EP1462616A2 - Anordnung für das axiale und radiale Festlegen eines Vane-Klusters in dem Gehäuse eines Turbinentriebwerkes - Google Patents
Anordnung für das axiale und radiale Festlegen eines Vane-Klusters in dem Gehäuse eines Turbinentriebwerkes Download PDFInfo
- Publication number
- EP1462616A2 EP1462616A2 EP04002392A EP04002392A EP1462616A2 EP 1462616 A2 EP1462616 A2 EP 1462616A2 EP 04002392 A EP04002392 A EP 04002392A EP 04002392 A EP04002392 A EP 04002392A EP 1462616 A2 EP1462616 A2 EP 1462616A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide vane
- housing
- shaped
- assembly
- axial
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- 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
- F05D2250/23—Three-dimensional prismatic
- F05D2250/232—Three-dimensional prismatic conical
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the invention relates to an arrangement for the axial and radial fixing of a guide vane assembly in the housing of a turbine engine with a locking ring, which in a corresponding radial groove engages in the facing wall of the housing and is secured against radial evasion by means of a locking element.
- vane clusters It is known as vane clusters called vane assemblies as a unit from behind to be inserted into the housing of a turbine engine and inserted into the Position by means of piston rings similar to circlips, which are provided for this purpose Corresponding grooves are inserted in the inserted position.
- the retaining rings themselves are replaced by a subsequent component, usually by an as Liner designated turbine belt segment locked, which the radial sliding out of the Circlip prevented from the assigned groove.
- the subsequent turbine shroud segment must be designed such that it can overlap the guide vane assembly by means of a hook-shaped rear edge.
- This object is achieved according to the invention using a locking ring in that that the locking ring is approximately L-shaped in cross section, the longer one Leg engages in the radial groove of the wall of the housing and its short leg a hook-shaped projection on the respective blade head of the guide blades of the guide blade group engages behind, as well as by means of a subsequent turbine shroud segment attached clamp held on the short leg held in its secure position is.
- the inventive solution does not require any axial webs to accommodate the otherwise common locking pins still a large length to accommodate the thermal axial Tolerances and thus avoids relatively high axial space requirements.
- the invention is based on a more or less schematic in the drawing illustrated embodiment described.
- FIG. 1 From an axially and radially immovable held in the housing of a turbine engine Guide vane assembly in FIG. 1 is only a guide vane 10 with its head part 11 and the associated inner region of the housing 14 of such an arrangement according to the State of the art shown. With this arrangement, the vane assembly is fixed via a locking ring 15. For this purpose, there is a groove 18 in the housing 14 for receiving the locking ring 15 is provided, on which a flange-like extension 19 of the Bucket head 11 abuts. The extension has an opening 20 into which a corresponding one flange-like extension 21 of the housing 14 secured securing pin 23 in order to prevent the guide vane assembly from slipping radially out with bearing play intervenes.
- the locking ring is locked radially by means of a Inner circumferential surface of the locking ring cam 25, which on the facing Front side of the downstream downstream assembly 26 of the Turbine engine is attached.
- the upstream end of the blade head 11 engages with an extension 27 into an associated recess 28 of the housing 14.
- a locking ring is also provided there, which is designated by the reference number 30 is and in contrast to the known circlips an L-shaped cross section having.
- the securing ring 30 engages with its long leg 32 in the housing 14 provided groove 18 a.
- the short leg 33 encompasses a suitably trained one short hook-shaped extension 34 on the blade head 11 of the associated guide blade 10 of the guide vane assembly to be held and forms with its end face 35 Contact surface for the circlip 30.
- a U-shaped bracket 36 is provided, which at the front end 24 of the following Assembly 26 of the turbine engine is attached and with its free leg 38 engaging under the short leg 33 of the retaining ring 30.
- the U-shaped Bracket 36 is, as described in connection with FIG. 2, with the facing End 24 of the following downstream bow section 26, which is referred to as liner, is firmly connected and engages in the recess 29 in the housing 14.
