EP2087208B9 - Turbo engine - Google Patents
Turbo engine Download PDFInfo
- Publication number
- EP2087208B9 EP2087208B9 EP07846281A EP07846281A EP2087208B9 EP 2087208 B9 EP2087208 B9 EP 2087208B9 EP 07846281 A EP07846281 A EP 07846281A EP 07846281 A EP07846281 A EP 07846281A EP 2087208 B9 EP2087208 B9 EP 2087208B9
- Authority
- EP
- European Patent Office
- Prior art keywords
- ring
- bellows
- rotor
- turbo
- cavity
- 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
Links
Images
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
- 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
- F01D11/20—Actively adjusting tip-clearance
- F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
- F05D2250/611—Structure; Surface texture corrugated undulated
Definitions
- the invention relates to a turbomachine, in particular a gas turbine, 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 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 via adjusting devices can be adjusted or adjusted in its gap, so as to automatically influence the gap and on all Operating conditions to ensure optimum cleavage. It is after the DE 10 2004 037 955 A1 the radially inner housing wall or the shroud segmented in the circumferential direction, wherein preferably each segment is associated with a separate adjusting device.
- the adjusting devices are preferably designed as electro-mechanical actuators.
- the DE 101 17 231 A1 discloses a turbomachine with a stator and a rotor, wherein the gap between radially outer ends of the blades and the radially inner housing wall by means of a pneumatic, so compressed air operated, actuator unit of a rotor gap control module can be adjusted.
- the pneumatic actuator unit of the disclosed therein rotor gap control module has an actuator chamber, a pressure chamber and the actuator chamber and the pressure chamber connecting valves, which are inflated depending on the prevailing pressure in the actuator chamber sealing elements of the rotor gap control module, so in the sense of a pneumatic active clearance Control to adjust or adjust the gap of the gap between radially outer ends of blades and the outer ring of the housing.
- the DE 29 22 835 C2 and the US 5,211,534 reveal further turbomachinery with a pneumatic or pneumatic Active Clearance Control.
- the turbomachine according to DE 29 22 835 C2 via a stator and a rotor, wherein the gap between radially outer ends of the blades and an inner ring or shroud of a housing wall can be adjusted pneumatically.
- the shroud ring is connected via resilient side walls with a support ring, wherein the shroud, the support ring and the side walls form a bellows-like structure.
- the gap between radially outer ends of the blades and the shroud can be adjusted.
- the flexible side walls arched several times.
- the side walls are after the DE 29 22 835 C2 Accordingly, seen in the axial direction in sections, inwardly into the cavity and partially outwardly curved out of the cavity.
- the document US-A-5,344,284 protects a pneumatic Active Clearance Control System with a rigid, sheet-like, circumferentially multi-segmented squelch, with each pad segment radially movable via a separate, flexible, rubber-like bellows.
- the bellows at the upstream and downstream end simply in the cavity of the bellows in curved walls. From the vertex of the curvature to the radially inner end of the bellows wall, a sealing overlap of the bellows wall with a radially outwardly projecting edge of the rigid Anstreifbelags is present. In this area, the bellows wall in the axial direction to the outside is not or only very limited mobility.
- the structure after US-A-5,344,284 is a so-called composite consisting of bellows and shroud without connection to adjacent vane rings.
- the present invention is based on the problem to provide a novel turbomachine with a pneumatic Active Clearance Control.
- each wall connecting the jacket ring to the support ring is seen in the axial direction to be simply inwardly inward arched into the respective cavity.
- each curved wall is designed in the manner of a toggle lever, wherein the wall sections include an obtuse angle of greater than 90 ° and are suitable for receiving pressure forces.
- Fig. 1 shows a partial cross-section through a stator of a compressor 10 of a turbomachine, wherein the stator comprises a housing 11 and a plurality of stationary vanes 12.
- the stator-side guide vanes 12 form so-called vane rings which, viewed in the axial direction, are arranged one behind the other.
