WO2002090720A1 - Anordnung für eine nicht-hermetische dichtung - Google Patents
Anordnung für eine nicht-hermetische dichtung Download PDFInfo
- Publication number
- WO2002090720A1 WO2002090720A1 PCT/DE2002/001402 DE0201402W WO02090720A1 WO 2002090720 A1 WO2002090720 A1 WO 2002090720A1 DE 0201402 W DE0201402 W DE 0201402W WO 02090720 A1 WO02090720 A1 WO 02090720A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- ring
- bristles
- sealing
- sealing ring
- brush
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
- F16J15/3288—Filamentary structures, e.g. brush seals
-
- 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
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/56—Brush seals
Definitions
- the invention relates to an arrangement for a non-hermetic seal between a stator and a rotor of a turbomachine, according to the preamble of claim 1.
- turbomachines refers to power-absorbing and bladed turbomachines with stator and rotor, such as compressors, pumps and turbines.
- the invention is particularly aimed at gas turbines in an at least partially axial design for mobile and stationary applications, but it can also be of interest, for example, for steam turbines. This specifically concerns the sealing area between the guide vanes and the rotor radially within the actual flow channel. In gas turbine technology, this area is often referred to as the Inner Air Seal (IAS).
- IAS Inner Air Seal
- a spoke centering offers advantages where, due to thermal influences, significant relative dimensional changes occur between coaxially arranged, connected components. Since the thermal exposure and the heat capacity of neighboring components can be very different, one component, for example, stretches earlier, faster or more than another, adjacent component.
- a spoke centering comprises at least three bearing points evenly distributed over the circumference of the component, each with radial relative mobility.
- the bearing points with a translational degree of freedom can be designed, for example, as a sliding block / groove or pin / socket combination. Spoke-centered components are locked against rotation and remain concentric with relative changes in size (circumference, diameter). There is also a relative axial fixation realizable.
- a contact element (9) in the form of an edge or bead is present on the side with a lower operating pressure, against which the brush sealing ring (positions 1, 2) is pressed, and also a sealing function takes over.
- the contact element (9) seals on the radially outer edge of a brush sealing face, so that the operating pressure difference is effective on a large part of the brush sealing face.
- the effective area extends radially from the rotating sealing surface on the inner part (3) to the contact element (9). The product of the pressure difference and effective area can lead to a considerable axial force on the brush sealing ring and ultimately the contact element.
- the object of the invention is to provide an arrangement for a non-hermetic seal between a ring-shaped guide vane grille and a rotor of an at least partially axial type turbomachine which, using the principle of the spoke-centered brush seal, makes significant improvements by reducing friction and wear, by means of a centering without force and by reducing the secondary leakage in the area of the axial contact surface of the brush sealing ring.
- a support ring is arranged in radial proximity to the rotating sealing surface, which is integrally connected to the guide vane feet and is therefore no longer part of the brush sealing ring.
- the arrangement is relieved of pressure axially as far as possible and thus free of forces, since the operating pressure difference is effective in the area of the small, annular bristle surface between the rotor and the support ring.
- the support ring Since the expected bristle wear on the support ring is small and tends to be smaller than the wear on the rotating sealing surface, the latter type of wear should remain the criterion for an exchange of the brush sealing ring. It is assumed that beyond the replacement of the brush sealing ring, relevant repair measures will not be necessary either on the rotor or on the guide vane feet including the support ring. Depending on whether the guide vanes of a ring are all integrally connected or arranged in segments or as individual parts, the support ring will also be made in one piece or interrupted by parting lines, that is to say segmented.
- FIG. 1 shows a partial longitudinal section through a gas turbine in the area of an inner air seal
- FIG. 2 shows an axial partial view of the sealing elements according to FIG. 1
- FIG. 3 shows a cross section through a brush sealing ring with guide element
- FIG. 4 shows an axial partial view of the brush sealing ring according to FIG. 3
- FIG. 5 shows a cross section with a burst sealing ring with stiffening ring and with guide elements
- FIG. 6 shows an axial partial view of the brush sealing ring according to FIG. 5
- FIG. 7 shows a cross section through a brush sealing ring in a welded construction with guide elements
- FIG. 8 shows an axial partial view of the brush sealing ring according to FIG. 7
- 9 shows an axial partial view of the sealing elements according to FIG. 1 in the region of a parting line.
