EP0899426A2 - Aube de guidage pour turbines à gaz - Google Patents

Aube de guidage pour turbines à gaz Download PDF

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Publication number
EP0899426A2
EP0899426A2 EP98114445A EP98114445A EP0899426A2 EP 0899426 A2 EP0899426 A2 EP 0899426A2 EP 98114445 A EP98114445 A EP 98114445A EP 98114445 A EP98114445 A EP 98114445A EP 0899426 A2 EP0899426 A2 EP 0899426A2
Authority
EP
European Patent Office
Prior art keywords
guide vane
projection
face
platform
guide
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
EP98114445A
Other languages
German (de)
English (en)
Other versions
EP0899426A3 (fr
EP0899426B1 (fr
Inventor
Rudolf Stanka
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 Motoren und Turbinen Union Muenchen GmbH
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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0899426A2 publication Critical patent/EP0899426A2/fr
Publication of EP0899426A3 publication Critical patent/EP0899426A3/fr
Application granted granted Critical
Publication of EP0899426B1 publication Critical patent/EP0899426B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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

Definitions

  • the invention relates to a guide vane for a gas turbine, in particular a low-pressure turbine, with an airfoil located between an inner platform and an outer platform extends, the outer platform fastening means for attachment to a housing has, a guide vane segment from at least three guide vanes and a vane assembly.
  • Guide vanes of low pressure turbines are made of metal and are in the development phase generally first soldered together into segments of three or six guide vanes.
  • the guide vanes are on their outer platforms in a (engine) housing attached and releasably together on their inner platforms by metal clips or the like tense.
  • the vibration behavior is due to the tension on the inner platforms the blades are improved.
  • the use of the braces as an additional Components have the disadvantage of more complex assembly and higher costs.
  • guide vanes made of mostly carbon fiber reinforced plastics are used and in so-called aerodynamic Cold "test benches are examined.
  • Such guide vanes are considerably faster and less expensive to produce than corresponding guide vanes made of metal and are therefore used with preference in the preceding investigations.
  • the guide vanes made of plastic are used at considerably lower temperatures (approx. 130 ° C.) than in the real one Operation, however, loaded with gas forces of the same order of magnitude as in the real engine.
  • the problem here is the geometry of the outer and inner platform of the guide vanes Metal to take over for those made of plastic, as these can withstand the high, real Unable to withstand gas forces. Gluing three or six guide vanes each to individual guide vane segments from which the guide ring assembly is formed Problem solved just as little as the tensioning of the guide vanes by means of bolts which are in the lateral end faces of the outer and inner platforms are provided. The vibration amplitudes were too large and caused the guide vanes to break.
  • the invention has for its object a guide vane of the type described above to create, which has an improved dynamic vibration behavior, the Vibration amplitude of adjacent guide vanes is limited and easy to manufacture and is inexpensive to manufacture.
  • the solution to the problem is characterized in that at least one a protrusion from the outer or inner platform on a first side face has with the protruding side surface and on a second, opposite, lateral End face a receptacle for positively receiving a projection of an adjacent one Has guide vane, the dimensions of which are so matched to the projection that align the inner and outer platforms of adjacent guide vanes when assembled.
  • Adjacent vanes of adjacent vane segments e.g. from three interconnected guide vanes
  • Adjacent vanes of adjacent vane segments with a positive fit in the axial direction are coupled together and a damping effect due to the friction on the contact surfaces arises.
  • the projections seal between the Platforms occurring columns.
  • the side surface of the projection is perpendicular to first, generally radial end face of the outer or inner Platform.
  • the side surface of the protrusion therefore runs strongly through the gas flow loaded circumferential direction and allows damping due to friction on the Contact areas.
  • the side surface of the protrusion is preferably at least 3 mm above the first end surface the outer or inner platform, so that a sufficiently large friction or contact surface with the inclusion of an adjacent guide vane.
  • the protrusion is at least 30% of the (cross-sectional) area of the first End face, so that the adjacent guide vanes do not just point to one another are coupled and a reliable limitation of the vibration amplitude is made possible.
  • the projection with play in the exception of the neighboring one The guide vane sits or is fitted so that, for example, adjoining guide vanes Adjacent vane segments easily move away from each other due to thermal expansion and can move towards each other.
  • an inner surface of the receptacle adjoining the second end surface runs in the assembled state parallel to the side surface of the projection, so that a secure friction contact guaranteed between the inner surface of the receptacle and the side surface of the projection is.