- a total of four fixed, stator vane rings 13, 14, 15 and 16 are shown.
- the compressor 10 comprises an in Fig. 1 Rotor, not shown, wherein the rotor of a plurality of axially arranged behind the other, not shown rotor disks is formed, each rotor disk in the circumferential direction next to each other several, also not shown blades carries.
- the rotor blades associated, circumferentially juxtaposed blades form so-called blade rings, wherein between each two adjacent Leitschaufelkränzen 13 and 14, 14 and 15 and 15 and 16 are each a non-illustrated blade ring is arranged.
- the housing 11 of the stator of the compressor 10 comprises a radially inner housing wall, wherein the radially inner housing wall in the region of each rotor-side, in Fig. 1 not shown blade ring forms a so-called inner ring or shroud 17 and surrounds the respective blade ring radially on the outside.
- the housing 11 further comprises a radially outer housing wall 18th
- each non-illustrated, rotor-side blade ring forms the radially inner housing wall in the region of each non-illustrated, rotor-side blade ring a so-called shroud ring 17 which surrounds the blade ring radially outward.
- shroud ring 17 which surrounds the blade ring radially outward.
- a radial gap is formed, which is subject to considerable changes during operation of the compressor, since on the one hand the blades and the respective shrouds have a different thermal behavior and on the other hand, the blades subject to a change in length due to the centrifugal forces or centrifugal forces acting during operation.
- the present invention now relates to such details, with the aid of which radial gaps between radially outer ends of blade rings and the respective shroud 17 can be accurately maintained.
- Fig. 1 are the shrouds 17, which extend between the vane rings 13 and 14 and 15 and 16, connected via curved and resilient walls 19 with a support ring 20, wherein the respective support ring 20 between the respective shroud 17 and the radially outer housing wall 18 is arranged ,
- the respective shroud 17, the support ring 20 and the between the respective shroud 17 and the respective support ring 20 extending, curved walls 19 each form a bellows-like structure 21, which has a cavity 22.
- the respective bellows-like structure 21 and thus the cavity 22 surrounds in the circumferential direction completely and thus closed the respective blade ring.
- the gap between the respective shroud 17 and the radially outer end of the respective blade ring is pneumatically adjustable.
- the respective radially inner shroud 17 can be pressed radially inward and the respective radially outer support ring 20 radially outward.
- an opposite deformation of the respective bellows-like structure 21 can be realized.
- Fig. 1 In the preferred embodiment of Fig. 1 are the curved, elastically yielding walls 19 of the bellows-like structures 21 seen in the axial direction only curved inwardly into the respective cavity 22 into it. In the region of a vertex of the curvature wall sections of the respective wall 19 close a relatively obtuse angle ⁇ of greater than 90 °.
- Fig. 2 shows a schematic representation of a bellows-like structure 21, described.
- Fig. 2 shows Fig. 2 in that, in the region of a vertex 29 of the curvature, the wall sections of the respective wall 19 enclose an obtuse angle ⁇ .
- curved walls 19 are superimposed at an increase in pressure in the corresponding cavity 22 of the respective bellows-like structure 21, two effects.
- the respective bellows-like structure 21 has a greater radial extent than axial extent.
- the walls 19 of the respective bellows-type structure 21 have a greater radial extent than axial extent.
- each bellows-like structures 21 seen in the radial direction have an approximately constant wall thickness.
- the curved walls 19 seen in the radial direction have a variable wall thickness.
- each bellows-like structure 21 has a smaller wall thickness than the respective radially outer support ring 20.
- the support ring 20 of each bellows-like structure 21 is therefore designed with a thicker wall thickness than the respective shroud 17. This ensures in that deformation of the bellows-like structure 21 caused by variation of the pressure prevailing in the respective cavity 22 primarily acts on the shroud 17.
- Fig. 1 can be further seen that the shroud 17 of each bellows-like structure 21 in a center region seen in the axial direction has a radially outwardly curved, projecting into the respective cavity 22 contour 23.