- FIG. 1 shows an arrangement 1 according to the invention in the area of an inner air seal of a gas turbine engine.
- a guide vane 2 can be seen, the suspension of which on the stator, i.e. on the engine housing, is not shown, since it should be carried out in a known manner.
- Left and right, i.e. Upstream and downstream of the guide blade 2 rotor blades 8 and 9 can be seen, which are components of a rotor 6.
- the latter also includes a co-rotating, cylindrical sealing surface 7.
- the foot 3 of the guide vane 2 extends radially inwards, here downwards, into the actual sealing area on the rotor. All guide blades 2 together, including their feet 3, form a rotor-concentric ring with an essentially radial blade orientation.
- the guide vanes are often integrally connected, e.g. in the form of a cast or welded construction, in larger machines it is common to combine several blades integrally to form a segment, in which case several such segments form a vane ring. There are parting lines between the segments, which can be bridged with suitable sealing elements if necessary. In extreme cases, each individual guide vane forms a separate component, which can make assembly easier.
- a burst sealing ring 10 is suspended from the guide vane feet 3 via a spoke centering 4.
- the arrangement 1 separates a room with a higher operating pressure p1 from a room with a lower operating pressure p2.
- a possibly segmented support ring 5 for the bristles of the brush sealing ring 10 is arranged at a small radial distance A from the sealing surface 7 and is optionally connected to the guide vane feet 3. Since the spoke centering 4 is designed to be pressure-permeable, the higher operating pressure p1 also acts on the right end face of the brush sealing ring up to the point where the support ring 5 bears against the bristles.
- FIG. 2 shows a partial axial view of the sealing elements for better understanding.
- the rotating sealing surface 7, the bristles 13 which are set at an angle ⁇ in accordance with the direction of rotation, and a sliding block-like guide element 22 which is mounted in a groove 16 of the guide vane foot 3 in a radially displaceable manner. It would also be conceivable to arrange the groove on the brush sealing ring and the sliding block on the guide blade root.
- FIG. 3 shows, on a larger scale, an axial section through the brush sealing ring 10 in the region of the guide element 22.
- This is a frictional variant of the brush sealing ring, in which the bristles 13 are guided around a core 19 and fixed by means of a C-shaped clamping ring 17 , Both ends of each bristle are thus in the sealing area on the rotor.
- the guide element 22 is frictionally and adjustably fixed on the clamping ring 17 by means of a clamping screw 26.
- Figure 4 shows the associated axial view.
- FIG. 5 shows a burst sealing ring 11, the brush element of which is stabilized by means of a two-part stiffening ring 28.
- a two-part stiffening ring 28 Such an embodiment is suitable for geometries with a larger diameter, in which the unit comprising the clamping ring 18, core 20 and bristles 14 would no longer be sufficiently dimensionally stable.
- the stiffening ring 28 is guided around the outer circumference of the clamping ring 18 and also holds it positively against deflections in both axial directions.
- an integral cover ring 29 is guided radially inward relatively far, which can protect the bristles 14 in particular against rotation-induced eddy currents.
- the guide elements 23, 24 for the spoke centering are fastened here by means of a rivet 27, which also holds the parts of the stiffening ring 28 together.
- the guide elements 23, 24 can be made rotatable about the rivet axis, which can benefit the smooth running of the spoke centering.
- a cover ring can often be dispensed with.
- Another version could look like a shoulder on the stiffening ring as axial stop serves for the brush element, whereas on the other side radially inwardly drawn guide elements take over this function.
- FIG. 6 shows the axial view belonging to FIG. 5.
- FIG. 7 shows a burst sealing ring 12, the bristles 15 of which are not - or at least not exclusively - clamped in a frictionally engaged manner, but are integrally integrated into a retaining ring by means of a weld seam 30.
- a comparable fastening could also be achieved by soldering or gluing, with possibly reduced temperature resistance.
- the guide elements 25 on both sides are machined out of the retaining ring 21 by material removal, e.g. by milling or ECM processing.
- FIG. 8 again shows the associated axial view.
- Figure 9 finally relates to designs with parting lines between guide vane feet, i.e. Versions with segmented vanes or arranged as individual parts.
- the bristles 13 are placed at an angle to the rotating sealing surface 7 - more precisely to their local tangent.
- the otherwise radial parting line is guided in the bristle region at an angle ⁇ , which preferably results in a right-angled crossover with the bristle direction ⁇ . If this leads to problems regarding the mounting of the guide vanes, the parting line can also be angled less or only run radially.
