EP2796667B1 - Gleitringdichtung - Google Patents

Gleitringdichtung Download PDF

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Publication number
EP2796667B1
EP2796667B1 EP13165101.0A EP13165101A EP2796667B1 EP 2796667 B1 EP2796667 B1 EP 2796667B1 EP 13165101 A EP13165101 A EP 13165101A EP 2796667 B1 EP2796667 B1 EP 2796667B1
Authority
EP
European Patent Office
Prior art keywords
housing structure
wire element
movable wire
structure according
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP13165101.0A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2796667A1 (de
Inventor
Manfred Feldmann
Norbert Schinko
Janine Sangl
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13165101.0A priority Critical patent/EP2796667B1/de
Priority to ES13165101.0T priority patent/ES2679343T3/es
Priority to US14/249,056 priority patent/US9835039B2/en
Publication of EP2796667A1 publication Critical patent/EP2796667A1/de
Application granted granted Critical
Publication of EP2796667B1 publication Critical patent/EP2796667B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—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 with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings

Definitions

  • the present invention relates to a housing structure of a turbomachine according to the preamble of claim 1, as in the document EP 0 937 864 A2 is described. Moreover, the present invention relates to a corresponding turbomachine, such as a stationary gas turbine or an aircraft engine.
  • Turbomachines such as stationary gas turbines or aircraft engines, are known from the prior art and are used in many ways. Accordingly, many components of turbomachines are already well developed and have a variety of matched property profiles.
  • sealing and insulating elements are used in housing structures, but they are subject to wear. Particularly in the case of high-speed low-pressure turbines in turbomachines, which are increasingly used to increase efficiency, the sealing and insulating elements in the housing structure are subject to increased wear due to the higher pressure loads. It is therefore desirable to remedy this situation, since at a high wear of the components by replacing the worn components high costs, especially high maintenance costs arise.
  • Such housing structures with sealing elements for gas turbines are for example from the publications EP 0 940 562 A2 . US 3,656,862 and US 2005/0232752 A1 known.
  • the housing structure should, however, be simple and reliably fulfill its other tasks.
  • the invention proposes, in a housing structure with an outer housing wall and the flow channel bounding inner wall, wherein between the inner wall and outer housing wall, a cavity is formed, the cavity with a sealing element detachable, in particular in the axial direction of the turbomachine separable to design to different pressure conditions to allow in the cavity.
  • the separation should be made possible in particular in the area of a so-called outer-air seal, that is to say in a sealing area between the blade tips and the inner wall of the housing structure.
  • a movable wire element is to be arranged as a separation or sealing element in the cavity, which may bear against contact surfaces or sealing surfaces to effect the separation or seal.
  • an abradable coating for blade tips is provided on the inner wall, wherein the movable wire element is arranged in the region of the abradable coating on the opposite, opposite side of the inner wall.
  • the mobility of the wire element is understood to mean that the wire element can move as a body itself, ie is moved translationally or rotationally, or that movement takes place by a movement of at least parts of the wire element due to a deformation of the wire element.
  • the movable wire element is not firmly clamped and arranged in the cavity, but is within certain limits movable to accommodate the different pressure and temperature conditions during operation and to be able to adapt to the surrounding components.
  • the movable wire element may be formed at least partially circumferentially around the flow channel, wherein in particular a completely circumferential arrangement is advantageous in order to provide over the entire circumference of the housing structure, the sealing effect can.
  • the movable wire element which may also be referred to as a mechanical seal, be formed in particular annular.
  • the mechanical seal or the movable wire element to allow a deformability or mobility in the circumferential direction to be slotted at least once, that is, be executed interrupted in the circumferential direction.
  • the wire element may be formed of an elastic material which, under the operating conditions, permits elastic deformation of the movable wire element in order to allow adaptation to adjacent components and in particular contact surfaces intended to form a seal.
  • the housing structure may be formed so that the cavity has a cross-sectional constriction on which at least partially the contact surfaces are formed, which together with the movable wire element form the seal.
  • the movable wire element or the mechanical seal and thus also the cross-sectional constriction of the cavity can be arranged in a region of the housing structure which corresponds to the region in which a scraper pad is arranged in the flow channel for co-operation with the blade tips.
  • the movable wire element can be arranged in the region of a so-called outer-air seal, since in this area particularly high pressure differences can occur, which can be intercepted accordingly by the mechanical seal in the housing structure.
  • the mechanical seal may have any cross-section, such as a circular or semi-circular or polygonal cross-section.
  • the shape of the cross section may be influenced by the neighboring components.
  • the mechanical seal may be formed as a solid body or as a hollow body, so for example be formed in cross-section as a solid cylinder or as a hollow cylinder.
  • the mobility of the mechanical seal can be provided in particular in the axial and / or circumferential direction, wherein the mobility in the circumferential direction may include on the one hand a rotation about the longitudinal axis of the flow channel, as well as a longitudinal expansion or circumferential expansion.