- Each bellows-like structure 21 is in each case assigned at least one compressed-air line 24 in order to either introduce compressed air into the respective cavity 22 of the respective bellows-like structure 21 or to discharge it from the same compressed air.
- a simpler representation shows Fig. 1 such a compressed-air line 24 exclusively for the bellows-like structure 21 positioned in the axial direction between the two guide-blade rings 13 and 14.
- Each bellows-like structure 21 is assigned at least one such compressed air line 24. The more such compressed air lines 24 per bellows-like structure 21 are present, the faster compressed air can be introduced into the respective cavity 24 or derived from the same.
- a sensor unit 25 In the embodiment of Fig. 1 is between the two Leitschaufelkränzen 13 and 14 and between the two Leitschaufelkränzen 15 and 16 each a bellows-like structure 21 arranged between the two Leitschaufelkränzen 14 and 15, however, no such bellows-like structure is present. Rather, according to Fig. 1 between the two Leitschaufelkränzen 14 and 15 and thus arranged in the region of a rotor blade ring arranged between the same, a sensor unit 25.
- the sensor unit 25 With the sensor unit 25, at least the radial dimension of the gap between the corresponding blade ring and the shell ring 17 surrounding this blade ring can be measured. Via a signal line 26, the sensor unit 25 transmits a corresponding actual value to a control device, not shown, wherein the control device compares the actual value with a desired value and depending on the pressure prevailing in the cavities 22 of the bellows structures 21 set pressure such that the actual value approaches the target value ,
- the compressed air supply into the cavities 22 and the compressed air discharge from the cavities 22 of the bellows-like structures 21 is adjustable via individual valves, so as to adjust the pressure prevailing in the cavities 22 of the two bellows-like structures 21 pressure individually and so each Dimension of the radial gap between the shroud 17 and the corresponding blade ring depending on the respective radial extent of the blade ring individually set.
- the two bellows-like structures 21 are each divided by axially extending parting planes in the axial direction, wherein during manufacture, the two axial halves of the bellows-like structures 21 are welded together. Alternatively, it is also possible to divide the bellows-like structures in the radial direction.
- Fig. 1 and 2 is in the region of each bellows-like structure 21 each wall 19 seen in the axial direction only curved inwardly into the respective cavity 22 into it.
- the bellows-type structure 30 according to FIG. 3 has a greater axial extent than radial extent, in particular the walls 19 of the bellows-type structure 30 have a greater axial extent than radial extent.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung betrifft eine Turbomaschine, insbesondere eine Gasturbine, nach dem Oberbegriff des Anspruchs 1.The invention relates to a turbomachine, in particular a gas turbine, according to the preamble of
Aus der
Die
Die
So verfügt die Turbomaschine gemäß
Das Dokument
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige Turbomaschine mit einem pneumatischen Active Clearance Control zu schaffen.On this basis, the present invention is based on the problem to provide a novel turbomachine with a pneumatic Active Clearance Control.
Dieses Problem wird durch eine Turbomaschine gemäß Anspruch 1 gelöst. In bekannter Weise ist im Bereich der oder jeder faltenbalgartigen Struktur jede den Mantelring mit dem Stützring verbindende Wand in Axialrichtung gesehen ausschließlich einfach nach innen in den jeweiligen Hohlraum hinein gewölbt. Erfindungsgemäß ist jede gewölbte Wand nach Art eines Kniehebels ausgeführt, wobei die Wandabschnitte einen stumpfen Winkel von größer als 90° einschließen und zur Aufnahme von Druckkräften geeignet sind.This problem is solved by a turbomachine according to
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 Querschnitt durch statorseitige Baugruppen einer erfindungsgemäßen Turbomaschine; und
- Fig. 2
- eine schematisierte Darstellung einer faltenbalgartigen Struktur der Turbomaschine gemäß
Fig. 1 .