- the locking ring 30 and thus the guide vane assembly are radial and axially in their predetermined position in the housing 14 of the turbine engine, not shown kept immovable.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- Fig. 1
- das Konzept einer Anordnung zur Sicherung einer Leitschaufelbaugruppe eines Turbinentriebwerkes in dem diese lagernden Gehäuse mit Hilfe eines mittels Stifte festgelegten Sicherungsringes, teilweise im Schnitt dargestellt, nach dem Stande der Technik,
- Fig. 2
- eine abgewandelte Ausführungsform einer Anordnung nach dem Stande der Technik, bei der das Festlegen des Sicherungsringes mittels einer am nachfolgenden Turbinendeckband befindlichen Klammer erfolgt und
- Fig. 3
- die Ausbildung einer Anordnung zur Sicherung einer Leitschaufelbaugruppe eines Turbinentriebwerkes in dem diese lagernden Gehäuse gemäß der Erfindung.
- 10
- Leitschaufel
- 11
- Schaufelkopf
- 14
- Gehäuse
- 15
- Sicherungsring
- 16
- Schenkel
- 17
- Fortsatz
- 18
- Nut im Gehäuse
- 19
- Fortsatz
- 20
- Öffnung
- 21
- Fortsatz
- 23
- Sicherungsstift, U-förmige Klammer
- 24
- Ende der nachfolgenden Baugruppe
- 25
- Nocken
- 26
- Turbinenbandsegment
- 27
- Fortsatz
- 28
- Ausnehmung im Gehäuse
- 29
- Ausnehmung im Gehäuse
- 30
- Sicherungsring
- 32
- langer Schenkel
- 33
- kurzer Schenkel
- 34
- hakenförmiger Vorsprung
- 35
- Stirnseite des Vorsprunges
- 36
- U-förmige Klammer
- 38
- freier Schenkel der Klammer 36
- 39
- zweiter Schenkel der Klammer 36
Claims (3)
- Anordnung für das axiale und radiale Festlegen einer Leitschaufelgruppe in dem Gehäuse eines Turbinentriebwerkes mit einem kolbenringförmigen Sicherungsring, der in eine korrespondierende radiale Nut in der zugewandten Wandung des Gehäuses eingreift und mittels eines Verriegelungselementes gegen radiales Ausweichen gesichert ist, dadurch gekennzeichnet, dass der Sicherungsring (30) im Querschnitt etwa L-förmig ausgebildet ist, dessen langer Schenkel (32) in die radiale Nut (18) der Wandung des Gehäuses (14) eingreift und dessen kurzer Schenkel (33) einen hakenförmigen Vorsprung (34) am Schaufelkopf (11) jeder Leitschaufel der Leitschaufelbaugruppe hintergreift sowie mittels einer am nachfolgenden Turbinenbandsegment (26) befestigten am kurzen Schenkel (33) anliegenden U-förmigen Klammer (36) in seiner Sicherungslage gehalten ist.
- Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass die Stirnseite des hakenförmigen Vorsprunges (34) die die axiale Lage der Leitschaufelbaugruppe bestimmende Anschlagfläche (35) für den Sicherungsring (30) bildet.
- Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass der mit dem stirnseitigen Ende der nachfolgenden Baugruppe (Liner 26) verbundene Schenkel (39) der U-förmigen Klammer (36) in eine Ausnehmung (29) des Gehäuses (14) des Turbinentriebwerkes eingreift.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2003112956 DE10312956B4 (de) | 2003-03-22 | 2003-03-22 | Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes |
DE10312956 | 2003-03-22 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1462616A2 true EP1462616A2 (de) | 2004-09-29 |
EP1462616A3 EP1462616A3 (de) | 2009-09-30 |
EP1462616B1 EP1462616B1 (de) | 2011-06-15 |
Family
ID=32798061
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20040002392 Expired - Fee Related EP1462616B1 (de) | 2003-03-22 | 2004-02-04 | Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP1462616B1 (de) |
DE (1) | DE10312956B4 (de) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2923526A1 (fr) * | 2007-11-13 | 2009-05-15 | Snecma Sa | Etage de turbine ou de compresseur de turbomachine |
CN101460709B (zh) * | 2006-04-06 | 2011-11-02 | 西门子公司 | 热涡轮机的导向叶片段、相应的制造方法及热涡轮机 |
FR2960591A1 (fr) * | 2010-06-01 | 2011-12-02 | Snecma | Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation |
FR2985792A1 (fr) * | 2012-01-18 | 2013-07-19 | Snecma | Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine |
WO2013156734A1 (fr) * | 2012-04-20 | 2013-10-24 | Snecma | Etage de turbine pour une turbomachine |
EP2787178A1 (de) | 2013-04-03 | 2014-10-08 | MTU Aero Engines GmbH | Leitschaufelanordnung |
DE102016203567A1 (de) * | 2016-03-04 | 2017-09-07 | Siemens Aktiengesellschaft | Strömungsmaschine mit mehreren Leitschaufelstufen und Verfahren zur teilweisen Demontage einer solchen Strömungsmaschine |
EP3000990B1 (de) | 2014-09-26 | 2019-05-29 | Rolls-Royce plc | Halter einer turbinenummantelung |
FR3083820A1 (fr) * | 2018-07-11 | 2020-01-17 | Safran Aircraft Engines | Dispositif de maintien ameliore pour distributeur de turbomachine |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102014209057A1 (de) | 2014-05-14 | 2015-11-19 | MTU Aero Engines AG | Gasturbinengehäuseanordnung |
DE102020201448A1 (de) | 2020-02-06 | 2021-08-12 | Siemens Aktiengesellschaft | Additiv hergestellte Turbinenschaufel mit Verdrehsicherung und Justageverfahren |
CN112177689A (zh) * | 2020-09-29 | 2021-01-05 | 中国航发湖南动力机械研究所 | 发动机的涡轮导向器定位结构和发动机 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5848854A (en) * | 1995-11-30 | 1998-12-15 | General Electric Company | Turbine nozzle retainer assembly |
US20020197153A1 (en) * | 2001-06-25 | 2002-12-26 | Rogers Mark John | Segmented turbine vane support structure |
US6537022B1 (en) * | 2001-10-05 | 2003-03-25 | General Electric Company | Nozzle lock for gas turbine engines |
EP1505259A1 (de) * | 2003-08-08 | 2005-02-09 | ROLLS-ROYCE plc | Vorrichtung zur Befestigung einer nicht-rotierenden Komponente einer Gasturbine |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6435820B1 (en) * | 1999-08-25 | 2002-08-20 | General Electric Company | Shroud assembly having C-clip retainer |
-
2003
- 2003-03-22 DE DE2003112956 patent/DE10312956B4/de not_active Expired - Fee Related
-
2004
- 2004-02-04 EP EP20040002392 patent/EP1462616B1/de not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5848854A (en) * | 1995-11-30 | 1998-12-15 | General Electric Company | Turbine nozzle retainer assembly |
US20020197153A1 (en) * | 2001-06-25 | 2002-12-26 | Rogers Mark John | Segmented turbine vane support structure |
US6537022B1 (en) * | 2001-10-05 | 2003-03-25 | General Electric Company | Nozzle lock for gas turbine engines |
EP1505259A1 (de) * | 2003-08-08 | 2005-02-09 | ROLLS-ROYCE plc | Vorrichtung zur Befestigung einer nicht-rotierenden Komponente einer Gasturbine |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101460709B (zh) * | 2006-04-06 | 2011-11-02 | 西门子公司 | 热涡轮机的导向叶片段、相应的制造方法及热涡轮机 |
