EP1673519A1 - Dichtungsanordnung für eine gasturbine - Google Patents
Dichtungsanordnung für eine gasturbineInfo
- Publication number
- EP1673519A1 EP1673519A1 EP04786886A EP04786886A EP1673519A1 EP 1673519 A1 EP1673519 A1 EP 1673519A1 EP 04786886 A EP04786886 A EP 04786886A EP 04786886 A EP04786886 A EP 04786886A EP 1673519 A1 EP1673519 A1 EP 1673519A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sealing
- rotor
- guide vane
- sealing arrangement
- arrangement according
- 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
Links
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
-
- 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
- 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
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/28—Three-dimensional patterned
- F05D2250/283—Three-dimensional patterned honeycomb
Definitions
- the invention relates to a sealing arrangement for a gas turbine according to the preamble of patent claim 1.
- Gas turbines consist of several assemblies, for example a fan, a combustion chamber, preferably several compressors and several turbines.
- the preferably several turbines are in particular a high-pressure turbine and a low-pressure turbine, and the several compressors are in particular a high-pressure compressor and a low-pressure compressor.
- a plurality of guide vane rings are positioned one behind the other in a turbine and a compressor of a gas turbine in the axial direction or in the flow direction of the gas turbine, each guide vane ring having a plurality of guide vanes which are arranged distributed over the circumference.
- a rotor blade ring which has a plurality of rotor blades, is positioned between each two adjacent guide vane rings. The rotor blades are assigned to a rotor and rotate together with the rotor with respect to a fixed housing and also the guide vanes of the guide vane rings, which are also designed to be stationary.
- sealing arrangements are known from the prior art which serve to seal a gap between the radially inner ends of the fixed guide vanes and the rotor of the gas turbine, these sealing arrangements being designed in this way are that the rotor has at least two sealing projections which run in the circumferential direction of the rotor and are positioned at an axial distance from one another and which interact with inlet linings which are assigned to the radially inner ends of the fixed guide vanes.
- the present invention relates to a sealing arrangement for sealing the gap between radially inner ends of the guide blades of a guide blade ring and a rotor of the gas turbine.
- the present invention is based on the problem of creating a novel sealing arrangement for a gas turbine.
- the sealing projections are inclined or inclined in the axial direction towards a side of higher pressure, at least one recirculation structure being arranged in a space delimited by the at least two sealing projections and the corresponding inlet linings, and the or each recirculation structure being on the side of higher pressure is aligned.
- the sealing projections are designed as sealing fins and the inlet linings as honeycomb structures.
- the sealing projections interacting with a guide vane ring and the corresponding inlet linings of the guide vane ring preferably have different radii, with outer radii of the sealing projections and inner radii of the inlet linings increasing or increasing in the direction of the side of higher pressure.
- FIG. 1 shows a schematic cross section through a compressor 10 of a gas turbine with a fixed housing 11 and a rotor 12 rotating relative to the fixed housing 11, the fixed housing 11 and the rotor 12 delimiting a main flow channel 13.
- the direction of flow through the main flow channel 13 is visualized in FIG. 1 by an arrow 14.
- a plurality of stationary guide vane rings 15 are arranged one behind the other in the main flow channel 13 in the axial direction or in the flow direction, FIG. 1 only showing such a guide vane ring 15.
- Each guide vane ring 15 is formed by a plurality of guide vanes 16 which are arranged around the rotor 12 at an axial position of the compressor 10 in the circumferential direction thereof.
- the fixed guide vanes 16 are integrated into the housing 11 with a radially outer end 17.
- a gap 19 is formed between a radially inner end 18 of the guide vanes 16 opposite the radially outer end 17 and the rotor 12.
- a rotor blade ring is arranged between two adjacent, stationary guide vane rings 15. 1 shows such a rotor blade ring 20, which is formed from a plurality of rotor blades 21 which are fastened to the rotor 12 with a radially inner end 22. Again, a gap is formed between a radially outer end 23 of the blades 21 and the housing 11 of the compressor 10. To seal this radial gap between the radially outer ends 23 of the rotating blades 20 and the fixed gear Housing 1 1 is assigned to housing 1 1, a so-called run-in coating 24, which enables the radially outer ends 23 of rotor blades 21 to be rubbed against housing 1 1 of compressor 10 with little wear.
- the present invention relates to a sealing arrangement for sealing the gap 19 between the radially inner ends 18 of the stationary guide vanes 16 of a guide vane ring 15 and the rotor 12 of the compressor 10.
- this sealing arrangement comprises two associated with the rotor 12 Sealing protrusions 25 and 26.
- the sealing projections 25 and 26 are designed as so-called sealing fins and are spaced apart from one another in the axial direction of the compressor 10.
- the sealing projections 25 and 26 extend over the entire circumference of the rotor 12, that is to say they are closed in the circumferential direction.
