 10 and the shroud 16 is within the meaning of the present invention, the shroud 16 of the housing-side structure to form at least one constriction 18 with a connected to the shroud 16 radially outwardly adjacent, stator housing part 19 and thermally decoupled from the same and the rest of the housing. The bottleneck 18 is in FIG. 1 arranged centrally to the shroud 16, wherein preferably the constriction 18 can be arranged up to the first third upstream of the shroud 16.

An diesem statorseitigen Gehäuseteil 19, welches sich radial außen an den Mantelring 16 anschließt und mit demselben über die Engstelle 18 verbunden ist, ist ein Flansch 20 ausgebildet, an welchem im Ausführungsbeispiel der Fig. 1 ein Stützelement 21 befestigt ist, das in Fig. 1 mit einem Abschnitt 22 am stromabwärtigen Ende des Mantelrings 16 zur Stabilisierung und insbesondere Abdichtung desselben anliegt. Über das Stützelement 21 kann ein Verkippen des Mantelrings 16 vermieden werden.At this stator-side housing part 19, which connects radially to the outside of the shroud 16 and is connected to the same via the constriction 18, a flange 20 is formed on which in the embodiment of Fig. 1 a support member 21 is fixed, which in Fig. 1 with a portion 22 at the downstream end of the shroud 16 for stabilizing and in particular sealing the same rests. About the support member 21, a tilting of the shroud 16 can be avoided.

Im in Fig. 1 gezeigten Ausführungsbeispiel erstreckt sich der Abschnitt 22 des Stützelements 21, mit welchem derselbe am Mantelring 16 zur Stabilisierung und insbesondere Abdichtung desselben anliegt, im Wesentlichen in horizontaler bzw. axialer Richtung, wobei dieser Abschnitt 22 mit einer sich im Wesentlichen in horizontaler bzw. axialer Richtung erstreckenden Fläche an einer sich ebenfalls im Wesentlichen in horizontaler bzw. axialer Richtung erstreckenden Fläche des Mantelrings 16 unter Ausbildung eines Dichtbereichs und damit Abdichtfunktion anliegt.Im in Fig. 1 the embodiment shown, the portion 22 of the support member 21, with which it rests on the shroud 16 for stabilizing and in particular sealing the same, extends substantially in the horizontal or axial direction, said portion 22 extending in a substantially horizontal or axial direction Surface at a likewise substantially in the horizontal or axial direction extending surface of the shroud 16 to form a sealing area and thus abuts sealing function.

Gemäß Fig. 1 ist das Stützelement 21 an dem Flansch 20 des Gehäuseteils 19 über insbesondere als Schraubelemente ausgebildete Befestigungselemente 34 befestigt. Über den Umfang des Stützelements 21 sind mehrere Befestigungselemente 34 verteilt.According to Fig. 1 the support member 21 is fixed to the flange 20 of the housing part 19 via fasteners 34 designed in particular as screw elements. Over the circumference of the support member 21 a plurality of fasteners 34 are distributed.

Das Stützelement 21 ist vorzugsweise als segmentierter Ring ausgebildet.The support element 21 is preferably formed as a segmented ring.

Um einen Eintritt von Heißgas aus dem Strömungskanal der Turbomaschine in eine gehäuseseitige Ausnehmung 23 zu verhindern, verfügt die gehäuseseitige Struktur der Turbomaschine weiterhin über einen Hitzeschild bzw. Wärmeschild 24, wobei der Wärmeschild 24 mit einem ersten Ende 25 in eine Ausnehmung 26 eines sich an den Mantelring 16 stromabwärts anschließenden, statorseitigen Bauteils eingreift, nämlich gemäß Fig. 1 in die Ausnehmung 26 einer Leitschaufel 15, und wobei der Wärmeschild 24 mit einem zweiten Ende 27 an dem Stützelement 21 anliegt, welcher der Stabilisierung und insbesondere Abdichtung des Mantelrings 16 dient. Der Wärmeschild 24 ist vorzugsweise als metallischer Ring ausgebildet.In order to prevent the entry of hot gas from the flow channel of the turbomachine into a housing-side recess 23, the housing-side structure of the turbomachine further has a heat shield or heat shield 24, wherein the heat shield 24 with a first end 25 in a recess 26 of the at Shroud 16 downstream downstream, the stator side member engages, namely according to Fig. 1 in the recess 26 of a vane 15, and wherein the heat shield 24 rests with a second end 27 on the support member 21, which serves to stabilize and in particular seal the shroud 16. The heat shield 24 is preferably formed as a metallic ring.

