EP2881545A1 - Sealing element, sealing device and gas turbine engine - Google Patents

Sealing element, sealing device and gas turbine engine Download PDF

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Publication number
EP2881545A1
EP2881545A1 EP13195751.6A EP13195751A EP2881545A1 EP 2881545 A1 EP2881545 A1 EP 2881545A1 EP 13195751 A EP13195751 A EP 13195751A EP 2881545 A1 EP2881545 A1 EP 2881545A1
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EP
European Patent Office
Prior art keywords
sealing element
mounting
turbomachine
angle
mounting direction
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13195751.6A
Other languages
German (de)
French (fr)
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EP2881545B1 (en
Inventor
Hans Dr. Stricker
Stefan Rauscher
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MTU Aero Engines AG
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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
Priority to EP13195751.6A priority Critical patent/EP2881545B1/en
Priority to ES13195751.6T priority patent/ES2628679T3/en
Priority to US14/558,415 priority patent/US9803494B2/en
Publication of EP2881545A1 publication Critical patent/EP2881545A1/en
Application granted granted Critical
Publication of EP2881545B1 publication Critical patent/EP2881545B1/en
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods

Definitions

  • the invention relates to a sealing element of a turbomachine according to the preamble of patent claim 1, a sealing device with at least one sealing element and a turbomachine with such a sealing device.
  • the sealing device is composed of a plurality of sealing elements or ring segments, each having at least one inlet or Anstreifbelag which is attached to a stationary with the housing portion in operative engagement support structure.
  • Known support structures have at least one dimensionally stable holding element, which is arranged in the mounted state of the turbomachine between two axially screwed together sections of the housing portion.
  • the support structures may each have a backup, which may also be referred to as mounting or securing position.
  • a fuse and at least one holding element are arranged one behind the other, wherein the fuse has a latching portion with an assembly angle in the mounting direction employed mounting surface and an employee employed in the opposite direction by a safety angle backup surface.
  • the safety angle is chosen such that a high holding force is achieved.
  • the mounting bracket is adjusted according to the safety angle, so that for mounting the support structure a correspondingly large mounting force must be applied, which can lead to a plastic deformation or deformation of the fuse.
  • the object of the invention is to provide a sealing element of a turbomachine, which eliminates the aforementioned disadvantages and in particular allows easy installation and a reliable position assurance during assembly. Furthermore, it is an object of the invention to provide a sealing device which is easy to assemble and disassemble in a turbomachine, and to provide a turbomachine whose at least one sealing device is held securely on a housing section during assembly or transport.
  • An inventive sealing element of a turbomachine for adjusting a radial gap between a blade row and a housing portion has a support structure with a front side, to which an inlet lining is attached, and a back, on which at least one dimensionally stable holding element for holding the support structure in a desired position on the Housing area is arranged.
  • the support structure has a fuse for securing the support structure in its desired position during assembly or transport.
  • the at least one retaining element and the fuse are arranged one behind the other in the mounting direction, wherein the fuse has a latching section with a mounting surface engaged by a mounting bracket in the mounting direction and a backup surface engaged by a safety angle in the opposite direction.
  • the latching section is also mounted elastically on the rear side via a spring section. According to the invention, the mounting angle is smaller than the safety angle.
  • the mounting angle is smaller than the safety angle can be achieved on the one hand a simple installation and on the other a high securing effect and thus a reliable position assurance during assembly.
  • the mounting angle and the safety angle are independent of each other and thus to their respective function - low assembly force or high holding force - optimally adaptable. Damage to the support structure due to an excessive mounting angle is excluded.
  • the mounting of the sealing element on the housing region can be made particularly easily if the at least one retaining element has a holding section extending in the mounting direction for forming a sliding engagement with a corresponding receptacle of the turbomachine.
  • the support structure can be transferred by a linear movement in its desired position.
  • the spring section allows an automatic deflection of the locking portion in a second direction and thus an automatic locking.
  • a further holding element may be provided, wherein the locking portion is preferably then arranged between the holding elements, wherein the further holding element can form a sliding engagement in the mounting direction with a corresponding receptacle of the turbomachine. Due to the sliding engagement of the second holding element in the mounting direction, both holding elements are simultaneously brought into operative engagement with the respective housing receptacle by a linear movement.
  • the spring portion is a profile with two legs arranged one above the other, with respect to a machine longitudinal axis of the turbomachine, outer or radially outer leg merges into the latching portion and the inner or radially inner leg merges into a fastened to the rear mounting portion.
  • a spring portion allows a large deflection or elasticity of the locking portion and is easy to manufacture.
  • Exemplary profiles with two legs are U-profiles, V-profiles and W-profiles.
  • To increase the spring action of the inner leg may be employed by an angle in the mounting direction.
  • the employment causes a change in the mounting bracket during mounting and the safety angle at a load in demounting direction. By this employment, the mounting force can be further reduced.
  • the outer leg preferably extends in the mounting direction and is thus not employed in the mounting direction.
  • the two legs are similar to one asymmetric U-profile to each other employed, which has a positive effect on the reduction of the mounting force and increase the holding force.
  • the mounting angle is smaller by at least 10 °, preferably by 20 ° to 30 °, smaller than a minimum securing angle.
  • the minimum securing angle is the smallest possible safety angle and depends essentially on the coefficient of friction between the housing section and the securing surface.
  • a disassembly of the sealing element can be simplified if the spring section is arranged in front of the latching section in the mounting direction and the latching section merges in the mounting direction in a rear free end portion.
  • the free end portion is arranged in the front dismounting direction and thus freely accessible during disassembly. In this way, for example, with a tool a radially outwardly inwardly directed compression force can be introduced into the spring portion and a radial overlap of the fuse element side backup surface can be reduced with the housing-side support surface.
  • a sealing device according to the invention of a turbomachine has a plurality of sealing elements according to the invention. Such a sealing device can be mounted without damage and is reliably secured during assembly in its desired position.
  • a turbomachine according to the invention has at least one sealing device according to the invention.
  • the turbomachine is characterized by an optimal radial gap in the area of the sealing device, since it is mounted without damage and also in its desired position.
  • FIG. 1 a first embodiment of a sealing element 1 according to the invention is shown in section along a machine longitudinal axis of a turbomachine.
  • the machine longitudinal axis extends in the axial direction.
  • Directional data such as axial or radial refer to the machine longitudinal axis.
  • Directional information such as upstream and downstream or location information such as front and rear, refer to the flow direction of a hot gas flowing through the turbomachine. If directional information and / or location information refer to a mounting direction or disassembly direction, this is explicitly mentioned.
  • the turbomachine is, for example, a gas turbine and in particular an aircraft engine.
  • the sealing element 1 is a ring segment of a sealing device, which is arranged here in a turbine-side housing portion 2 of the turbomachine. In principle, the sealing element 1 can also be arranged on the compressor side.
  • the sealing element 1 or the sealing device consisting of at least one sealing element serves for adjusting and in particular reducing a radial gap between the housing region 2 and a blade row 4 encompassed by the housing region 2.
  • the blade row 4 is arranged to rotate about the machine longitudinal axis in an annular space 6.
  • the annular space 6 is flowed through by the hot gas substantially in the direction of the machine longitudinal axis and here axially from left to right.
  • the housing portion 2 is here composed of two housing sections 8, 10 with annular flanges, which are screwed together as indicated by the dot-dash line 12 in the region of their annular flanges.
  • the housing sections 8, 10 themselves can be subdivided into a lower half and an upper half, which are or are joined in a horizontal plane.
  • the front housing section 8 has a receptacle 14 for interacting with a rear dimensionally stable holding element 16 of the sealing element 1.
  • the receptacle 14 is designed for this purpose as an axial projection extending in the flow direction with a radial contact surface 17.