- Fig. 1
- a cross section through stator-side modules of a turbomachine according to the invention; and
- Fig. 2
- a schematic representation of a bellows-like structure of the turbomachine according to
Fig. 1 ,
Neben dem Stator umfasst der Verdichter 10 einen in
Das Gehäuse 11 des Stators des Verdichters 10 umfasst eine radial innenliegende Gehäusewand, wobei die radial innenliegende Gehäusewand im Bereich jedes rotorseitigen, in
Wie bereits ausgeführt, bildet die radial innenliegende Gehäusewand im Bereich jedes nicht-dargestellten, rotorseitigen Laufschaufelkranzes einen sogenannten Mantelring 17, der den Laufschaufelkranz radial außen umschließt. Zwischen den radial außenliegenden Enden der Laufschaufeln eines jeden Laufschaufelkranzes und dem jeweiligen Mantelring 17 ist dabei ein radialer Spalt ausgebildet, der während des Betriebs des Verdichters erheblichen Veränderungen unterliegt, da einerseits die Laufschaufeln und die jeweiligen Mantelringe ein unterschiedliches thermisches Verhalten aufweisen und da andererseits die Laufschaufeln aufgrund der im Betrieb wirkenden Fliehkräfte bzw. Zentrifugalkräfte einer Längenänderung unterliegen.As already stated, forms the radially inner housing wall in the region of each non-illustrated, rotor-side blade ring a so-called
Die Einhaltung definierter Abmessungen des jeweiligen Spalts zwischen den radial außenliegenden Enden der Laufschaufeln eines Laufschaufelkranzes und dem jeweiligen Mantelring 17 bereitet während des Betriebs erhebliche Schwierigkeiten, ist jedoch zur Optimierung des Wirkungsgrads von entscheidender Bedeutung.Compliance with defined dimensions of the respective gap between the radially outer ends of the blades of a blade ring and the
Die hier vorliegende Erfindung betrifft nun solche Details, mit Hilfe derer radiale Spalte zwischen radial außenliegenden Enden von Laufschaufelkränzen und dem jeweiligen Mantelring 17 exakt eingehalten werden können.The present invention now relates to such details, with the aid of which radial gaps between radially outer ends of blade rings and the
Gemäß
Durch Veränderung eines im jeweiligen Hohlraum 22 der faltenbalgähnlichen Struktur 21 herrschenden Drucks ist der Spalt zwischen dem jeweiligen Mantelring 17 und dem radial außenliegenden Ende des jeweiligen Laufschaufelkranzes pneumatisch einstellbar. Bei einer Druckerhöhung im Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 kann der jeweilige, radial innenliegende Mantelring 17 nach radial innen und der jeweilige, radial außenliegende Stützring 20 nach radial außen gedrückt werden. Durch eine Druckreduzierung im Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 kann eine entgegengesetzte Verformung der jeweiligen faltenbalgähnlichen Struktur 21 realisiert werden.By changing a prevailing in the
Im bevorzugten Ausführungsbeispiel der
So zeigt
Erstens werden bedingt durch die Druckerhöhung im Hohlraum 22 der jeweilige Mantelring 17 sowie der jeweilige Stützring 20 unmittelbar in Radialrichtung gesehen auseinander gedrückt. Zweitens wird dieses radiale Auseinanderdrücken des jeweiligen Mantelrings 17 und Stützrings 20 durch einen kniehebelartigen Effekt der gewölbten Wände 19 unterstützt bzw. zumindest nicht behindert. Dabei sind die gewölbten Wände 19 im Wesentlichen ausschließlich Druckkräften ausgesetzt.First, due to the pressure increase in the
Gemäß
Im gezeigten Ausführungsbeispiel der
Wie ebenfalls
Hierdurch wird erzielt, dass bei einer Verformung des Mantelrings 17 infolge einer Druckänderung im Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 eine äußere Kontur 28 des Mantelrings 17 in Radialrichtung gesehen im Wesentlichen ausschließlich parallel verschoben wird, so dass ein Spalt zwischen dem Mantelring 17 und dem Laufschaufelkranz exakt eingestellt werden kann.As a result, it is achieved that upon deformation of the
Jeder faltenbalgähnlichen Struktur 21 ist jeweils mindestens eine Druckluftleitung 24 zugeordnet, um in den jeweiligen Hohlraum 22 der jeweiligen faltenbalgähnlichen Struktur 21 entweder Druckluft einzuleiten bzw. aus demselben Druckluft abzuleiten. Aus Gründen einer einfacheren Darstellung zeigt