- the sealing projections 25 and 26 cooperate with inlet linings 27 and 28.
- the inlet linings 27 and 28 are assigned to the radially inner ends 18 of the fixed guide vanes 16, namely integrated into the radially inner ends 18 of the guide vanes 16 designed as a platform.
- the inlet linings 27 and 28 are accordingly designed to be stationary and the sealing projections 25 and 26 rotate together with the rotor 12 relative to the stationary inlet linings 27 and 28.
- the inlet linings 27 and 28 are preferably designed as honeycomb seals, with honeycombs of these honeycomb structures in the direction of the sealing projections 25 and 26 are open.
- the gas pressure inside the compressor increases in the direction of flow (arrow 14).
- the sealing projections 25 and 26, which - as already mentioned - are designed as sealing fins, are inclined or inclined in the axial direction towards a side of higher gas pressure.
- FIG. 1 shows that the flow direction of the main flow channel 13 of the compressor 10 runs from left to right, that is to say a gas pressure on the right side of the guide vanes 16 is higher than on the left side of the latter.
- the sealing projections 25 and 26 are with their tips to the right side, that is to the side higher gas pressure, inclined. This optimizes the sealing effect of the sealing projections 25 and 26.
- a recirculation structure 30 is arranged in a space 29 delimited by the sealing projections 25 and 26 and the corresponding inlet linings 27 and 28.
- the recirculation structure 30 is integrated into the radially inner end 18 of the guide vanes 16 of the guide vane ring 15, the radially inner ends 18 being designed as a platform for the guide vanes 16.
- the inlet linings 27 and 28, which are also assigned to the radially inner end 18 of the guide vanes 16, are arranged on both sides of the recirculation structure 30 according to FIG. 1. It is within the meaning of the present invention that the recirculation structure 30, like the sealing projections 25 and 26, is oriented towards the side of higher gas pressure.
- the sealing effect is further optimized by integrating a recirculation structure 30 designed in this way into the sealing arrangement comprising sealing projections 25 and 26 and corresponding inlet linings 27 and 28.
- the two sealing projections 25 and 26 and the two inlet linings 27 and 28 interacting with the sealing projections 25 and 26 have stepped radii.
- the sealing protrusion 26 located downstream in the direction of flow (arrow 14), which in the case of a compressor is accordingly arranged on the side of higher gas pressure than the upstream sealing protrusion 25, has an outer radius that is larger than that of the upstream sealing protrusion 25.
- the inlet lining 28 cooperating with the downstream sealing projection 26 also has a larger inner diameter than the inlet lining 27 interacting with the upstream sealing projection 25.
- the recirculation structure 30 projects radially beyond the downstream inlet lining 28.
- each guide vane ring 15 is shown in the schematic representation according to FIG. 1, a plurality of such guide vane rings are positioned one behind the other in the compressor 10 in the axial direction.
- Each guide vane ring can have a sealing arrangement as described above for sealing the radial gap 19 between the radially inner ends 18 of the fixed guide vanes and the rotor 12.
- the present invention is preferably used to reduce the leakage in the so-called statorwell cavities of high-pressure compressors of an aircraft engine.
- the sealing arrangement according to the invention can also be used in the turbines of aircraft engines or in stationary gas turbines.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2003148290 DE10348290A1 (de) | 2003-10-17 | 2003-10-17 | Dichtungsanordnung für eine Gasturbine |
PCT/DE2004/002174 WO2005040561A1 (de) | 2003-10-17 | 2004-09-30 | Dichtungsanordnung für eine gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1673519A1 true EP1673519A1 (de) | 2006-06-28 |
EP1673519B1 EP1673519B1 (de) | 2012-08-29 |
Family
ID=34428460
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04786886A Expired - Fee Related EP1673519B1 (de) | 2003-10-17 | 2004-09-30 | Dichtungsanordnung für eine gasturbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US9011083B2 (de) |
EP (1) | EP1673519B1 (de) |
DE (1) | DE10348290A1 (de) |
WO (1) | WO2005040561A1 (de) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2014020509A (ja) * | 2012-07-20 | 2014-02-03 | Toshiba Corp | シール装置、軸流タービン、および発電プラント |
JPWO2014077058A1 (ja) * | 2012-11-13 | 2017-01-05 | 三菱重工コンプレッサ株式会社 | 回転機械 |