- the arrangement of the bristles in the brush sealing ring can be not only predominantly radial but also axial with the free ends being bent radially (hook brush seal).
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Sealing Devices (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP02737800A EP1386059B1 (de) | 2001-05-10 | 2002-04-16 | Anordnung für eine nicht-hermetische dichtung in einer turbomaschine |
UA20031211302A UA74645C2 (en) | 2001-05-10 | 2002-04-16 | Appliance for untight seal |
CA002446412A CA2446412C (en) | 2001-05-10 | 2002-04-16 | Device for a non-hermetic seal |
US10/476,925 US6932347B2 (en) | 2001-05-10 | 2002-04-16 | Device for a non-hermetic seal |
DE50212476T DE50212476D1 (de) | 2001-05-10 | 2002-04-16 | Anordnung für eine nicht-hermetische dichtung in einer turbomaschine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10122732.9 | 2001-05-10 | ||
DE10122732A DE10122732C2 (de) | 2001-05-10 | 2001-05-10 | Anordnung für eine nicht-hermetisch abdichtende Dichtung |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2002090720A1 true WO2002090720A1 (de) | 2002-11-14 |
Family
ID=7684289
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE2002/001402 WO2002090720A1 (de) | 2001-05-10 | 2002-04-16 | Anordnung für eine nicht-hermetische dichtung |
Country Status (7)
Country | Link |
---|---|
US (1) | US6932347B2 (de) |
EP (1) | EP1386059B1 (de) |
CA (1) | CA2446412C (de) |
DE (2) | DE10122732C2 (de) |
RU (1) | RU2303139C2 (de) |
UA (1) | UA74645C2 (de) |
WO (1) | WO2002090720A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10331601B4 (de) | 2003-07-12 | 2019-06-06 | MTU Aero Engines AG | Dichtungsanordnung und Verfahren zur Herstellung derselben |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10259381A1 (de) * | 2002-12-18 | 2004-07-15 | Mtu Aero Engines Gmbh | Dichtungsanordnung |
DE10320450B4 (de) | 2003-05-08 | 2013-07-18 | Mtu Aero Engines Gmbh | Dichtungsanordnung |
DE102004038933A1 (de) | 2004-08-11 | 2006-02-23 | Mtu Aero Engines Gmbh | Dichtungsanordnung |
DE102007010378A1 (de) * | 2007-03-03 | 2008-09-04 | Mtu Aero Engines Gmbh | Dichtelement zur Abdichtung eines Spaltes zwischen Stator und Rotor einer axialen Strömungsmaschine |
US8414254B2 (en) * | 2008-02-18 | 2013-04-09 | United Technologies Corporation | Sealing assembly for a turbine engine |
US9371733B2 (en) | 2010-11-16 | 2016-06-21 | Mtu Aero Engines Gmbh | Rotor blade arrangement for a turbo machine |
DE102011083814A1 (de) | 2011-09-30 | 2013-04-04 | Mtu Aero Engines Gmbh | Segmentiertes Bauteil |
US20130106061A1 (en) * | 2011-10-28 | 2013-05-02 | General Electric Company | High temperature seal system |
US9097128B2 (en) * | 2012-02-28 | 2015-08-04 | General Electric Company | Seals for rotary devices and methods of producing the same |
FR3010462B1 (fr) * | 2013-09-11 | 2021-10-08 | Snecma | Secteur angulaire de redresseur pour compresseur de turbomachine comportant un joint d'etancheite a brosse |
DE102015224379A1 (de) | 2015-12-04 | 2017-06-08 | MTU Aero Engines AG | Stabilisierter Dichtring für eine Strömungsmaschine |
DE102018202279A1 (de) * | 2018-02-14 | 2019-08-14 | MTU Aero Engines AG | Bürstendichtung mit mehreren im Abstand angeordneten Befestigungselementen |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4919439A (en) * | 1987-10-09 | 1990-04-24 | Williams International Corporation | Balanced ring seal |
US5114159A (en) * | 1991-08-05 | 1992-05-19 | United Technologies Corporation | Brush seal and damper |