  • the rear housing section 10 has an axial circumferential wall 18 extending downstream from the annular flange and a radially inwardly extending annular wall 20 from the circumferential wall 18 downstream of the annular flange.
  • the peripheral wall 18 has such a length or axial extent that in the assembled state of the sealing element 1 or the sealing device between the rear retaining element 16 and the annular wall 20, an axial gap is formed.
  • the annular wall 20 here has such a radial extent or height that it extends slightly radially inwardly beyond the receptacle 14 addition.
  • the sealing element 1 has an inlet or Anstreifbelag 21, which is arranged opposite to each other in the flow direction arranged circumferentially sealing webs 22, 24 of the blade row 4.
  • the sealing element 1 has a supporting structure 26.
  • the supporting structure 26 and the inlet lining 21 are metallic.
  • the inlet lining 21 and the support structure 26 are manufactured separately from each other and added later.
  • the inlet lining 21 can also be manufactured integrally with the supporting structure 26. This can be done, for example, by means of a generative manufacturing process such as laser sintering or a laser melting process and enables the production of the sealing element 1 as a closed ring and thus as a one-piece sealing device.
  • the support structure 26 has an axial base portion 28 and a radially disposed wall portion 30 disposed upstream of the base portion 28.
  • the base section 28 has a hot gas side or annular space-side front side 32, on which the inlet lining 21 is arranged, and an opposite cooling air side or the housing region 2 facing back 34.
  • the back 34 is provided with the rear support member 16, which is connected to the housing-side receptacle 14th interacts.
  • the rear support member 16 is here S-shaped with an attached at the back 34 axial leg portion 36, a radially extending from the foot portion 36 radially outwardly web 38 and an upstream of the web 38 extending axial head or holding portion 40th
  • the holding section 40 has in particular an upstream extending in the direction of the annular space 6 facing contact surface 42 for cooperation with the contact surface 17 of the receptacle 14th
  • a front dimensionally stable support member 44 which extends axially upstream of the Wandungsabitess 30 and cooperates with a corresponding stator-side receptacle 46.
  • the front retaining element 44 has an axially extending front-side radial contact surface 48 which cooperates with an axially extending abutment surface 49 of the receptacle 46.
  • the stator-side receptacle 46 is, for example, a rear platform region of an upstream row of guide vanes.
  • the support structure 26 has a fuse 50.
  • the sealing element 1 or the sealing device with its retaining elements 16, 44 in sliding engagement with the receptacles 14, 46, the sliding engagements can be solved by a sufficiently strong disassembly movement in the opposite direction 47, however.
  • a self-release of the sealing member 1 from the front housing portion 8 is prevented due to the fuse 50.
  • this means that the sealing element 1 or the sealing device is secured to the front housing section 8 in its desired position even when the rear housing section 10 is not yet bolted to the front housing section 8.
  • the fuse 50 extends from the rear side 34 between the holding elements 16, 44 and cooperates with a housing-side holding surface 52.
  • the holding surface 52 is an inclined surface that is disposed opposite to receiving the rear holding member 16 on the front housing portion 8 and extending between a radially inner peripheral surface 54 and an upstream radially outer circumferential surface 56 of the front housing portion 8. It thus extends obliquely in the mounting direction 57.
  • the fuse 50 has a latching portion 58 which is connected via a spring portion 60 and a mounting portion 62 on the back 34.
  • the mounting angle .alpha. is smaller than the securing angle .beta. Or .beta the securing angle ⁇ is greater than the mounting angle ⁇ .
  • the backup surface 66 is in the assembled state in abutment with the housing-side holding surface 52.
  • the holding surface 52 is therefore preferably employed by an angle not sketched in the mounting direction, which is equal to the safety angle ⁇ in the opposite direction, ie in the mounting direction 57.
  • the mounting direction 57 is an axial upstream movement.
  • the opposite direction 47 or dismounting direction is thus an axial downstream movement.
  • the spring portion 60 is a longitudinally section in approximately asymmetrical U-shaped profile with a radially inner leg 68, a radially outer leg 70 and a leg 68, 70 interconnecting arc section 72.
  • the inner leg 68 goes with its front end in the mounting portion 62 on which is connected to a large area on the back 34.
  • the inner leg 68 is hired in the mounting direction by an angle of attack ⁇ and merges with its rear end in the arc section 72.
  • the outer leg 70 extends in the mounting direction and connects the arcuate portion 72 with the locking portion 58 located upstream of the arc portion 72.
  • the housing sections 8, 10 are separated from each other.
  • the sealing element 1 is brought in the mounting direction, ie against the flow direction, from back to front by an axial sliding movement into sliding engagement with the front housing section 8.
  • the front retaining element 44 is pushed with its contact surface 48 along the rear platform region 46 of the upstream guide blade row and the rear retaining element 16 is pushed with its contact surface 42 along the axial projection 14.
  • the fuse 50 runs with its mounting surface 64 on the axial projection 14.
  • the fuse 50 Due to the spring action of the spring portion 60, the fuse 50 is elastically compressed from its original shape and / or elastically twisted about the transition region 74 between the inner leg 68 and the attachment portion 62 and the latch portion 58 is moved along the inner peripheral surface 54 of the front housing portion 8, until it returns to its original shape after passing the inner peripheral surface 58 and is in abutment with the support surface 52 with its mounting surface 64.
  • the holding elements 16, 44 are in sliding engagement with the receptacles 14, 46 and the fuse 50 lies with its locking surface 66 flat against the support surface 52.
  • the sealing element 1 is thus secured in the desired position against falling out. Due to the small mounting angle ⁇ only a small axial mounting force is necessary for installation. Due to the large safety angle ⁇ , however, a large axial holding force is achieved, so that on the one hand a reliable self-locking is achieved.
  • the employment of the inner leg 68 reinforces the respective effect. That is, the mounting angle ⁇ is further reduced by the employment of the inner leg 68 during insertion.
  • the front housing section 8 can now be transported, for example, without the risk that the sealing element 1 leaves its desired position on the front housing section 8.
  • the rear housing section 8 thus does not have to be screwed to the front housing section 8 immediately after assembly of the sealing element 1 or the sealing device in order to prevent a change in position of the sealing element 1.
  • the mounting angle ⁇ is at least 10 °, more preferably 20 ° to 30 °, smaller than a minimum securing angle.
  • the minimum securing angle is the smallest possible securing angle ⁇ and substantially dependent on the coefficient of friction between the holding surface 52 and the securing surface 66.
  • FIG. 2 a second embodiment of a sealing element 1 according to the invention is shown in section along a machine longitudinal axis of a turbomachine.
  • the spring portion 60 of the fuse 50 In contrast to the first embodiment according to FIG. 1 is the spring portion 60 of the fuse 50 at its according to the view in FIG. 2 Vertical axis arranged rotated 180 ° and positioned upstream of the latching portion 58.
  • the spring portion 60 is arranged almost inverted.
  • the arcuate portion 72 is disposed upstream of the radially inner leg 68 and upstream of the radially outer leg 70.
  • the orientation of the locking portion 58 has not changed, so that due to the reorientation of the spring portion 60 of the radially outer leg 70 now merges into the mounting surface 64 and not in the locking surface 66 of the locking portion 58.
  • the spring portion 60 is in the mounting direction arranged in the latching portion 58 and in the dismounting direction of the spring portion 60 is disposed behind the latching portion 58. Due to the changed orientation of the spring portion 60, a position of the pitch angle ⁇ of the inner leg 68 has also changed.
  • the latching portion 58 downstream transitions into an axially extending rear free end portion 76 which is radially spaced in the mounted state of the sealing element 1 from the opposite radially inner peripheral surface 54 of the front housing portion 8.
  • the radial spacing creates a receiving space 78 for, for example, a disassembling tool, by means of which, in cooperation with the free end section 76, a compression force directed radially inwardly from the outside toward the lock 50 is introduced.
  • a tool such as a screwdriver, is inserted into the receiving space 78.
  • the tool is brought into abutment with the free end portion 76 and moved radially from outside to inside, whereby the compression force is introduced into the fuse 50, which is such that the spring portion 60 is compressed and thus the coverage of the backup surface 66 with the support surface 52nd the housing portion 8 is reduced, so that the sealing element 1 can be removed simplified in the axial direction.
  • a sealing element for positioning in a turbomachine, wherein for self-assurance of the sealing element in a mounting position whose support structure has a fuse which has a resilient latching portion whose mounting surface is employed at a smaller angle in the mounting direction as a backup surface in the opposite direction, a sealing device, as well a turbomachine.