Im Ausführungsbeispiel der
Mit der Sensoreinheit 25 kann zumindest die radiale Abmessung des Spalts zwischen dem entsprechenden Laufschaufelkranz und dem diesen Laufschaufelkranz umgebenden Mantelring 17 vermessen werden. Über eine Signalleitung 26 übermittelt die Sensoreinheit 25 einen entsprechenden Istwert an eine nicht dargestellte Regeleinrichtung, wobei die Regeleinrichtung den Istwert mit einem Sollwert vergleicht und abhängig hiervon den in den Hohlräumen 22 der faltenbalgartigen Strukturen 21 herrschenden Druck derart einstellt, dass sich der Istwert dem Sollwert annähert.With the
Dabei kann vorgesehen sein, dass die Druckluftzufuhr in die Hohlräume 22 bzw. die Druckluftabfuhr aus den Hohlräumen 22 der faltenbalgartigen Strukturen 21 über individuelle Ventile einstellbar ist, um so den in den Hohlräumen 22 der beiden faltenbalgartigen Strukturen 21 herrschenden Druck individuell einzustellen und so jeweils die Abmessung des radialen Spalts zwischen dem Mantelring 17 und dem entsprechenden Laufschaufelkranz anhängig von der jeweiligen Radialerstreckung des Laufschaufelkranzes individuell einzustellen.It can be provided that the compressed air supply into the
Alternativ kann vorgesehen sein, die Druckluftzufuhr in die Hohlräume 22 der faltenbalgartigen Strukturen 21 bzw. die Druckluftabfuhr aus denselben über ein gemeinsames Ventil einzustellen. Durch unterschiedliche Radialerstreckungen der jeweiligen Laufschaufelkränze des Verdichters 10 erforderliche, unterschiedliche Verformungen der faltenbalgähnlichen Strukturen 21 sind dann durch eine angepasste Wölbung der gewölbten Wände 19 und/oder eine angepasste Wandstärke der gewölbten Wände 19 und/oder durch eine angepasste radiale Erstreckung der faltenbalgähnlichen Strukturen 21 erzielbar.Alternatively, it can be provided to adjust the compressed air supply into the
Gemäß
Gemäß
Die faltenbalgartige Struktur 30 gemäß Fig. 3 weist eine größere Axialerstreckung als Radialerstreckung auf, insbesondere weisen die Wände 19 der faltenbalgartigen Struktur 30 eine größere Axialerstreckung als Radialerstreckung auf.The bellows-type structure 30 according to FIG. 3 has a greater axial extent than radial extent, in particular the
Claims (9)
- A turbo-engine having a stator and a rotor, wherein the rotor has rotor blades and the stator has a housing (11) and guide vanes (12), wherein the rotor blades on the rotor side form at least one rotor-blade ring, wherein the or each rotor-blade ring at a radially external end adjoins an inner ring or jacket ring (17) of the housing (11) on the stator side, is surrounded by the same and delimits a gap with the same, wherein the respective jacket ring (17) is connected to a support ring (20) by way of curved walls (19) which together with the jacket ring (17) and the support ring (20) delimit a cavity (22) and form a bellows-like structure (21), wherein by changing a pressure that prevails in the cavity (22) of the respective bellows-like structure (21) it is possible to adjust pneumatically the gap between the jacket ring (17) and the radially external end of the respective rotor-blade ring, and wherein in the region of the or each bellows-like structure (21) each wall (19), viewed in the axial direction, is curved only once inwards into the respective cavity (22), wherein each wall (19) is constructed in the manner of a toggle lever against action of an excess pressure with respect to the environment, wherein in the region of a vertex (29) of the curvature wall sections of the respective wall (19) enclose an obtuse angle of more than 90°, and wherein the wall sections are suitable for taking up pressure forces,
characterised in that
the jacket ring (17) together with the support ring (20) and the curved walls (19) present, in an axial-radial section, an integral formation which is connected to a guide-vane ring in a form-locking manner on at least one side in the region of the jacket ring. - A turbo-engine according to claim 1,
characterised in that