Ein zweites Ausführungsbeispiel einer erfindungsgemäßen gehäuseseitigen Struktur einer Turbomaschine zeigt Fig. 2, wobei das Ausführungsbeispiel der Fig. 2 im Wesentlichen dem Ausführungsbeispiel der Fig. 1 entspricht, sodass zur Vermeidungen unnötiger Wiederholungen für gleiche Baugruppen gleiche Bezugsziffern verwendet werden und nachfolgend nur aus solche Details eingegangen wird, durch die sich das Ausführungsbeispiel der Fig. 2 vom Ausführungsbeispiel der Fig. 1 unterscheidet.A second embodiment of a housing-side structure of a turbomachine according to the invention shows Fig. 2 , wherein the embodiment of the Fig. 2 essentially the embodiment of Fig. 1 corresponds so that the same reference numerals are used to avoid unnecessary repetition for the same components and will be discussed below only from such details, through which the embodiment of the Fig. 2 from the embodiment of Fig. 1 different.

Im Ausführungsbeispiel der Fig. 2 sind zwei Engstellen 18A und 18B vorhanden, über die der den Einlaufbelag tragende Mantelring 16 mit dem an den Mantelring 16 radial außen angrenzenden, statorseitigen Gehäuseteil 19 verbunden und von demselben thermisch entkoppelt ist. In Axialrichtung gesehen sind die Engstellen 18A und 18B demnach außermittig zum Mantelring 16 positioniert, wohingegen im Ausführungsbeispiel der Fig. 2 die Engstelle 18 in Axialrichtung gesehen mittig zum Mantelring 16 positioniert ist.In the embodiment of Fig. 2 are two bottlenecks 18A and 18B present, via which the inlet lining bearing shroud 16 is connected to the radially outwardly adjacent to the shroud 16, stator housing part 19 and thermally decoupled from the same. Seen in the axial direction, the bottlenecks 18A and 18B are therefore positioned off-center to the shroud 16, whereas in the embodiment of the Fig. 2 the constriction 18 is positioned centrally in the axial direction to the shroud 16 seen in the axial direction.

Es kann auch nur eine außermittige Engstelle vorhanden sein. So ist es möglich, dass im Ausführungsbeispiel der Fig. 2 die stromaufwärtige Engstelle 18A vorhanden ist, jedoch nicht die stromabwärtige Engstelle 18B.There may also be only one off-center bottleneck. So it is possible that in the embodiment of Fig. 2 the upstream constriction 18A is present, but not the downstream constriction 18B.

Wie das Ausführungsbeispiel der Fig. 2 durch eine gestrichelte Linienführung zeigt, kann im Ausführungsbeispiel der Fig. 2 auf das Stützelement 21 verzichtet werden, insbesondere dann, wenn die stromabwärtige Engstelle 18B, die stabilisierend wirkt, vorhanden ist. In diesen Fall kann dann auch auf die Befestigungselemente 34 verzichtet werden. In diesem Fall liegt der Wärmeschild 24 mit dem zweiten Ende 27 nicht an dem Stützelement 21 an, sondern vielmehr am Flansch 20 des Gehäuseteils 19.Like the embodiment of Fig. 2 shown by a dashed line, can in the embodiment of the Fig. 2 are dispensed with the support member 21, in particular, when the downstream constriction 18 B, which has a stabilizing effect, is present. In this case can then be dispensed with the fasteners 34. In this case, the heat shield 24 rests with the second end 27 not on the support member 21, but rather on the flange 20 of the housing part 19th

Ein drittes Ausführungsbeispiel einer erfindungsgemäßen gehäuseseitigen Struktur einer Turbomaschine zeigt Fig. 3, wobei im Ausführungsbeispiel der Fig. 2 wiederum ein Stützelement 21' vorhanden ist, welches der Stabilisierung und insbesondere Abdichtung des Mantelrings 16 dient, und welches am Flansch 20 befestigt ist, der an dem Gehäuseteil 19 ausgebildet ist, welches über die Engstelle 18 mit dem Mantelring 16 verbunden ist. Die Engstelle 18 dient wiederum der thermischen Entkopplung des Mantelrings 16 vom Gehäuseteil 19.A third embodiment of a housing-side structure of a turbomachine according to the invention shows Fig. 3 , wherein in the embodiment of the Fig. 2 in turn, a support member 21 'is present, which serves to stabilize and in particular seal the shroud 16, and which is fixed to the flange 20 which is formed on the housing part 19, which is connected via the constriction 18 with the shroud 16. The constriction 18 in turn serves the thermal decoupling of the shroud 16 from the housing part 19th