Abstract

Offenbart ist ein Dichtelement (1) zur Positionierung in einer Strömungsmaschine, wobei zur Selbstsicherung des Dichtelementes in einer Montageposition deren Tragstruktur eine Sicherung (50) aufweist, die einen federnden Rastabschnitt (58) hat, dessen Montagefläche (64) in einem kleineren Winkel in Montagerichtung angestellt ist als eine Sicherungsfläche (66) in Gegenrichtung, eine Dichteinrichtung, sowie eine Strömungsmaschine.Disclosed is a sealing element (1) for positioning in a turbomachine, wherein for self-assurance of the sealing element in a mounting position whose support structure has a fuse (50) having a resilient latching portion (58) whose mounting surface (64) at a smaller angle in the mounting direction is employed as a backup surface (66) in the opposite direction, a sealing device, and a turbomachine.

Description

Die Erfindung betrifft ein Dichtelement einer Strömungsmaschine nach dem Oberbegriff des Patentanspruchs 1, eine Dichteinrichtung mit zumindest einem Dichtelement und eine Strömungsmaschine mit einer derartigen Dichteinrichtung.The invention relates to a sealing element of a turbomachine according to the preamble of patent claim 1, a sealing device with at least one sealing element and a turbomachine with such a sealing device.

In Strömungsmaschinen wie Gasturbinen und Flugtriebwerken werden turbinenseitig Radialspalte zwischen rotorseitigen Laufschaufelreihen und die Laufschaufelreihen umgebenden Gehäusebereichen regelmäßig mittels einer Dichteinrichtung abgedichtet bzw. verringert. Die Dichteinrichtung setzt sich aus einer Vielzahl von Dichtelementen bzw. Ringsegmenten zusammen, die jeweils zumindest einen Einlauf- bzw. Anstreifbelag aufweisen, der an einer mit dem Gehäusebereich im Wirkeingriff stehenden Tragstruktur befestigt ist. Bekannte Tragstrukturen haben zumindest ein formstabiles Halteelement, das im montierten Zustand der Strömungsmaschine zwischen zwei axial miteinander verschraubten Abschnitten des Gehäusebereiches angeordnet ist. Zum Sichern der Dichteinrichtung bzw. dessen Dichtelements während der Montage oder während des Transportes der noch nicht fertiggestellten Strömungsmaschine, also bei nicht verschraubten Gehäuseabschnitten, können die Tragstrukturen jeweils eine Sicherung aufweisen, die auch als Montage- oder als Lagesicherung bezeichnet werden kann.In turbomachines such as gas turbines and aircraft engines, radial gaps between rotor-side blade rows and the blade rows surrounding housing regions are regularly sealed or reduced by means of a sealing device on the turbine side. The sealing device is composed of a plurality of sealing elements or ring segments, each having at least one inlet or Anstreifbelag which is attached to a stationary with the housing portion in operative engagement support structure. Known support structures have at least one dimensionally stable holding element, which is arranged in the mounted state of the turbomachine between two axially screwed together sections of the housing portion. To secure the sealing device or its sealing element during assembly or during transport of the unfinished turbomachine, that is, when not screwed housing sections, the support structures may each have a backup, which may also be referred to as mounting or securing position.

Bei einer bekannten Tragstruktur sind in Montagerichtung betrachtet eine Sicherung und zumindest ein Halteelement hintereinander angeordnet, wobei die Sicherung einen Rastabschnitt mit einer um einen Montagewinkel in Montagerichtung angestellten Montagefläche und einer um einen Sicherungswinkel in Gegenrichtung angestellter Sicherungsfläche hat. Zur elastischen Ausbildung des Rastabschnittes ist dieser über einen Federabschnitt an der Rückseite angebunden. Der Sicherungswinkel ist derart gewählt, dass eine hohe Haltekraft erreicht wird. Der Montagewinkel ist entsprechend dem Sicherungswinkel eingestellt, so dass zur Montage der Tragstruktur eine entsprechend große Montagekraft aufgebracht werden muss, die zu einer plastischen Verformung bzw. Deformation der Sicherung führen kann.In a known support structure viewed in the mounting direction, a fuse and at least one holding element are arranged one behind the other, wherein the fuse has a latching portion with an assembly angle in the mounting direction employed mounting surface and an employee employed in the opposite direction by a safety angle backup surface. For elastic training of the locking portion of this is connected via a spring portion on the back. The safety angle is chosen such that a high holding force is achieved. The mounting bracket is adjusted according to the safety angle, so that for mounting the support structure a correspondingly large mounting force must be applied, which can lead to a plastic deformation or deformation of the fuse.

Aufgabe der Erfindung ist es, ein Dichtelement einer Strömungsmaschine zu schaffen, das die vorgenannten Nachteile beseitigt und insbesondere eine leichte Montage und eine zuverlässige Lagesicherung während der Montage ermöglicht. Des Weiteren ist es Aufgabe der Erfindung, eine Dichteinrichtung zu schaffen, die in einer Strömungsmaschine einfach zu montieren und demontieren ist, sowie eine Strömungsmaschine zu schaffen, deren zumindest eine Dichteinrichtung während der Montage oder des Transportes sicher an einem Gehäuseabschnitt gehalten ist.The object of the invention is to provide a sealing element of a turbomachine, which eliminates the aforementioned disadvantages and in particular allows easy installation and a reliable position assurance during assembly. Furthermore, it is an object of the invention to provide a sealing device which is easy to assemble and disassemble in a turbomachine, and to provide a turbomachine whose at least one sealing device is held securely on a housing section during assembly or transport.

Diese Aufgabe wird gelöst durch ein Dichtelement mit den Merkmalen des Patentanspruchs 1, durch eine Dichteinrichtung mit den Merkmalen des Patentanspruchs 9 und durch eine Strömungsmaschine mit den Merkmalen des Patenanspruchs 10.This object is achieved by a sealing element having the features of patent claim 1, by a sealing device having the features of patent claim 9 and by a turbomachine having the features of patent claim 10.

Ein erfindungsgemäßes Dichtelement einer Strömungsmaschine zum Einstellen eines Radialspaltes zwischen einer Laufschaufelreihe und einem Gehäusebereich hat eine Tragstruktur mit einer Vorderseite, an der ein Einlaufbelage befestigt ist, und eine Rückseite, an der zumindest ein formstabiles Halteelement zum Halten der Tragstruktur in einer Soll-Position an dem Gehäusebereich angeordnet ist. Zudem hat die Tragstruktur eine Sicherung zum Sichern der Tragstruktur in ihrer Soll-Position während der Montage oder des Transportes. Das zumindest eine Halteelement und die Sicherung sind in Montagerichtung hintereinander angeordnet, wobei die Sicherung einen Rastabschnitt mit einer um einen Montagewinkel in Montagerichtung angestellter Montagefläche und einer um einen Sicherungswinkel in Gegenrichtung angestellter Sicherungsfläche aufweist. Der Rastabschnitt ist ferner über einen Federabschnitt elastisch an der Rückseite gelagert. Erfindungsgemäß ist der Montagewinkel kleiner als der Sicherungswinkel.An inventive sealing element of a turbomachine for adjusting a radial gap between a blade row and a housing portion has a support structure with a front side, to which an inlet lining is attached, and a back, on which at least one dimensionally stable holding element for holding the support structure in a desired position on the Housing area is arranged. In addition, the support structure has a fuse for securing the support structure in its desired position during assembly or transport. The at least one retaining element and the fuse are arranged one behind the other in the mounting direction, wherein the fuse has a latching section with a mounting surface engaged by a mounting bracket in the mounting direction and a backup surface engaged by a safety angle in the opposite direction. The latching section is also mounted elastically on the rear side via a spring section. According to the invention, the mounting angle is smaller than the safety angle.

Dadurch, dass der Montagewinkel kleiner als der Sicherungswinkel ist kann zum einen eine einfache Montage und zum anderen eine hohe Sicherungswirkung und somit eine zuverlässige Lagesicherung während der Montage erzielt werden. Der Montagewinkel und der Sicherungswinkel sind unabhängig voneinander und hierdurch an ihre jeweilige Funktion - geringe Montagekraft bzw. hohe Haltekraft - optimal anpassbar. Eine Beschädigung der Tragstruktur aufgrund eines zu großen Montagewinkels ist ausgeschlossen.The fact that the mounting angle is smaller than the safety angle can be achieved on the one hand a simple installation and on the other a high securing effect and thus a reliable position assurance during assembly. The mounting angle and the safety angle are independent of each other and thus to their respective function - low assembly force or high holding force - optimally adaptable. Damage to the support structure due to an excessive mounting angle is excluded.

Die Montage des Dichtelements an dem Gehäusebereich lässt sich besonders leicht gestalten, wenn das zumindest eine Halteelement einen sich in Montagerichtung erstreckenden Halteabschnitt zum Bilden eines Schiebeeingriffs mit einer korrespondierenden Aufnahme der Strömungsmaschine hat. Hierdurch kann die Tragstruktur durch eine lineare Bewegung in ihre Soll-Position überführt werden. Der Federabschnitt ermöglicht dabei eine automatische Auslenkung des Rastabschnittes in eine zweite Richtung und somit eine automatische Verrastung.The mounting of the sealing element on the housing region can be made particularly easily if the at least one retaining element has a holding section extending in the mounting direction for forming a sliding engagement with a corresponding receptacle of the turbomachine. As a result, the support structure can be transferred by a linear movement in its desired position. The spring section allows an automatic deflection of the locking portion in a second direction and thus an automatic locking.