the walls (19) have a constant wall thickness. - A turbo-engine according to claim 1,
characterised in that
the walls have a variable wall thickness, viewed in the radial direction. - A turbo-engine according to one of claims 1 to 3,
characterised in that
in the region of the or each bellows-like structure (21) the jacket ring (17) has a smaller wall thickness than the support ring (20). - A turbo-engine according to one of claims 1 to 4,
characterised in that
in the region of the or each bellows-like structure (21) the jacket ring (17) has in a central region, viewed in the axial direction, a contour (23) that is curved into the cavity (22). - A turbo-engine according to one of claims 1 to 5,
characterised in that
associated with the or each bellows-like structure there is in each case at least one compressed-air line (24) in order to introduce compressed air into the respective cavity (22) or to divert it out of the cavity. - A turbo-engine according to one of claims 1 to 6,
characterised in that
associated with at least two rotor-blade rings there is a respective bellows-like structure (21), and in that arranged between the two rotor-blade rings, with which a respective bellows-like structure (21) is associated, there is at least one rotor-blade ring with which a sensor unit (25) is associated, wherein the or each sensor unit (25) measures the radial dimension of the gap in the region of the respective rotor-blade ring and transmits a corresponding actual value to a regulating device, and wherein the regulating device compares the actual value with a desired value and as a function thereof adjusts the pressure that prevails in the cavities (22) of the respective bellows-like structures (21) in such a way that the actual value approximates the desired value. - A turbo-engine according to claim 7,
characterised in that
the compressed-air supply into the cavities (22) or the compressed-air removal from the cavities (22) can be adjusted by way of a common valve, wherein, as a result of differing radial extents of the respective rotor-blade rings, necessary different deformations of the bellows-like structures (21) can be attained by means of an adapted curvature and/or adapted wall thickness of the curved walls of the respective bellows-like structures (21). - A turbo-engine according to claim 7,
characterised in that
the compressed-air supply into the cavities (22) or the compressed-air removal from the cavities (22) can be adjusted by way of individual valves, wherein, as a result of differing radial extents of the respective rotor-blade rings, necessary different deformations of the bellows-like structures (21) can be attained by means of an individual compressed-air supply or compressed-air removal.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102006052786A DE102006052786B4 (en) | 2006-11-09 | 2006-11-09 | turbomachinery |
PCT/DE2007/001946 WO2008055474A1 (en) | 2006-11-09 | 2007-10-30 | Turbo engine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2087208A1 EP2087208A1 (en) | 2009-08-12 |
EP2087208B1 EP2087208B1 (en) | 2011-01-26 |
EP2087208B9 true EP2087208B9 (en) | 2012-04-25 |
Family
ID=39167469
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07846281A Not-in-force EP2087208B9 (en) | 2006-11-09 | 2007-10-30 | Turbo engine |
Country Status (6)
Country | Link |
---|---|
US (1) | US8608435B2 (en) |
EP (1) | EP2087208B9 (en) |
AT (1) | ATE497088T1 (en) |
CA (1) | CA2666200A1 (en) |
DE (2) | DE102006052786B4 (en) |
WO (1) | WO2008055474A1 (en) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2218880A1 (en) * | 2009-02-16 | 2010-08-18 | Siemens Aktiengesellschaft | Active clearance control for gas turbines |
FR3024492B1 (en) * | 2014-07-29 | 2019-08-23 | Safran Aircraft Engines | ELEMENT COMPRISING A STATOR AND A TURBOMACHINE ROTOR WITH A SEAL AND TESTING THIS SEAL |
US10794213B2 (en) * | 2016-06-21 | 2020-10-06 | Rolls-Royce North American Technologies Inc. | Blade tip clearance control for an axial compressor with radially outer annulus |