Im Ausführungsbeispiel der Fig. 3 liegt das Stützelement 21' mit zwei Abschnitten 28 und 29 an einem stromabwärtigen Ende des Mantelrings 16 an, nämlich mit einem sich im Wesentlichen in horizontaler bzw. axialer Richtung erstreckenden ersten Abschnitt 28 und einem sich im Wesentlichen in vertikaler bzw. radialer Richtung erstreckenden Abschnitt 29. Der sich im Wesentlichen in horizontaler bzw. in axialer Richtung erstreckende Abschnitt 28 des Stützelements 21' liegt an einer sich ebenfalls im Wesentlichen in horizontaler bzw. axialer Richtung erstreckenden Fläche des Mantelrings 16 an, wohingegen der Abschnitt 29 an einer sich im Wesentlichen in vertikaler bzw. radialer Richtung erstreckenden Abschnitts des Mantelrings 16 anliegt. Diese Abschnitte 28, 29 dienen insbesondere der Stabilisierung des Mantelrings 16 und Abdichtung desselben.In the embodiment of Fig. 3 the support element 21 'with two sections 28 and 29 at a downstream end of the shroud 16, namely with a substantially in the horizontal or axial direction extending first portion 28 and a substantially vertically or radially extending portion 29th The section 28 of the support element 21 ', which extends essentially in the horizontal or in the axial direction, bears against a surface of the shroud 16 which likewise extends substantially in the horizontal or axial direction, whereas the section 29 adjoins a substantially vertical one or radial direction extending portion of the shroud 16 abuts. These sections 28, 29 are used in particular for stabilizing the outer ring 16 and sealing it.

Im Ausführungsbeispiel der Fig. 3 ist am Stützelement 21' ein weiterer Abschnitt 30 ausgebildet, der sich ebenfalls im Wesentlichen in axialer bzw. horizontaler Richtung erstreckt und in stromabwärtiger Richtung gegenüber dem Mantelring 16 vorsteht und radial außen ein sich stromabwärts an den Mantelring 16 anschließendes, statorseitiges Bauteil 31 abschnittsweise überdeckt.In the embodiment of Fig. 3 on the support member 21 ', a further portion 30 is formed, which also extends substantially in the axial or horizontal direction and projecting in the downstream direction relative to the shroud 16 and radially outside a downstream of the shroud 16 subsequent, stator-side member 31 partially overlapped.

Bei einer thermischen Ausdehnung des Bauteils 31 im Betrieb kommt dasselbe am Abschnitt 30 des Stützelements 21' zur Anlage und verhindert so, dass aus dem Strömungskanal Heißgas durch einen zwischen dem Stützelement 21 und Bauteil 31 ausgebildeten Spalt 32 in eine gehäuseseitige Ausnehmung eintritt. Bei diesem Bauteil 31 kann es sich um einem Abschnitt eine statorseitigen Leitschaufelkranzes oder um einen statorseitigen Strömungskanalabschnitt handeln.During a thermal expansion of the component 31 during operation, the same comes into abutment on the section 30 of the support element 21 'and thus prevents hot gas from the flow channel from entering a housing-side recess through a gap 32 formed between the support element 21 and the component 31. This component 31 may be a section of a stator vane ring or a stator-side flow channel section.

Eine radial innere Kontur 35 des Abschnitts 29 des Stützelements 21', die einen Strömungskanal radial außen abschnittsweise begrenzt, nämlich im Übergangsbereich zum Bauteil 31, ist derart ausgestaltet bzw. konturiert, dass dieselbe eine Gasströmung nach radial innen lenkt und so einen Heißgaseintritt über den Spalt 32 in die gehäuseseitige Ausnehmung 23 verhindert bzw. deutlich reduziert.A radially inner contour 35 of the portion 29 of the support element 21 ', which limits a flow channel radially outwardly in sections, namely in the transition region to the component 31, is configured or contoured such that it directs a gas flow radially inward and thus a hot gas inlet via the gap 32 prevented in the housing-side recess 23 and significantly reduced.