Zur Halterung des Dichtelements an mehreren Punkten kann ein weiteres Halteelement vorgesehen sein, wobei der Rastabschnitt vorzugsweise dann zwischen den Halteelementen angeordnet ist, wobei das weitere Halteelement einen Schiebeeingriff in Montagerichtung mit einer korrespondierenden Aufnahme der Strömungsmaschine bilden kann. Durch den Schiebereingriff des zweiten Halteelements in Montagerichtung werden beide Halteelemente gleichzeitig durch eine lineare Bewegung in Wirkeingriff mit der jeweiligen Gehäuseaufnahme gebracht.For holding the sealing element at several points, a further holding element may be provided, wherein the locking portion is preferably then arranged between the holding elements, wherein the further holding element can form a sliding engagement in the mounting direction with a corresponding receptacle of the turbomachine. Due to the sliding engagement of the second holding element in the mounting direction, both holding elements are simultaneously brought into operative engagement with the respective housing receptacle by a linear movement.

Bevorzugterweise ist der Federabschnitt ein Profil mit zwei übereinander angeordneten Schenkeln, dessen bezogen auf eine Maschinenlängsachse der Strömungsmaschine, äußerer bzw. radial äußerer Schenkel in den Rastabschnitt übergeht und dessen innerer bzw. radial innerer Schenkel in einen an der Rückseite angebundenen Befestigungsabschnitt übergeht. Ein derartiger Federabschnitt ermöglicht eine große Auslenkung bzw. Elastizität des Rastabschnittes und ist einfach herzustellen. Beispielhafte Profile mit zwei Schenkeln sind U-Profile, V-Profile und W-Profile.Preferably, the spring portion is a profile with two legs arranged one above the other, with respect to a machine longitudinal axis of the turbomachine, outer or radially outer leg merges into the latching portion and the inner or radially inner leg merges into a fastened to the rear mounting portion. Such a spring portion allows a large deflection or elasticity of the locking portion and is easy to manufacture. Exemplary profiles with two legs are U-profiles, V-profiles and W-profiles.

Zur Vergrößerung der Federwirkung kann der innere Schenkel um einen Anstellwinkel in Montagerichtung angestellt sein. Die Anstellung bewirkt eine Veränderung des Montagewinkels beim Montieren und des Sicherungswinkels bei einer Belastung in Demontagerichtung. Durch diese Anstellung kann die Montagekraft weiter reduziert werden.To increase the spring action of the inner leg may be employed by an angle in the mounting direction. The employment causes a change in the mounting bracket during mounting and the safety angle at a load in demounting direction. By this employment, the mounting force can be further reduced.

Der äußere Schenkel erstreckt sich vorzugsweise in Montagerichtung und ist somit in Montagerichtung nicht angestellt. Hierdurch sind die beiden Schenkel ähnlich einem asymmetrischen U-Profil zueinander angestellt, was sich positiv auf die Reduzierung der Montagekraft bzw. Steigerung der Haltekraft auswirkt.The outer leg preferably extends in the mounting direction and is thus not employed in the mounting direction. As a result, the two legs are similar to one asymmetric U-profile to each other employed, which has a positive effect on the reduction of the mounting force and increase the holding force.

Bevorzugterweise ist der Montagewinkel um wenigstens 10° kleiner, vorzugsweise um 20° bis 30°, kleiner als ein Mindestsicherungswinkel. Der Mindestsicherungswinkel ist der kleinstmögliche Sicherungswinkel und wesentlich vom Reibkoeffizienten zwischen dem Gehäuseabschnitt und der Sicherungsfläche abhängig. Durch einen derart reduzierten Montagewinkel erfolgt eine Montage mit einer besonders geringen Montagekraft.Preferably, the mounting angle is smaller by at least 10 °, preferably by 20 ° to 30 °, smaller than a minimum securing angle. The minimum securing angle is the smallest possible safety angle and depends essentially on the coefficient of friction between the housing section and the securing surface. By such a reduced mounting bracket is a mounting with a very low installation force.

Eine Demontage des Dichtelements lässt sich vereinfachen, wenn in Montagrichtung der Federabschnitt vor dem Rastabschnitt angeordnet ist und der Rastabschnitt in Montagrichtung in einen hinteren freien Endabschnitt übergeht. Der freie Endabschnitt ist in Demontagerichtung vorne angeordnet und somit bei einer Demontage frei zugänglich. Hierdurch kann beispielsweise mit einem Werkzeug eine radial von außen nach innen gerichtete Stauchkraft in den Federabschnitt eingeleitet werden und eine radiale Überdeckung der sicherungselementenseitigen Sicherungsfläche mit der gehäuseseitigen Haltefläche reduziert werden.A disassembly of the sealing element can be simplified if the spring section is arranged in front of the latching section in the mounting direction and the latching section merges in the mounting direction in a rear free end portion. The free end portion is arranged in the front dismounting direction and thus freely accessible during disassembly. In this way, for example, with a tool a radially outwardly inwardly directed compression force can be introduced into the spring portion and a radial overlap of the fuse element side backup surface can be reduced with the housing-side support surface.

Eine erfindungsgemäße Dichteinrichtung einer Strömungsmaschine hat eine Vielzahl von erfindungsgemäßen Dichtelementen. Eine derartige Dichteinrichtung lässt sich beschädigungsfrei montieren und ist während der Montage zuverlässig in ihrer Soll-Position gesichert.A sealing device according to the invention of a turbomachine has a plurality of sealing elements according to the invention. Such a sealing device can be mounted without damage and is reliably secured during assembly in its desired position.

Eine erfindungsgemäße Strömungsmaschine hat zumindest eine erfindungsgemäße Dichteinrichtung. Die Strömungsmaschine zeichnet sich durch einen optimalen Radialspalt im Bereich der Dichteinrichtung aus, da diese ohne Beschädigungen und zudem in ihrer Soll-Position montiert wird.A turbomachine according to the invention has at least one sealing device according to the invention. The turbomachine is characterized by an optimal radial gap in the area of the sealing device, since it is mounted without damage and also in its desired position.

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

Im Folgenden werden bevorzugte Ausführungsbeispiele der Erfindung anhand von stark vereinfachten schematischen Darstellung näher erläutert. Es zeigen:

Figur 1
einen Axialschnitt durch ein erstes Ausführungsbeispiel eines erfindungsgemäßen Dichteelements, das an einem Gehäusebereich einer Strömungsmaschine angeordnet ist, und
Figur 2
einen Axialschnitt durch ein zweites Ausführungsbeispiel eines erfindungsgemäßen Dichteelements, das an einem Gehäusebereich einer Strömungsmaschine angeordnet ist.
In the following preferred embodiments of the invention will be explained in more detail with reference to a greatly simplified schematic representation. Show it:
FIG. 1
an axial section through a first embodiment of a sealing element according to the invention, which is arranged on a housing portion of a turbomachine, and
FIG. 2
an axial section through a second embodiment of a sealing element according to the invention, which is arranged on a housing portion of a turbomachine.

In Figur 1 ist ein erstes Ausführungsbeispiel eines erfindungsgemäßen Dichtelements 1 im Schnitt entlang einer Maschinenlängsachse einer Strömungsmaschine gezeigt. Die Maschinenlängsachse erstreckt sich in Axialrichtung. Richtungsangaben wie axial oder radial beziehen sich auf die Maschinenlängsachse. Richtungsangaben wie stromaufwärts und stromabwärts oder Ortsangaben wie vorne und hinten, beziehen sich auf die Strömungsrichtung eines die Strömungsmaschine durchströmenden Heißgases. Wenn sich Richtungsangaben und/oder Ortsangaben auf eine Montagerichtung oder Demontagerichtung beziehen, wird dies ausdrücklich erwähnt.In FIG. 1 a first embodiment of a sealing element 1 according to the invention is shown in section along a machine longitudinal axis of a turbomachine. The machine longitudinal axis extends in the axial direction. Directional data such as axial or radial refer to the machine longitudinal axis. Directional information such as upstream and downstream or location information such as front and rear, refer to the flow direction of a hot gas flowing through the turbomachine. If directional information and / or location information refer to a mounting direction or disassembly direction, this is explicitly mentioned.

Die Strömungsmaschine ist beispielsweise eine Gasturbine und insbesondere ein Flugtriebwerk. Das Dichtelement 1 ist ein Ringsegment einer Dichteinrichtung, das hier in einem turbinenseitigen Gehäusebereich 2 der Strömungsmaschine angeordnet ist. Grundsätzlich kann das Dichtelement 1 auch verdichterseitig angeordnet sein. Das Dichtelement 1 bzw. die aus zumindest einem Dichtelement bestehende Dichteinrichtung dient zum Einstellen und insbesondere Reduzieren eines Radialspaltes zwischen dem Gehäusebereich 2 und einer von dem Gehäusebereich 2 umgriffenen Laufschaufelreihe 4. Die Laufschaufelreihe 4 ist in einem Ringraum 6 um die Maschinenlängsachse rotierend angeordnet. Der Ringraum 6 wird vom Heißgas im Wesentlichen in Richtung der Maschinenlängsachse und hier axial von links nach rechts durchströmt.The turbomachine is, for example, a gas turbine and in particular an aircraft engine. The sealing element 1 is a ring segment of a sealing device, which is arranged here in a turbine-side housing portion 2 of the turbomachine. In principle, the sealing element 1 can also be arranged on the compressor side. The sealing element 1 or the sealing device consisting of at least one sealing element serves for adjusting and in particular reducing a radial gap between the housing region 2 and a blade row 4 encompassed by the housing region 2. The blade row 4 is arranged to rotate about the machine longitudinal axis in an annular space 6. The annular space 6 is flowed through by the hot gas substantially in the direction of the machine longitudinal axis and here axially from left to right.