  • the mobility in the axial direction may include an axial displacement and a deformation in the axial direction, for example, an elastic deformation when pressed against the contact surfaces.
  • the movement of the mechanical seal is limited by the adjacent components. Under operating load, the movement is limited insofar that the sealing element always on the two angular sealing surfaces is pressed to each other. Movements of the two sealing surfaces to each other can thus be compensated by the sealing element.
  • At least one radially projecting into the cavity holding member may be provided, so that the displacement distance for the mechanical seal can be limited.
  • the Fig. 1 shows in a partial sectional view of a housing structure of an aircraft engine with an outer housing wall 1 and an inner wall 2, which are arranged circumferentially around a flow channel in which the fluid of the turbomachine, so for example the combustion gases of an aircraft engine are guided to drive blades.
  • the blades are arranged with their tips so that between the inside of the inner wall 2 and the tips of the blades as little or no gap as possible in order to avoid drive losses for the blades by flowing past the combustion gases.
  • an abradable coating 3 which is in contact with the tips of the blade in order to form a so-called outer air seal (OAS).
  • the housing structure comprises in addition to the inner wall 2 an outer housing wall 1 and arranged therebetween elements, such as heat shields, insulating elements or cavities 4, and has the task to reduce or absorb the pressure and temperature differences between the flow channel and the external environment during operation of the turbomachine.
  • a corresponding cavity 4 can serve, for example, for guiding cooling air and for receiving corresponding components in order to be able to realize the temperature difference between the outside of the outer wall and the inner side of the inner wall.
  • the cavity 4 is likewise subdivided into two regions 5 and 6, in which different pressure ratios p1 and p2 are to be set according to the pressure conditions in the flow channel For example, to prevent the entry of hot gas from the flow channel via shocks that occur at the segmentally constructed inner wall 2.
  • different pressure ratios p1 and p2 are to be set according to the pressure conditions in the flow channel
  • a recess 7 is formed in the cavity 4 between the separable regions 5 and 6, which leads to a reduction in the cross section of the cavity 4, so that at the recess 7, a movable wire element 10, a so-called mechanical seal, can be arranged against abutment surfaces 8 and 9 can lie, which are formed on the one on the indentation 7 and the other on the inner wall 2 or arranged thereon heat shield or the like. Since the pressure p1 at a flow direction of the fluid or hot gas in Fig. 1 from left to right is greater than the pressure p2, the mechanical seal 10 is automatically pressed against the contact surfaces 8 and 9 so as to effect a separation of the regions 5 and 6 and a sealing of these regions.
  • the cross section of the wire element is circular and the wire element is formed as a solid body, ie in the form of a curved solid cylinder or torus.
  • the wire element 10 is just like the inner wall 2 and the outer housing wall 1 and the components provided therebetween circumferentially arranged around the flow channel, so that the mechanical seal or the wire element 10 may have a ring shape.
  • the ring may have a break in the circumferential direction to allow the ring to widen and contract circumferentially, i. that he can move. This is advantageous in order to compensate for the temperature fluctuations occurring during operation and the resulting changes in length.
  • the mechanical seal 10 may be formed of a resilient material, in particular in the operating conditions, such as a resilient metallic material, to allow easy deformability, which advantageously results in that the mechanical seal 10 to the surrounding components and In particular, the contact surfaces 8, 9 can adjust.
  • the movable wire element or the mechanical seal 10 is not fixed, but in particular in the axial direction and in the circumferential direction has at least a certain free mobility, in the cavity 4, a radially extending into the cavity 4 bracket 11 is provided, the axial mobility limited the mechanical seal 10 and holds the mechanical seal 10 at the site.
  • This holder 11 can be designed as a separate component or integrated into adjacent components.
  • FIG Fig. 2 A second embodiment of a housing structure according to the invention is shown in FIG Fig. 2 shown.
  • the embodiment of the Fig. 2 is largely identical to the embodiment of the Fig. 1 , so that the same components are provided with the same reference numerals and a repeated description of these components is omitted. It is thus only on the differences of the embodiment of Fig. 2 with respect to the embodiment of the Fig. 1 received.
  • the main difference of the embodiment of the Fig. 2 compared to the embodiment of the Fig. 1 is in the form of the mechanical seal 10.
  • a semicircular shaped wire element 10 ' is used, wherein in the illustration of Fig. 2
  • the cross-sectional shape of the wire element 10 is dashed Fig. 1 is shown.
  • the mechanical seal can have any cross-sectional shapes that can be adapted to the given boundary conditions, so that in certain environmental conditions rectangular, square, polygonal or other freely shaped cross-sectional shapes, but also in the circumferential direction changing cross-sectional shapes are conceivable.
  • a radially protruding bracket 11 ' which in the embodiment of the Fig. 2 is arranged on the side of the inner wall, while in the embodiment of the Fig. 1 the holder 11 protrudes from the outside inwards.
  • the holder 11 ' may be designed as a separate component or integrated into adjacent components.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Devices (AREA)
EP13165101.0A 2013-04-24 2013-04-24 Gleitringdichtung Not-in-force EP2796667B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13165101.0A EP2796667B1 (de) 2013-04-24 2013-04-24 Gleitringdichtung
ES13165101.0T ES2679343T3 (es) 2013-04-24 2013-04-24 Junta de estanqueidad deslizante
US14/249,056 US9835039B2 (en) 2013-04-24 2014-04-09 Slide ring seal