Auch im Ausführungsbeispiel der Fig. 3 ist ein Hitzeschild bzw. Wärmeschild 33 vorhanden, der jedoch im Unterschied zum Ausführungsbeispiel der Fig. 1 zusammen mit dem Stützelement 21' am Flansch 20 befestigt ist. Auch der Wärmeschild 33 der Fig. 3 verhindert einen Heißgaseintritt in eine gehäuseseitige Ausnehmung. Der Wärmeschild 33 ist vorzugsweise als metallischer Ring ausgebildet.Also in the embodiment of Fig. 3 is a heat shield or heat shield 33 is present, however, in contrast to the embodiment of Fig. 1 is attached to the flange 20 together with the support member 21 '. Also, the heat shield 33 of Fig. 3 prevents a hot gas entering a housing-side recess. The heat shield 33 is preferably formed as a metallic ring.

Mit der hier vorliegenden Erfindung kann auf konstruktiv einfache Art und Weise eine effektive und zuverlässige Spaltmaßhaltung zwischen radial außen liegenden Enden von Laufschaufeln eines Laufschaufelkranzes und einem sich radial außen anschließenden Mantelring 16 gewährleistet werden. Der Mantelring 16 ist thermisch vom Gehäuse über mindestens eine Engstelle 18, 18A, 18B entkoppelt.With the present invention, an effective and reliable Spaltmaßhaltung between radially outer ends of blades of a blade ring and a radially outer adjoining shroud 16 can be ensured in a structurally simple manner. The shroud 16 is thermally decoupled from the housing via at least one constriction 18, 18A, 18B.

Ein Verkippen des Mantelrings 16 wird vorzugsweise durch ein Stützelement 21 bzw. 21' verhindert, welches den Mantelring 16 mechanisch stabilisiert sowie insbesondere gegenüber Heißgaseintritt abdichtet.A tilting of the shroud 16 is preferably prevented by a support member 21 and 21 ', which mechanically stabilizes the shroud 16 and seals in particular against hot gas inlet.

Über einen zusätzlichen Wärmeschild 24 bzw. 33 kann die Spaltmaßhaltung weiter verbessert werden.Via an additional heat shield 24 or 33, the Spaltmaßhaltung can be further improved.

Claims (10)

  1. Housing-side structure of a turbomachine, in particular of a gas turbine, comprising a casing ring, which is in particular segmented, a stator-side housing part (19) and a support element (21; 21'), the casing ring (16) being connected to the stator-side housing part (19) which is radially adjacent to the casing ring (16) on the outside and being thermally decoupled from said housing part via at least one constriction (18, 18A, 18B), the constriction (18, 18A, 18B) having a smaller extent compared with the casing ring (16) and the housing part (19) in the axial direction of the turbomachine, a flange (20) being formed on the stator-side housing part (19) which is radially adjacent to the casing ring (16) on the outside, characterized in that the support element (21; 21') is fixed to the flange (20), at least one portion (22; 28, 29) of which element abuts a downstream end of the casing ring (16) for the stabilization thereof.
  2. Housing-side structure according to claim 1, characterized in that only one portion (22) of the support element (21), which is used for stabilizing the casing ring (16), abuts the downstream end of the casing ring (16), this portion (22) extending substantially in a horizontal or axial direction.
  3. Housing-side structure according to claim 1, characterized in that one portion (28) of the support element (21') used for stabilizing the casing ring (16) that extends substantially in a horizontal or axial direction and one portion (29) thereof that extends substantially in a vertical or radial direction abut the downstream end of the casing ring (16).
  4. Housing-side structure according to either claim 2 or claim 3, characterized in that one portion (30) of the support element (21') used for stabilizing the casing ring (16) that extends substantially in a horizontal or axial direction protrudes in a downstream direction with respect to the casing ring (16) and forms a stop for an adjacent component (31), the adjacent component coming into abutment against said stop when said component is thermally expanded.
  5. Housing-side structure according to any of claims 1 to 4, characterized by a heat shield (24; 33) that prevents hot gas from entering a housing-side recess.
  6. Housing-side structure according to claim 5, characterized in that the heat shield (33), together with the support element (21'), which is used for stabilizing the casing ring (16), is fixed to the flange (20) of the stator-side housing part (19) which is radially adjacent to the casing ring (16) on the outside.
  7. Housing-side structure according to claim 5, characterized in that a first end (25) of the heat shield (24) is inserted into a recess (26) in a stator-side component (15) which adjoins the casing ring (16) downstream thereof, and a second end (27) of said shield abuts the support element (21), which is used for stabilizing the casing ring (16), or abuts the flange (20) of the stator-side housing part (19).
  8. Housing-side structure according to any of claims 5 to 7, characterized in that the heat shield (24; 33) is designed as a metal ring.
  9. Housing-side structure of a turbomachine, in particular of a gas turbine, comprising a casing ring which is in particular segmented and has a run-in lining for radially outer ends of rotor-side rotating blades of a rotating blade ring, and comprising a component that is adjacent to the casing ring in a downstream direction, characterized in that the housing-side structure is designed according to any of claims 1 to 8.
  10. Turbomachine, in particular a gas turbine, comprising a stator and a rotor, the rotor having rotating blades and the stator having a housing and guide blades, the rotor-side rotating blades forming at least one rotating blade ring, the, or each, rotating blade ring being adjacent to a radially outer end on a stator-side casing ring of a housing-side structure of the housing, being enclosed by said casing ring and defining a gap together therewith, each casing ring having a run-in lining for the radially outer ends of the rotor-side rotating blades of each rotating blade ring, characterized in that the housing-side structure is designed according to any of claims 1 to 8.
EP11785296.2A 2010-09-01 2011-08-29 Housing structure of a turbomachine Not-in-force EP2611992B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010036071A DE102010036071A1 (en) 2010-09-01 2010-09-01 Housing-side structure of a turbomachine
PCT/DE2011/001667 WO2012028140A1 (en) 2010-09-01 2011-08-29 Housing-side structure of a turbomachine