Der Gehäusebereich 2 setzt sich hier aus zwei Gehäuseabschnitten 8, 10 mit Ringflanschen zusammen, die wie durch die strichpunktierte Linie 12 angedeutet im Bereich Ihrer Ringflansche miteinander verschraubt sind. Die Gehäuseabschnitte 8, 10 selbst können sich in eine untere Hälfte und in eine obere Hälfte unterteilen, die in einer Horizontalebene gefügt sind bzw. werden.The housing portion 2 is here composed of two housing sections 8, 10 with annular flanges, which are screwed together as indicated by the dot-dash line 12 in the region of their annular flanges. The housing sections 8, 10 themselves can be subdivided into a lower half and an upper half, which are or are joined in a horizontal plane.

Der vordere Gehäuseabschnitt 8 hat eine Aufnahme 14 zum Zusammenwirken mit einem hinteren formstabilen Halteelement 16 des Dichtelements 1. Die Aufnahme 14 ist hierzu als ein sich in Strömungsrichtung erstreckender Axialvorsprung mit einer radialen Anlagefläche 17 ausgebildet.The front housing section 8 has a receptacle 14 for interacting with a rear dimensionally stable holding element 16 of the sealing element 1. The receptacle 14 is designed for this purpose as an axial projection extending in the flow direction with a radial contact surface 17.

Der hintere Gehäuseabschnitt 10 hat eine sich von dem Ringflansch stromabwärts erstreckende axiale Umfangswandung 18 und eine sich von der Umfangswandung 18 stromabwärts des Ringflansches radial nach innen erstreckende Ringwandung 20. Die Umfangswandung 18 hat eine derartige Länge bzw. axiale Erstreckung, dass im montierten Zustand des Dichtelementes 1 bzw. der Dichteinrichtung zwischen dem hinteren Halteelement 16 und der Ringwandung 20 ein Axialspalt gebildet ist. Die Ringwandung 20 hat hier eine derartige radiale Erstreckung bzw. Höhe, dass sie sich leicht radial nach innen über die Aufnahme 14 hinaus erstreckt.The rear housing section 10 has an axial circumferential wall 18 extending downstream from the annular flange and a radially inwardly extending annular wall 20 from the circumferential wall 18 downstream of the annular flange. The peripheral wall 18 has such a length or axial extent that in the assembled state of the sealing element 1 or the sealing device between the rear retaining element 16 and the annular wall 20, an axial gap is formed. The annular wall 20 here has such a radial extent or height that it extends slightly radially inwardly beyond the receptacle 14 addition.

Das Dichtelement 1 hat einen Einlauf- bzw. Anstreifbelag 21, der gegenüberliegend von in Strömungsrichtung hintereinander angeordneten umfangsseitigen Dichtstegen 22, 24 der Laufschaufelreihe 4 angeordnet ist. Zum Haltern des Einlaufbelags 21 hat das Dichtelement 1 eine Tragstruktur 26. Die Tragstruktur 26 und der Einlaufbelag 21 sind metallisch. In dem hier gezeigten Ausführungsbeispiel werden der Einlaufbelag 21 und die Tragstruktur 26 getrennt voneinander hergestellt und nachträglich gefügt. Der Einlaufbelag 21 kann jedoch auch integral mit der Tragstruktur 26 gefertigt werden. Dies kann beispielweise mittels eines generativen Fertigungsverfahrens wie Lasersintern bzw. eines Laserschmelzverfahrens erfolgen und ermöglicht die Herstellung des Dichtelements 1 als einen geschlossener Ring und somit als eine einstückige Dichteinrichtung.The sealing element 1 has an inlet or Anstreifbelag 21, which is arranged opposite to each other in the flow direction arranged circumferentially sealing webs 22, 24 of the blade row 4. For holding the inlet lining 21, the sealing element 1 has a supporting structure 26. The supporting structure 26 and the inlet lining 21 are metallic. In the embodiment shown here, the inlet lining 21 and the support structure 26 are manufactured separately from each other and added later. However, the inlet lining 21 can also be manufactured integrally with the supporting structure 26. This can be done, for example, by means of a generative manufacturing process such as laser sintering or a laser melting process and enables the production of the sealing element 1 as a closed ring and thus as a one-piece sealing device.

Die Tragstruktur 26 hat einen axialen Grundabschnitt 28 und einen in Radialrichtung angestellten Wandungabschnitt 30, der stromaufwärts des Grundabschnittes 28 angeordnet ist. Der Grundabschnitt 28 hat eine heißgasseitige bzw. ringraumseitige Vorderseite 32, an dem der Einlaufbelag 21 angeordnet ist, und eine entgegengesetzte kühlluftseitige bzw. dem Gehäusebereich 2 zugewandte Rückseite 34. Die Rückseite 34 ist mit dem hinteren Halteelement 16 versehen, das mit der gehäuseseitigen Aufnahme 14 zusammenwirkt.The support structure 26 has an axial base portion 28 and a radially disposed wall portion 30 disposed upstream of the base portion 28. The base section 28 has a hot gas side or annular space-side front side 32, on which the inlet lining 21 is arranged, and an opposite cooling air side or the housing region 2 facing back 34. The back 34 is provided with the rear support member 16, which is connected to the housing-side receptacle 14th interacts.

Das hintere Halteelement 16 ist hier S-förmig ausgebildet mit einem an der Rückseite 34 angebundenen axialen Fußabschnitt 36, einem sich von dem Fußabschnitt 36 radial nach außen erstreckenden Steg 38 und einem sich von dem Steg 38 stromaufwärts erstreckenden axialen Kopf- bzw. Halteabschnitt 40. Der Halteabschnitt 40 hat insbesondere eine sich stromaufwärts erstreckende in Richtung des Ringraums 6 weisende Kontaktfläche 42 zum Zusammenwirken mit der Anlagefläche 17 der Aufnahme 14.The rear support member 16 is here S-shaped with an attached at the back 34 axial leg portion 36, a radially extending from the foot portion 36 radially outwardly web 38 and an upstream of the web 38 extending axial head or holding portion 40th The holding section 40 has in particular an upstream extending in the direction of the annular space 6 facing contact surface 42 for cooperation with the contact surface 17 of the receptacle 14th

Zudem hat die Tragstruktur 26 bei diesem Ausführungsbeispiel ein vorderes formstabiles Haltelement 44, das sich stromaufwärts des Wandungsabschnitts 30 axial erstreckt und mit einer korrespondierenden statorseitigen Aufnahme 46 zusammenwirkt. Das vordere Halteelement 44 hat eine sich in Axialrichtung erstreckende vorderseitige radiale Kontaktfläche 48, die mit einer sich in Axialrichtung erstreckenden Anlagefläche 49 der Aufnahme 46 zusammenwirkt. Die statorseitige Aufnahme 46 ist beispielsweise ein hinterer Plattformbereich einer stromaufwärtigen Leitschaufelreihe.In addition, the support structure 26 in this embodiment, a front dimensionally stable support member 44 which extends axially upstream of the Wandungsabschnitts 30 and cooperates with a corresponding stator-side receptacle 46. The front retaining element 44 has an axially extending front-side radial contact surface 48 which cooperates with an axially extending abutment surface 49 of the receptacle 46. The stator-side receptacle 46 is, for example, a rear platform region of an upstream row of guide vanes.