DE102013224199A1 (de) * | 2013-11-27 | 2015-05-28 | MTU Aero Engines AG | Gasturbinen-Laufschaufel |
US10215192B2 (en) * | 2014-07-24 | 2019-02-26 | Siemens Aktiengesellschaft | Stator vane system usable within a gas turbine engine |
DE102017204243A1 (de) * | 2017-03-14 | 2018-09-20 | MTU Aero Engines AG | Dichtfin mit zumindest einer gewölbten Seitenflanke |
FR3099788B1 (fr) * | 2019-08-06 | 2021-09-03 | Safran Aircraft Engines | Abradable de turbine de turbomachine comprenant une face d’usure pourvue de redresseurs de flux |
Family Cites Families (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1689735A (en) * | 1923-10-05 | 1928-10-30 | Losel Franz | Labyrinth gland construction |
US1857961A (en) * | 1927-12-15 | 1932-05-10 | Westinghouse Electric & Mfg Co | Bi-metal packing |
US1756958A (en) * | 1928-10-03 | 1930-05-06 | Westinghouse Electric & Mfg Co | Elastic-fluid turbine |
US4351532A (en) * | 1975-10-01 | 1982-09-28 | United Technologies Corporation | Labyrinth seal |
US4513975A (en) * | 1984-04-27 | 1985-04-30 | General Electric Company | Thermally responsive labyrinth seal |
US5244216A (en) * | 1988-01-04 | 1993-09-14 | The Texas A & M University System | Labyrinth seal |
US5029876A (en) * | 1988-12-14 | 1991-07-09 | General Electric Company | Labyrinth seal system |
US5281090A (en) * | 1990-04-03 | 1994-01-25 | General Electric Co. | Thermally-tuned rotary labyrinth seal with active seal clearance control |
US5354174A (en) * | 1990-09-12 | 1994-10-11 | United Technologies Corporation | Backbone support structure for compressor |
US5118253A (en) * | 1990-09-12 | 1992-06-02 | United Technologies Corporation | Compressor case construction with backbone |
US5127797A (en) * | 1990-09-12 | 1992-07-07 | United Technologies Corporation | Compressor case attachment means |
US5236302A (en) * | 1991-10-30 | 1993-08-17 | General Electric Company | Turbine disk interstage seal system |
US5218816A (en) * | 1992-01-28 | 1993-06-15 | General Electric Company | Seal exit flow discourager |
US5320488A (en) * | 1993-01-21 | 1994-06-14 | General Electric Company | Turbine disk interstage seal anti-rotation system |
US5333993A (en) * | 1993-03-01 | 1994-08-02 | General Electric Company | Stator seal assembly providing improved clearance control |
US5380155A (en) * | 1994-03-01 | 1995-01-10 | United Technologies Corporation | Compressor stator assembly |
GB2307520B (en) * | 1995-11-14 | 1999-07-07 | Rolls Royce Plc | A gas turbine engine |
US5749701A (en) * | 1996-10-28 | 1998-05-12 | General Electric Company | Interstage seal assembly for a turbine |
US5984630A (en) * | 1997-12-24 | 1999-11-16 | General Electric Company | Reduced windage high pressure turbine forward outer seal |
DE19931765A1 (de) | 1999-07-08 | 2001-01-11 | Rolls Royce Deutschland | Zweistufige oder mehrstufige Axialturbine einer Gasturbine |
US6610416B2 (en) * | 2001-04-26 | 2003-08-26 | General Electric Company | Material treatment for reduced cutting energy and improved temperature capability of honeycomb seals |
US6769865B2 (en) * | 2002-03-22 | 2004-08-03 | General Electric Company | Band cooled turbine nozzle |
GB0218060D0 (en) * | 2002-08-03 | 2002-09-11 | Alstom Switzerland Ltd | Sealing arrangements |
US6969239B2 (en) * | 2002-09-30 | 2005-11-29 | General Electric Company | Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine |
FR2867223B1 (fr) * | 2004-03-03 | 2006-07-28 | Snecma Moteurs | Turbomachine comme par exemple un turboreacteur pour avion |
GB0412476D0 (en) * | 2004-06-04 | 2004-07-07 | Rolls Royce Plc | Seal system |
GB0424883D0 (en) * | 2004-11-11 | 2004-12-15 | Rolls Royce Plc | Seal structure |
US7287956B2 (en) * | 2004-12-22 | 2007-10-30 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
GB0613715D0 (en) * | 2006-07-11 | 2006-08-23 | Rolls Royce Plc | A seal between relatively moveable members |
GB0722511D0 (en) * | 2007-11-19 | 2007-12-27 | Rolls Royce Plc | Turbine arrangement |
-
2003
- 2003-10-17 DE DE2003148290 patent/DE10348290A1/de not_active Ceased
-
2004
- 2004-09-30 WO PCT/DE2004/002174 patent/WO2005040561A1/de active Application Filing
- 2004-09-30 US US10/576,035 patent/US9011083B2/en not_active Expired - Fee Related
- 2004-09-30 EP EP04786886A patent/EP1673519B1/de not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2005040561A1 * |
Also Published As
Publication number | Publication date |
---|---|
US9011083B2 (en) | 2015-04-21 |
WO2005040561A1 (de) | 2005-05-06 |
US20070274825A1 (en) | 2007-11-29 |
EP1673519B1 (de) | 2012-08-29 |
DE10348290A1 (de) | 2005-05-12 |
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