US8128357B2 (en) | 2006-04-06 | 2012-03-06 | Siemens Aktiengesellschaft | Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine |
FR2923526A1 (fr) * | 2007-11-13 | 2009-05-15 | Snecma Sa | Etage de turbine ou de compresseur de turbomachine |
EP2060744A1 (de) * | 2007-11-13 | 2009-05-20 | Snecma | Turbinen- oder Kompressorstufe eines Turbotriebwerks |
US8277179B2 (en) | 2007-11-13 | 2012-10-02 | Snecma | Turbine or compressor stage for a turbomachine |
FR2960591A1 (fr) * | 2010-06-01 | 2011-12-02 | Snecma | Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation |
WO2011151596A1 (fr) * | 2010-06-01 | 2011-12-08 | Snecma | Turbomachine avec un dispositif pour caler en rotation un segment de distributeur dans un carter; pion antirotation |
CN102918230A (zh) * | 2010-06-01 | 2013-02-06 | 斯奈克玛 | 带有用于防止喷嘴导流叶片组件的扇段在壳体内旋转的装置的涡轮机;防旋转栓 |
US20130078086A1 (en) * | 2010-06-01 | 2013-03-28 | Snecma | Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg |
US9562441B2 (en) | 2010-06-01 | 2017-02-07 | Snecma | Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg |
CN102918230B (zh) * | 2010-06-01 | 2015-08-26 | 斯奈克玛 | 带有用于防止喷嘴导流叶片组件的扇段在壳体内旋转的装置的涡轮机;防旋转栓 |
RU2558174C2 (ru) * | 2010-06-01 | 2015-07-27 | Снекма | Газотурбинный двигатель с устройством для блокировки вращения сегмента направляющего аппарата в картере и блокировочный штифт, препятствующий вращению |
GB2513754A (en) * | 2012-01-18 | 2014-11-05 | Snecma | Angular downstream guide vane sector with vibration damping by means of a wedge for a turbine engine compressor |
WO2013107967A1 (fr) * | 2012-01-18 | 2013-07-25 | Snecma | Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine |
GB2513754B (en) * | 2012-01-18 | 2017-11-22 | Snecma | An angular diffuser sector for a turbine engine compressor, with a vibration damper wedge |
US9709072B2 (en) | 2012-01-18 | 2017-07-18 | Snecma | Angular diffuser sector for a turbine engine compressor, with a vibration damper wedge |
FR2985792A1 (fr) * | 2012-01-18 | 2013-07-19 | Snecma | Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine |
WO2013156734A1 (fr) * | 2012-04-20 | 2013-10-24 | Snecma | Etage de turbine pour une turbomachine |
CN104246141B (zh) * | 2012-04-20 | 2016-08-24 | 斯奈克玛 | 用于涡轮引擎的涡轮级以及包括该涡轮级的涡轮引擎 |
JP2015514907A (ja) * | 2012-04-20 | 2015-05-21 | スネクマ | タービンエンジン用タービン段 |
CN104246141A (zh) * | 2012-04-20 | 2014-12-24 | 斯奈克玛 | 用于涡轮引擎的涡轮级 |
RU2633316C2 (ru) * | 2012-04-20 | 2017-10-11 | Снекма | Ступень турбины турбомашины и турбомашина |
FR2989724A1 (fr) * | 2012-04-20 | 2013-10-25 | Snecma | Etage de turbine pour une turbomachine |
US9957841B2 (en) | 2012-04-20 | 2018-05-01 | Snecma | Turbine stage for a turbine engine |
EP2787178A1 (de) | 2013-04-03 | 2014-10-08 | MTU Aero Engines GmbH | Leitschaufelanordnung |
EP3000990B1 (de) | 2014-09-26 | 2019-05-29 | Rolls-Royce plc | Halter einer turbinenummantelung |
DE102016203567A1 (de) * | 2016-03-04 | 2017-09-07 | Siemens Aktiengesellschaft | Strömungsmaschine mit mehreren Leitschaufelstufen und Verfahren zur teilweisen Demontage einer solchen Strömungsmaschine |
US10844747B2 (en) | 2016-03-04 | 2020-11-24 | Siemens Aktiengesellschaft | Continuous flow machine having multiple guide vane stages and method for partially disassembling a continuous flow machine of this type |
FR3083820A1 (fr) * | 2018-07-11 | 2020-01-17 | Safran Aircraft Engines | Dispositif de maintien ameliore pour distributeur de turbomachine |
Also Published As
Publication number | Publication date |
---|---|
DE10312956B4 (de) | 2011-08-11 |
DE10312956A1 (de) | 2004-09-30 |
EP1462616B1 (de) | 2011-06-15 |
EP1462616A3 (de) | 2009-09-30 |
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