Zum Sichern des Dichtelements 1 in seiner Soll-Position während der Montage oder während des Transports, bei dem die Gehäuseabschnitte 8, 10 voneinander getrennt sind, hat die Tragstruktur 26 eine Sicherung 50. Dies bedeutet, dass sich das Dichtelement 1 bzw. die Dichteinrichtung mit ihren Halteelementen 16, 44 im Schiebeeingriff mit den Aufnahmen 14, 46 befindet, die Schiebeingriffe durch eine ausreichend kräftige Demontagebewegung in Gegenrichtung 47 jedoch gelöst werden können. Eine Selbstlösung des Dichtelements 1 von dem vorderen Gehäuseabschnitt 8 wird jedoch aufgrund der Sicherung 50 verhindert. Konkret heißt das bei diesem Ausführungsbeispiel, dass das Dichtelement 1 bzw. die Dichteinrichtung an dem vorderen Gehäuseabschnitt 8 in seiner bzw. ihrer Soll-Position auch dann gesichert ist, wenn der hintere Gehäuseabschnitt 10 noch nicht mit dem vorderen Gehäuseabschnitt 8 verschraubt ist. Die Sicherung 50 erstreckt sich von der Rückseite 34 zwischen den Halteelementen 16, 44 und wirkt mit einer gehäuseseitigen Haltefläche 52 zusammen. Die Haltefläche 52 ist eine Schrägfläche, die entgegengesetzt zur Aufnahme des hinteren Halteelements 16 an dem vorderen Gehäuseabschnitt 8 angeordnet ist und sich zwischen einer radial inneren Umfangsfläche 54 und einer stromaufwärtigen radial äußeren Umfangsfläche 56 des vorderen Gehäuseabschnitts 8 erstreckt. Sie erstreckt sich somit schräg in Montagerichtung 57.To secure the sealing element 1 in its desired position during assembly or during transport, in which the housing sections 8, 10 are separated from each other, the support structure 26 has a fuse 50. This means that the sealing element 1 or the sealing device with its retaining elements 16, 44 in sliding engagement with the receptacles 14, 46, the sliding engagements can be solved by a sufficiently strong disassembly movement in the opposite direction 47, however. However, a self-release of the sealing member 1 from the front housing portion 8 is prevented due to the fuse 50. Specifically, in this embodiment, this means that the sealing element 1 or the sealing device is secured to the front housing section 8 in its desired position even when the rear housing section 10 is not yet bolted to the front housing section 8. The fuse 50 extends from the rear side 34 between the holding elements 16, 44 and cooperates with a housing-side holding surface 52. The holding surface 52 is an inclined surface that is disposed opposite to receiving the rear holding member 16 on the front housing portion 8 and extending between a radially inner peripheral surface 54 and an upstream radially outer circumferential surface 56 of the front housing portion 8. It thus extends obliquely in the mounting direction 57.

Die Sicherung 50 hat einen Rastabschnitt 58, der über einen Federabschnitt 60 und einen Befestigungsabschnitt 62 an der Rückseite 34 angebunden ist.The fuse 50 has a latching portion 58 which is connected via a spring portion 60 and a mounting portion 62 on the back 34.

Der Rastabschnitt 58 hat eine in Montagerichtung um einen Montagewinkel α angestellte Montagefläche 64 und eine in Gegenrichtung um einen Sicherungswinkel β angestellte Sicherungsfläche 66. Zur Montage des Dichtelements 1 mit einer kleinen Montagekraft und gleichzeitig zur zuverlässigen Sicherung ist der Montagewinkel α kleiner als der Sicherungswinkel β bzw. der Sicherungswinkel β ist größer als der Montagewinkel α. Die Sicherungsfläche 66 befindet sich im montierten Zustand in Anlage mit der gehäuseseitigen Haltefläche 52. Zur großflächigen Anlage ist die Haltefläche 52 daher bevorzugterweise um einen nicht skizzierten Winkel in Montagerichtung angestellt, der gleich dem Sicherungswinkel β in Gegenrichtung, also in Montagrichtung 57, ist. Die Montagerichtung 57 ist eine axiale stromaufwärtige Bewegung. Die Gegenrichtung 47 bzw. Demontagerichtung ist somit eine axiale stromabwärtige Bewegung.For mounting the sealing element 1 with a small mounting force and at the same time for reliable securing, the mounting angle .alpha. Is smaller than the securing angle .beta. Or .beta the securing angle β is greater than the mounting angle α. The backup surface 66 is in the assembled state in abutment with the housing-side holding surface 52. For large-scale investment, the holding surface 52 is therefore preferably employed by an angle not sketched in the mounting direction, which is equal to the safety angle β in the opposite direction, ie in the mounting direction 57. The mounting direction 57 is an axial upstream movement. The opposite direction 47 or dismounting direction is thus an axial downstream movement.

Der Federabschnitt 60 ist ein im Längsschnitt in etwa asymmetrisches U-förmiges Profil mit einem radial inneren Schenkel 68, einem radial äußeren Schenkel 70 und einem die Schenkel 68, 70 miteinander verbindenden Bogenabschnitt 72. Der innere Schenkel 68 geht mit seinem vorderen Ende in den Befestigungsabschnitt 62 über, der großflächig an der Rückseite 34 angebunden ist. Der innere Schenkel 68 ist um einen Anstellwinkel γ in Montagerichtung angestellt und geht mit seinem hinteren Ende in den Bogenabschnitt 72 über. Der äußere Schenkel 70 erstreckt sich in Montagerichtung und verbindet den Bogenabschnitt 72 mit dem zum Bogenabschnitt 72 stromaufwärts gelegenen Rastabschnitt 58.The spring portion 60 is a longitudinally section in approximately asymmetrical U-shaped profile with a radially inner leg 68, a radially outer leg 70 and a leg 68, 70 interconnecting arc section 72. The inner leg 68 goes with its front end in the mounting portion 62 on which is connected to a large area on the back 34. The inner leg 68 is hired in the mounting direction by an angle of attack γ and merges with its rear end in the arc section 72. The outer leg 70 extends in the mounting direction and connects the arcuate portion 72 with the locking portion 58 located upstream of the arc portion 72.

Zur Montage des Dichtelements 1 sind die Gehäuseabschnitte 8, 10 getrennt voneinander. Das Dichtelement 1 wird in Montagerichtung, also gegen die Strömungsrichtung, von hinten nach vorne durch eine axiale Schiebebewegung in Schiebeeingriff mit dem vorderen Gehäuseabschnitt 8 gebracht. Dabei wird das vordere Halteelement 44 mit seiner Kontaktfläche 48 entlang dem hinteren Plattformbereich 46 der stromaufwärtigen Leitschaufelreihe und das hintere Haltelement 16 wird mit seiner Kontaktfläche 42 entlang dem Axialvorsprung 14 geschoben. Beim Einschieben läuft die Sicherung 50 mit ihrer Montagefläche 64 auf den Axialvorsprung 14 auf. Aufgrund der Federwirkung des Federabschnitts 60 wird die Sicherung 50 aus ihrer ursprünglichen Form elastisch gestaucht und/oder leicht um den Übergangsbereich 74 zwischen dem inneren Schenkel 68 und dem Befestigungsabschnitt 62 elastisch verdreht und der Rastabschnitt 58 entlang der inneren Umfangsfläche 54 des vorderen Gehäuseabschnitt 8 bewegt, bis sie nach dem Passieren der inneren Umfangsfläche 58 ihre ursprüngliche Form wieder annimmt und sich mit ihrer Montagefläche 64 in Anlage mit der Haltefläche 52 befindet.For mounting the sealing element 1, the housing sections 8, 10 are separated from each other. The sealing element 1 is brought in the mounting direction, ie against the flow direction, from back to front by an axial sliding movement into sliding engagement with the front housing section 8. In this case, the front retaining element 44 is pushed with its contact surface 48 along the rear platform region 46 of the upstream guide blade row and the rear retaining element 16 is pushed with its contact surface 42 along the axial projection 14. When inserting the fuse 50 runs with its mounting surface 64 on the axial projection 14. Due to the spring action of the spring portion 60, the fuse 50 is elastically compressed from its original shape and / or elastically twisted about the transition region 74 between the inner leg 68 and the attachment portion 62 and the latch portion 58 is moved along the inner peripheral surface 54 of the front housing portion 8, until it returns to its original shape after passing the inner peripheral surface 58 and is in abutment with the support surface 52 with its mounting surface 64.