US5351971A (en) * | 1993-05-21 | 1994-10-04 | Eg&G Sealol, Inc. | Brush seal device having a floating backplate |
DE19628559A1 (de) * | 1996-07-16 | 1998-01-29 | Mtu Muenchen Gmbh | Dichtungseinrichtung für gegeneinander rotierende Teile |
US5715596A (en) * | 1995-11-30 | 1998-02-10 | United Technologies Corporation | Brush seal for stator of a gas turbine engine case |
DE19720649A1 (de) * | 1997-05-16 | 1998-11-19 | Mtu Muenchen Gmbh | Bürstendichtung |
US5884918A (en) * | 1996-10-04 | 1999-03-23 | Eg&G Sealol, Inc. | Brush seal with a flexible front plate |
DE19803502A1 (de) * | 1998-01-30 | 1999-08-12 | Behr Gmbh & Co | Lüfteranordnung |
US6168162B1 (en) * | 1998-08-05 | 2001-01-02 | General Electric Co. | Self-centering brush seal |
WO2001013013A1 (de) * | 1999-08-11 | 2001-02-22 | Mtu Aero Engines Gmbh | Bürstendichtring |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB9525212D0 (en) * | 1995-12-09 | 1996-02-07 | Rolls Royce Plc | Brush seal |
US6173962B1 (en) * | 1995-12-09 | 2001-01-16 | Rolls Royce Plc | Brush seal |
-
2001
- 2001-05-10 DE DE10122732A patent/DE10122732C2/de not_active Expired - Fee Related
-
2002
- 2002-04-16 RU RU2003134152/06A patent/RU2303139C2/ru not_active IP Right Cessation
- 2002-04-16 EP EP02737800A patent/EP1386059B1/de not_active Expired - Lifetime
- 2002-04-16 UA UA20031211302A patent/UA74645C2/uk unknown
- 2002-04-16 CA CA002446412A patent/CA2446412C/en not_active Expired - Fee Related
- 2002-04-16 WO PCT/DE2002/001402 patent/WO2002090720A1/de active IP Right Grant
- 2002-04-16 DE DE50212476T patent/DE50212476D1/de not_active Expired - Lifetime
- 2002-04-16 US US10/476,925 patent/US6932347B2/en not_active Expired - Lifetime
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4919439A (en) * | 1987-10-09 | 1990-04-24 | Williams International Corporation | Balanced ring seal |
US5114159A (en) * | 1991-08-05 | 1992-05-19 | United Technologies Corporation | Brush seal and damper |
US5351971A (en) * | 1993-05-21 | 1994-10-04 | Eg&G Sealol, Inc. | Brush seal device having a floating backplate |
US5715596A (en) * | 1995-11-30 | 1998-02-10 | United Technologies Corporation | Brush seal for stator of a gas turbine engine case |
DE19628559A1 (de) * | 1996-07-16 | 1998-01-29 | Mtu Muenchen Gmbh | Dichtungseinrichtung für gegeneinander rotierende Teile |
US5884918A (en) * | 1996-10-04 | 1999-03-23 | Eg&G Sealol, Inc. | Brush seal with a flexible front plate |
DE19720649A1 (de) * | 1997-05-16 | 1998-11-19 | Mtu Muenchen Gmbh | Bürstendichtung |
DE19803502A1 (de) * | 1998-01-30 | 1999-08-12 | Behr Gmbh & Co | Lüfteranordnung |
US6168162B1 (en) * | 1998-08-05 | 2001-01-02 | General Electric Co. | Self-centering brush seal |
WO2001013013A1 (de) * | 1999-08-11 | 2001-02-22 | Mtu Aero Engines Gmbh | Bürstendichtring |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10331601B4 (de) | 2003-07-12 | 2019-06-06 | MTU Aero Engines AG | Dichtungsanordnung und Verfahren zur Herstellung derselben |
Also Published As
Publication number | Publication date |
---|---|
RU2303139C2 (ru) | 2007-07-20 |
US6932347B2 (en) | 2005-08-23 |
DE50212476D1 (de) | 2008-08-21 |
CA2446412A1 (en) | 2002-11-14 |
RU2003134152A (ru) | 2005-05-20 |
US20040188943A1 (en) | 2004-09-30 |
EP1386059B1 (de) | 2008-07-09 |
DE10122732C2 (de) | 2003-04-30 |
UA74645C2 (en) | 2006-01-16 |
CA2446412C (en) | 2009-04-14 |
DE10122732A1 (de) | 2002-11-28 |
EP1386059A1 (de) | 2004-02-04 |
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