US10851712B2 (en) | 2017-06-27 | 2020-12-01 | General Electric Company | Clearance control device |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2922835C2 (en) | 1979-06-06 | 1985-06-05 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Circumferential gap seal on axial flow machines |
US4329114A (en) * | 1979-07-25 | 1982-05-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Active clearance control system for a turbomachine |
JPS5741407A (en) * | 1980-08-22 | 1982-03-08 | Hitachi Ltd | Sealing mechanism on top of turbine rotor blade |
GB2103294B (en) * | 1981-07-11 | 1984-08-30 | Rolls Royce | Shroud assembly for a gas turbine engine |
JPS5820904A (en) * | 1981-07-29 | 1983-02-07 | Hitachi Ltd | Seal structure of tip of moving blade for gas turbine |
GB2169962B (en) * | 1985-01-22 | 1988-07-13 | Rolls Royce | Blade tip clearance control |
JPS62142808A (en) * | 1985-12-18 | 1987-06-26 | Toshiba Corp | Clearance control device for gas turbine |
US4784569A (en) * | 1986-01-10 | 1988-11-15 | General Electric Company | Shroud means for turbine rotor blade tip clearance control |
GB2195715B (en) * | 1986-10-08 | 1990-10-10 | Rolls Royce Plc | Gas turbine engine rotor blade clearance control |
DE3830762C2 (en) * | 1988-09-09 | 1994-08-18 | Mtu Muenchen Gmbh | Device for holding a jacket ring in gas turbines |
US5048288A (en) * | 1988-12-20 | 1991-09-17 | United Technologies Corporation | Combined turbine stator cooling and turbine tip clearance control |
US4971517A (en) * | 1988-12-27 | 1990-11-20 | Allied-Signal Inc. | Turbine blade clearance controller |
GB9103809D0 (en) * | 1991-02-23 | 1991-04-10 | Rolls Royce Plc | Blade tip clearance control apparatus |
US5344284A (en) * | 1993-03-29 | 1994-09-06 | The United States Of America As Represented By The Secretary Of The Air Force | Adjustable clearance control for rotor blade tips in a gas turbine engine |
DE10117231A1 (en) | 2001-04-06 | 2002-10-31 | Hodson Howard | Rotor gap control module |
US6918743B2 (en) * | 2002-10-23 | 2005-07-19 | Pratt & Whitney Canada Ccorp. | Sheet metal turbine or compressor static shroud |
DE102004037955A1 (en) | 2004-08-05 | 2006-03-16 | Mtu Aero Engines Gmbh | Turbomachine, in particular gas turbine |
-
2006
- 2006-11-09 DE DE102006052786A patent/DE102006052786B4/en not_active Expired - Fee Related
-
2007
- 2007-10-30 EP EP07846281A patent/EP2087208B9/en not_active Not-in-force
- 2007-10-30 US US12/514,283 patent/US8608435B2/en not_active Expired - Fee Related
- 2007-10-30 DE DE502007006392T patent/DE502007006392D1/en active Active
- 2007-10-30 AT AT07846281T patent/ATE497088T1/en active
- 2007-10-30 WO PCT/DE2007/001946 patent/WO2008055474A1/en active Application Filing
- 2007-10-30 CA CA002666200A patent/CA2666200A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
---|---|
EP2087208A1 (en) | 2009-08-12 |
US20100003122A1 (en) | 2010-01-07 |
ATE497088T1 (en) | 2011-02-15 |
EP2087208B1 (en) | 2011-01-26 |
WO2008055474A1 (en) | 2008-05-15 |
DE102006052786A1 (en) | 2008-05-15 |
CA2666200A1 (en) | 2008-05-15 |
US8608435B2 (en) | 2013-12-17 |
DE502007006392D1 (en) | 2011-03-10 |
DE102006052786B4 (en) | 2011-06-30 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2044293B1 (en) | Gas turbine with a peripheral ring segment comprising a recirculation channel | |
DE102011052236A1 (en) | Profiled axial-radial outlet diffuser | |
DE19807247A1 (en) | Turbomachine with rotor and stator | |
EP2466074A1 (en) | Gas turbine engine with piston ring sealing device | |
EP2239419A1 (en) | Axial turbo engine rotor with sealing disc | |
CH697962B1 (en) | Inner housing for a rotary machine, rotary machine and method for controlling a measure of a split ring in a rotary machine. | |
CH702000A2 (en) | Swirl chambers to the gap flow control. | |
DE102011054586A1 (en) | Sealing arrangement for a turbomachine | |
EP1624159A1 (en) | Gas turbine engine with shroud clearance control | |
EP2087208B9 (en) | Turbo engine | |
EP2853692B1 (en) | Sealing element for an axial flow engine | |
EP1914388A1 (en) | Sealing element for sealing a leakage passage between a rotor and a stator of a turbomachine. | |