Im montierten Zustand befinden sich die Halteelemente 16, 44 im Schiebeeingriff mit den Aufnahmen 14, 46 und die Sicherung 50 liegt mit ihrer Sicherungsfläche 66 flächig an der Haltefläche 52 an. Das Dichtelement 1 ist somit in der Soll-Position gegen Herausfallen gesichert. Aufgrund des kleinen Montagewinkel α ist zur Montage nur eine kleine axiale Montagekraft notwendig. Aufgrund des großen Sicherungswinkels β wird jedoch eine große axiale Haltekraft erzielt, so dass zum einen eine zuverlässige Selbstsicherung erzielt wird. Die Anstellung des inneren Schenkels 68 verstärkt dabei die jeweilige Wirkung. D.h., der Montagewinkel α wird durch die Anstellung des inneren Schenkels 68 beim Einschieben weiter verkleinert. Der vordere Gehäuseabschnitt 8 kann nun beispielsweise transportiert werden, ohne das die Gefahr besteht, dass das Dichtelement 1 seine Soll-Position an dem vorderen Gehäuseabschnitt 8 verlässt. Der hintere Gehäuseabschnitt 8 muss somit nicht unmittelbar nach der Montage des Dichtelements 1 bzw. der Dichteinrichtung mit dem vorderen Gehäuseabschnitt 8 verschraubt werden, um eine Lageänderung des Dichtelements 1 zu verhindern.In the assembled state, the holding elements 16, 44 are in sliding engagement with the receptacles 14, 46 and the fuse 50 lies with its locking surface 66 flat against the support surface 52. The sealing element 1 is thus secured in the desired position against falling out. Due to the small mounting angle α only a small axial mounting force is necessary for installation. Due to the large safety angle β, however, a large axial holding force is achieved, so that on the one hand a reliable self-locking is achieved. The employment of the inner leg 68 reinforces the respective effect. That is, the mounting angle α is further reduced by the employment of the inner leg 68 during insertion. The front housing section 8 can now be transported, for example, without the risk that the sealing element 1 leaves its desired position on the front housing section 8. The rear housing section 8 thus does not have to be screwed to the front housing section 8 immediately after assembly of the sealing element 1 or the sealing device in order to prevent a change in position of the sealing element 1.

Bevorzugterweise ist der Montagewinkel α um wenigstens 10°, stärker bevorzugt um 20° bis 30°, kleiner als ein Mindestsicherungswinkel. Der Mindestsicherungswinkel ist der kleinstmögliche Sicherungswinkel β und wesentlich vom Reibkoeffizienten zwischen der Haltefläche 52 und der Sicherungsfläche 66 abhängig.Preferably, the mounting angle α is at least 10 °, more preferably 20 ° to 30 °, smaller than a minimum securing angle. The minimum securing angle is the smallest possible securing angle β and substantially dependent on the coefficient of friction between the holding surface 52 and the securing surface 66.

Zur Demontage des Dichtelementes 1 bzw. der Dichteinrichtung ist dieses bzw. diese in Gegenrichtung 47 von dem vorderen Gehäuseabschnitt 8 zu trennen, wobei nach Überwinden der Haltekraft die Sicherung 50 elastisch gestaucht bzw. um den Übergangsbereich 74 leicht verdreht wird und erst nach dem Passieren des Axialvorsprungs 14 seine ursprüngliche Form wieder annimmt.To disassemble the sealing element 1 and the sealing device, this or this is to be separated in the opposite direction 47 of the front housing section 8, wherein after overcoming the holding force, the fuse 50 elastically compressed or slightly twisted around the transition region 74 and only after passing the Axial projection 14 resumes its original shape.

In Figur 2 ist ein zweites Ausführungsbeispiel eines erfindungsgemäßen Dichtelements 1 im Schnitt entlang einer Maschinenlängsachse einer Strömungsmaschine gezeigt.In FIG. 2 a second embodiment of a sealing element 1 according to the invention is shown in section along a machine longitudinal axis of a turbomachine.

Im Unterschied zum ersten Ausführungsbeispiel nach Figur 1 ist der Federabschnitt 60 der Sicherung 50 um seine gemäß der Ansicht in Figur 2 Hochachse um 180° gedreht angeordnet und stromaufwärts des Rastabschnitts 58 positioniert. Der Federabschnitt 60 ist quasi umgedreht angeordnet. Hierdurch ist der Bogenabschnitt 72 stromaufwärts des radial inneren Schenkels 68 und stromaufwärts des radial äußeren Schenkels 70 angeordnet ist. Die Orientierung des Rastabschnitts 58 hat sich nicht geändert, so dass aufgrund der Neuorientierung des Federabschnitts 60 der radial äußere Schenkel 70 nun in die Montagefläche 64 übergeht und nicht in die Sicherungsfläche 66 des Rastabschnitts 58. Mit anderen Worten, der Federabschnitt 60 ist in Montagerichtung vor dem Rastabschnitt 58 angeordnet bzw. in Demontagerichtung ist der Federabschnitt 60 hinter dem Rastabschnitt 58 angeordnet. Aufgrund der geänderten Ausrichtung des Federabschnitts 60 hat sich eine Position des Anstellwinkels γ des inneren Schenkels 68 ebenfalls geändert.In contrast to the first embodiment according to FIG. 1 is the spring portion 60 of the fuse 50 at its according to the view in FIG. 2 Vertical axis arranged rotated 180 ° and positioned upstream of the latching portion 58. The spring portion 60 is arranged almost inverted. As a result, the arcuate portion 72 is disposed upstream of the radially inner leg 68 and upstream of the radially outer leg 70. The orientation of the locking portion 58 has not changed, so that due to the reorientation of the spring portion 60 of the radially outer leg 70 now merges into the mounting surface 64 and not in the locking surface 66 of the locking portion 58. In other words, the spring portion 60 is in the mounting direction arranged in the latching portion 58 and in the dismounting direction of the spring portion 60 is disposed behind the latching portion 58. Due to the changed orientation of the spring portion 60, a position of the pitch angle γ of the inner leg 68 has also changed.

Im weiteren Unterschied zum ersten Ausführungsbeispiel nach Figur 1 geht der Rastabschnitt 58 stromabwärts in eine sich in Axialrichtung erstreckenden hinteren freien Endabschnitt 76 über, der im montierten Zustand des Dichtelements 1 radial von der gegenüberliegenden radial inneren Umfangsfläche 54 des vorderen Gehäuseabschnitts 8 beabstandet ist. In Demontagerichtung ist der freie Endabschnitt 76 vor dem Rastabschnitt 58 angeordnet und somit frei zugänglich. Durch die radiale Beabstandung wird ein Aufnahmeraum 78 für beispielsweise ein Demontagewerkzeug geschaffen, mittels dem beim Zusammenwirken mit dem freien Endabschnitt 76 in die Sicherung 50 eine radial von außen nach innen gerichtete Stauchkraft eingeleitet wird. Dies ist beispielsweise dann besonders vorteilhaft, wenn die Sicherung 50 in Umfangsrichtung zwischen zwei Halteelementen 16 angeordnet ist, da dann die "Entriegelung" durch das Einleiten der radialen Stauchkraft vereinfacht wird. Selbstverständlich sind hierzu andere Mechanismen als der freie Endabschnitt 76 in Kombination mit dem Aufnahmeraum 78 vorstellbar.In further difference from the first embodiment according to FIG. 1 the latching portion 58 downstream transitions into an axially extending rear free end portion 76 which is radially spaced in the mounted state of the sealing element 1 from the opposite radially inner peripheral surface 54 of the front housing portion 8. In the dismounting direction of the free end portion 76 is disposed in front of the locking portion 58 and thus freely accessible. The radial spacing creates a receiving space 78 for, for example, a disassembling tool, by means of which, in cooperation with the free end section 76, a compression force directed radially inwardly from the outside toward the lock 50 is introduced. This is for example particularly advantageous when the fuse 50 in Circumferential direction is arranged between two retaining elements 16, since then the "unlocking" is simplified by the introduction of the radial compression force. Of course, other mechanisms than the free end portion 76 in combination with the receiving space 78 are conceivable.

Zur Demontage des Dichtelements 1 wird in den Aufnahmeraum 78 ein Werkzeug, wie zum Beispiel ein Schraubendreher, eingeführt. Das Werkzeug wird in Anlage mit dem freien Endabschnitt 76 gebracht und radial von außen nach innen bewegt, wodurch in die Sicherung 50 die Stauchkraft eingeleitet wird, die derart ist, dass der Federabschnitt 60 gestaucht wird und somit die Überdeckung der Sicherungsfläche 66 mit der Haltefläche 52 des Gehäuseabschnitts 8 reduziert wird, so dass das Dichtelement 1 in axialer Richtung vereinfacht entnommen werden kann.To disassemble the sealing element 1, a tool, such as a screwdriver, is inserted into the receiving space 78. The tool is brought into abutment with the free end portion 76 and moved radially from outside to inside, whereby the compression force is introduced into the fuse 50, which is such that the spring portion 60 is compressed and thus the coverage of the backup surface 66 with the support surface 52nd the housing portion 8 is reduced, so that the sealing element 1 can be removed simplified in the axial direction.