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13165101.0A EP2796667B1 (de) 2013-04-24 2013-04-24 Gleitringdichtung

Publications (2)

Publication Number Publication Date
EP2796667A1 EP2796667A1 (de) 2014-10-29
EP2796667B1 true EP2796667B1 (de) 2018-06-27

Family

ID=48182784

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13165101.0A Not-in-force EP2796667B1 (de) 2013-04-24 2013-04-24 Gleitringdichtung

Country Status (3)

Country Link
US (1) US9835039B2 (es)
EP (1) EP2796667B1 (es)
ES (1) ES2679343T3 (es)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3656862A (en) * 1970-07-02 1972-04-18 Westinghouse Electric Corp Segmented seal assembly
DE19807247C2 (de) * 1998-02-20 2000-04-20 Mtu Muenchen Gmbh Strömungsmaschine mit Rotor und Stator
US6146091A (en) * 1998-03-03 2000-11-14 Mitsubishi Heavy Industries, Ltd. Gas turbine cooling structure
US7063503B2 (en) * 2004-04-15 2006-06-20 Pratt & Whitney Canada Corp. Turbine shroud cooling system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP2796667A1 (de) 2014-10-29
US20140321969A1 (en) 2014-10-30
ES2679343T3 (es) 2018-08-24
US9835039B2 (en) 2017-12-05

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