CH709266B1 (en) | Turbine blade and method for balancing a tip shroud of a turbine blade and gas turbine. | |
DE102007050916A1 (en) | Stator arrangement for compressor of fluid conveying arrangement in gas turbine engine, has radial passage conduit formed in part of stator ring segment, where radial passage conduit is arranged adjacent to stator blade passage conduit | |
DE4309637A1 (en) | Radially flow-through turbocharger turbine | |
EP2129875B1 (en) | Turbo engine with active clearance control | |
EP2955336B1 (en) | Intermediate housing for a gas turbine and gas turbine with such an intermediate housing | |
EP3495639B1 (en) | Compressor module for a turbomachine reducing the boundary layer in an intermediate compressor case | |
DE102010005153A1 (en) | Housing system for an axial flow machine | |
DE102009003480A1 (en) | Steam turbine and method of assembling same | |
DE102010036071A1 (en) | Housing-side structure of a turbomachine | |
EP2650520B1 (en) | Aircraft gas turbine engine having a bleed channel in a guide vane root element of a bypass channel | |
EP3997310A1 (en) | Guide vane segment having a support portion rib | |
EP2122128B1 (en) | Turbine wheel | |
WO2008106931A1 (en) | Sealing element for sealing a gap between a stator and a rotor of an axial turbomachine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20090430 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR |
|
17Q | First examination report despatched |
Effective date: 20090908 |
|
DAX | Request for extension of the european patent (deleted) | ||
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: GERMAN |
|
REF | Corresponds to: |
Ref document number: 502007006392 Country of ref document: DE Date of ref document: 20110310 Kind code of ref document: P |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 502007006392 Country of ref document: DE Effective date: 20110310 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: VDEP Effective date: 20110126 |
|
LTIE | Lt: invalidation of european patent or patent extension |
Effective date: 20110126 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110526 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110427 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110507 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110526 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FD4D |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110426 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20111027 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502007006392 Country of ref document: DE Effective date: 20111027 |
|
BERE | Be: lapsed |
Owner name: MTU AERO ENGINES G.M.B.H. Effective date: 20111031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 Ref country code: MC Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111031 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111031 Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111031 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20111030 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20110126 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20131114 AND 20131120 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 497088 Country of ref document: AT Kind code of ref document: T Effective date: 20121031 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20121031 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20141024 Year of fee payment: 8 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 9 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20151030 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20151030 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 10 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 11 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20171023 Year of fee payment: 11 Ref country code: DE Payment date: 20171023 Year of fee payment: 11 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502007006392 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20190501 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20181031 |