Offenbart ist ein Dichtelement zur Positionierung in einer Strömungsmaschine, wobei zur Selbstsicherung des Dichtelementes in einer Montageposition deren Tragstruktur eine Sicherung aufweist, die einen federnden Rastabschnitt hat, dessen Montagefläche in einem kleineren Winkel in Montagerichtung angestellt ist als eine Sicherungsfläche in Gegenrichtung, eine Dichteinrichtung, sowie eine Strömungsmaschine.Disclosed is a sealing element for positioning in a turbomachine, wherein for self-assurance of the sealing element in a mounting position whose support structure has a fuse which has a resilient latching portion whose mounting surface is employed at a smaller angle in the mounting direction as a backup surface in the opposite direction, a sealing device, as well a turbomachine.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Dichteelementtight element
22
Gehäusebereichhousing area
44
LaufschaufelreiheBlade row
66
Ringraumannulus
88th
vorderer Gehäuseabschnittfront housing section
1010
hinterer Gehäuseabschnittrear housing section
1212
Linieline
1414
Aufnahme / AxialvorsprungIntake / axial projection
1616
hinteres Halteelementrear retaining element
1717
Anlageflächecontact surface
1818
Umfangswandungperipheral
2020
Ringwandungannular wall
2121
Einlaufbelag / AnstreifbelagInlet lining / scuff coating
2222
Dichtstegsealing land
2424
Dichtstegsealing land
2626
Tragstruktursupporting structure
2828
Grundabschnittbase portion
3030
Wandungsabschnittwall section
3232
Vorderseitefront
3434
Rückseiteback
3636
Fußabschnittfoot section
3838
Stegweb
4040
Halteabschnittholding section
4242
Kontaktflächecontact area
4444
vorderes Halteelementfront retaining element
4646
Aufnahme / hinterer PlattformbereichPickup / rear deck area
4747
Gegenrichtungopposite direction
4848
Kontaktflächecontact area
4949
Anlageflächecontact surface
5050
Sicherungfuse
5252
Halteflächeholding surface
5454
innere Umfangsflächeinner peripheral surface
5656
äußere Umfangsflächeouter peripheral surface
5757
Montagerichtungmounting direction
5858
Rastabschnittdetent portion
6060
Federabschnittspring section
6262
Befestigungsabschnittattachment section
6464
Montageflächemounting surface
6666
Sicherungsflächesecuring face
6868
innerer Schenkelinner thigh
7070
äußerer Schenkelouter thigh
7272
Bogenabschnittarc section
7474
ÜbergangsbereichTransition area
7676
Endabschnittend
7878
Aufnahmeraumaccommodation space
αα
Montagewinkelmounting Brackets
ββ
Sicherungswinkelsafety bracket
γγ
Anstellwinkelangle of attack

Claims (10)

Dichtelement (1) einer Strömungsmaschine zum Einstellen eines Radialspaltes zwischen einer Laufschaufelreihe (4) und einem Gehäusebereich (2), mit einer Tragstruktur (26), an deren Vorderseite (32) ein Einlaufbelag (21) und an deren Rückseite (34) zumindest ein formstabiles Halteelement (16) zum Halten der Tragstruktur (26) in einer Soll-Position und eine Sicherung (50) zum Sichern der Tragstruktur (26) in ihrer Soll-Position während der Montage oder des Transports angeordnet sind, wobei das zumindest eine Halteelement (16) und die Sicherung (50) in Montagerichtung (57) hintereinander angeordnet sind und die Sicherung (50) einen Rastabschnitt (58) mit einer um einen Montagewinkel (α) in Montagerichtung (57) angestellter Montagefläche (64) und einer um einen Sicherungswinkel (β) in Gegenrichtung angestellter Sicherungsfläche (66) aufweist, und wobei der Rastabschnitt (58) über einen Federabschnitt (60) elastisch gelagert ist, dadurch gekennzeichnet, dass der Montagewinkel (α) kleiner als der Sicherungswinkel (β) ist.Sealing element (1) of a turbomachine for adjusting a radial gap between a blade row (4) and a housing portion (2), with a support structure (26), at the front side (32) an inlet lining (21) and at the rear side (34) at least one dimensionally stable holding element (16) for holding the support structure (26) in a desired position and a fuse (50) for securing the support structure (26) are arranged in their desired position during assembly or transport, wherein the at least one retaining element ( 16) and the fuse (50) in the mounting direction (57) are arranged one behind the other and the fuse (50) has a latching portion (58) with an assembly angle (α) in mounting direction (57) employee mounting surface (64) and one to a safety angle (β) has in the opposite direction hired securing surface (66), and wherein the latching portion (58) via a spring portion (60) is elastically mounted, characterized in that the mounting bracket (α) is smaller than the safety angle (β). Dichtelement nach Anspruch 1, wobei das zumindest eine Halteelement (16) einen sich in Montagerichtung erstreckenden Halteabschnitt (40) zum Bilden eines Schiebeeingriffs mit einer korrespondieren Aufnahme (14) der Strömungsmaschine hat.Sealing element according to claim 1, wherein the at least one holding element (16) has a holding portion (40) extending in the mounting direction for forming a sliding engagement with a corresponding receptacle (14) of the turbomachine. Dichtelement nach Anspruch 1 oder 2, wobei der Rastabschnitt (58) zwischen zwei Haltelementen (16, 44) angeordnet ist und mittels des zweiten Halteelements (44) ein Schiebeeingriff in Montagerichtung (57) mit einer korrespondierenden Aufnahme (46) der Strömungsmaschine bildbar ist.Sealing element according to claim 1 or 2, wherein the latching portion (58) between two holding elements (16, 44) is arranged and by means of the second holding element (44) a sliding engagement in mounting direction (57) with a corresponding receptacle (46) of the turbomachine is formed. Dichtelement nach Anspruch 1, 2 oder 3, wobei der Federabschnitt (60) ein Profil mit zwei übereinander angeordneten Schenkeln (68, 70) ist, wobei der äußere Schenkel (70) in den Rastabschnitt (58) übergeht und der innere Schenkel (68) in einen an der Rückseite (34) angebundenen Befestigungsabschnitt (62) übergeht.Sealing element according to claim 1, 2 or 3, wherein the spring portion (60) is a profile with two superimposed legs (68, 70), wherein the outer leg (70) merges into the latching portion (58) and the inner leg (68). in a on the back (34) connected to the attachment section (62) passes. Dichtelement nach Anspruch 4, wobei der innere Schenkel (68) um einen Anstellwinkel (γ) in Montagerichtung (57) angestellt ist.Sealing element according to claim 4, wherein the inner leg (68) by an angle (γ) in the mounting direction (57) is employed. Dichtelement nach Anspruch 4 oder 5, wobei sich der äußere Schenkel (70) in Montagerichtung (57) erstreckt.Sealing element according to claim 4 or 5, wherein the outer leg (70) in the mounting direction (57). Dichtelement nach einem der vorhergehenden Ansprüche, wobei der Montagewinkel (α) um wenigstens 10°, vorzugsweise um 20° bis 30°, kleiner als ein Mindestsicherungswinkel ist.Sealing element according to one of the preceding claims, wherein the mounting angle (α) by at least 10 °, preferably by 20 ° to 30 °, smaller than a minimum securing angle. Dichtelement nach einem der Ansprüche 4 bis 7, wobei in Montagrichtung der Federabschnitt (60) vor dem Rastabschnitt (58) angeordnet ist und der Rastabschnitt (58) in Montagrichtung in einen hinteren freien Endabschnitt (76) übergeht.Sealing element according to one of claims 4 to 7, wherein in the mounting direction of the spring portion (60) in front of the latching portion (58) is arranged and the latching portion (58) merges in the mounting direction in a rear free end portion (76). Dichteinrichtung einer Strömungsmaschine mit zumindest einem Dichtelement (1) nach einem der vorhergehenden Ansprüche.Sealing device of a turbomachine with at least one sealing element (1) according to one of the preceding claims. Strömungsmaschine mit zumindest einer Dichteinrichtung nach Anspruch 9.Turbomachine with at least one sealing device according to claim 9.
EP13195751.6A 2013-12-04 2013-12-04 Sealing element, sealing device and gas turbine engine Active EP2881545B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13195751.6A EP2881545B1 (en) 2013-12-04 2013-12-04 Sealing element, sealing device and gas turbine engine
ES13195751.6T ES2628679T3 (en) 2013-12-04 2013-12-04 Sealing element, sealing device and turbomachine
US14/558,415 US9803494B2 (en) 2013-12-04 2014-12-02 Sealing element, sealing unit, and turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13195751.6A EP2881545B1 (en) 2013-12-04 2013-12-04 Sealing element, sealing device and gas turbine engine

Publications (2)

Publication Number Publication Date
EP2881545A1 true EP2881545A1 (en) 2015-06-10
EP2881545B1 EP2881545B1 (en) 2017-05-31

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US (1) US9803494B2 (en)
EP (1) EP2881545B1 (en)
ES (1) ES2628679T3 (en)

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Also Published As

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US9803494B2 (en) 2017-10-31
US20150152742A1 (en) 2015-06-04
EP2881545B1 (en) 2017-05-31
ES2628679T3 (en) 2017-08-03

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