Publications (2)

Publication Number Publication Date
EP2611992A1 EP2611992A1 (en) 2013-07-10
EP2611992B1 true EP2611992B1 (en) 2018-03-21

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Application Number Title Priority Date Filing Date
EP11785296.2A Not-in-force EP2611992B1 (en) 2010-09-01 2011-08-29 Housing structure of a turbomachine

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US (1) US9540953B2 (en)
EP (1) EP2611992B1 (en)
DE (1) DE102010036071A1 (en)
WO (1) WO2012028140A1 (en)

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Publication number Priority date Publication date Assignee Title
EP2679777A1 (en) * 2012-06-28 2014-01-01 Alstom Technology Ltd Compressor for a gas turbine and method for repairing and/or changing the geometry of and/or servicing said compressor
JP5889266B2 (en) * 2013-11-14 2016-03-22 三菱重工業株式会社 Turbine
DE102018113997A1 (en) * 2018-06-12 2019-12-12 Rolls-Royce Deutschland Ltd & Co Kg Housing arrangement for an axial compressor of a gas turbine engine
DE102018116062A1 (en) 2018-07-03 2020-01-09 Rolls-Royce Deutschland Ltd & Co Kg Structure assembly for a compressor of a turbomachine
US12116898B2 (en) * 2023-01-26 2024-10-15 Pratt & Whitney Canada Corp. Ram air driven blade tip clearance control system for turboprop engines

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US3825364A (en) * 1972-06-09 1974-07-23 Gen Electric Porous abradable turbine shroud
GB2117843B (en) * 1982-04-01 1985-11-06 Rolls Royce Compressor shrouds
FR2604750B1 (en) * 1986-10-01 1988-12-02 Snecma TURBOMACHINE PROVIDED WITH AN AUTOMATIC CONTROL DEVICE FOR TURBINE VENTILATION FLOWS
US5080557A (en) 1991-01-14 1992-01-14 General Motors Corporation Turbine blade shroud assembly
US5462403A (en) * 1994-03-21 1995-10-31 United Technologies Corporation Compressor stator vane assembly
US6783324B2 (en) * 2002-08-15 2004-08-31 General Electric Company Compressor bleed case
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FR2885168A1 (en) * 2005-04-27 2006-11-03 Snecma Moteurs Sa SEALING DEVICE FOR A TURBOMACHINE ENCLOSURE, AND AIRCRAFT ENGINE EQUIPPED WITH SAME
FR2913050B1 (en) * 2007-02-28 2011-06-17 Snecma HIGH-PRESSURE TURBINE OF A TURBOMACHINE
FR2938873B1 (en) 2008-11-21 2014-06-27 Turbomeca POSITIONING DEVICE FOR RING SEGMENT

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Publication number Publication date
DE102010036071A1 (en) 2012-03-01
EP2611992A1 (en) 2013-07-10
WO2012028140A1 (en) 2012-03-08
US9540953B2 (en) 2017-01-10
US20130183149A1 (en) 2013-07-18

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