  • the outer platform include a platform and a stiffening wall which are connected by cross struts running at a distance from one another and / or the inner one Platform includes a platform and a reinforcement wall.
  • This will make the torsion and Flexural rigidity of the inner platform and in particular that of the platform, the stiffening wall as well as the two cross struts existing outer platform, which also with the Fastening means for attaching the guide blade to the engine housing is provided, clearly increased. Thanks to this geometric measure, the guide vane also lasts when in use comparatively weaker materials, e.g. fiber-reinforced plastic, the proportionately high real gas forces.
  • the guide vane is formed in one piece, so that it is inexpensive can be made by metal or injection molding.
  • the guide vane is made of carbon fiber reinforced plastic, so that it is aerodynamic Cold "test benches can be examined. This enables test data for the calibration of aerodynamic design methods to be determined significantly faster and more cost-effectively than is the case when using guide vanes made of metal.
  • Such test guide vanes made of plastic can also be glued to guide vane segments consisting of three or six guide vanes
  • the side surface of the projection offers adhesive surfaces which, in contrast to the first and second end surfaces of the outer and inner platforms, are not subjected to tensile / compressive stress, but rather to shear, which is the significantly more favorable form of stress for adhesive bonds.
  • FIG. 1 shows an exemplary embodiment of the guide vane according to the invention, designated by 1, which consists of carbon fiber-reinforced plastic and is produced by the injection molding process. Such a guide vane 1 is so-called. Aerodynamic Cold "test benches are used to quickly and inexpensively determine test data from pressure, speed and flow field measurements for the calibration of aerodynamic design processes.
  • the guide vane 1 comprises an airfoil 2, an outer platform 3 from a platform 3 'and a spaced stiffening wall 4 and an inner platform 5 from one Platform 5 'and an associated and also extending at a distance from it Reinforcement wall 6. Both the outer and the inner platform 3 and 5 is on one first end face 7 is provided with a projection 8, each of which over the first end face 7 has side surface 9 projecting by approximately 3 mm.
  • Fig. 2 shows the guide vane 1 of Fig. 1 in a side view, in which the substantially parallel to the (outer) platform 3 'stiffening wall 4 and with the (inner) platform 5 'connected reinforcement wall 6, which extends over several corners are.
  • On the outer platform 3 are two hook-like fasteners 10 for attachment the guide vane 1 is formed on an engine housing (not shown).
  • Each cavity forms a receptacle 12 with which the second end face 13 of the outer and inner platform 3 and 5 is provided.
  • a Projection 8 of an adjacent guide vane 1 is positively received in this receptacle 12, the dimensions of which are matched to those of the projection 8 so that the outer and inner platforms 3 and 5 adjacent guide vanes 1 in the assembled state aligned, as can be seen in FIGS. 4 and 5.
  • the receptacle 12 has one to the second End face 13 adjacent inner surface 14, which in the assembled state due to the coordinated Dimensioning of the projection 8 and the receptacle 12 a contact surface with the Side surface 9 of the projection 8 forms. This also creates a seal between neighboring vanes 1 achieved.
  • Fig. 2 it can be seen that the projection 8 and the Image 12 more than 50% of the cross-sectional area of the first or Make out the second end face 7 or 13.
  • FIG. 3 shows a single guide vane 1 vibrating in the axial direction, two different ones Vibration states are shown.
  • the vibration is damped by the occurring between the inner surfaces 14 of the receptacle 12 and the side surface 9 of the projection 8 Friction.
  • FIG. 4 shows a guide vane segment 15 consisting of three guide vanes 1.
  • Such guide vane segments from which a ring-shaped vane assembly is formed, serve for reinforcement of the individual guide vanes 1.
  • the guide vanes 1 made of plastic become not only by the form fit between the projection 8 and the receptacle 12 adjacent Guide vanes 1 and the friction present in the contact surface are connected to one another, but additionally at least on the side surface 9 of the projection 8 or the inner surface 14 of the receptacle 12 glued together.
  • the guide vanes 1 can also their first and second end faces 7 and 13 may be glued together.
  • the adhesive connection between the side surface 9 of the projection 8 and the inner surface 14 of the receptacle 12 stressed under shear stresses during operation and is therefore clear more resilient than a bonded connection between the first and second end face 7 or 13.
  • a plurality of guide vane segments 15 are used to form an annular guide ring assembly assembled, whereby these do not stick together to compensate for thermal expansion, but only by the positive connection between the projection 8 and the receptacle 12 are coupled to each other.
  • the positive locking effect is caused by the between the side surface 9 of the projection 8 and the inner surface 14 of the receptacle 12 friction occurring Damping effect and thus an improvement in the dynamic vibration behavior of the Guide vane 1.
  • the above-described limitation occurs due to the positive locking the vibration amplitude and sealing the gaps between adjacent vane segments.
  • each guide vane 1 of a guide vane segment 15 is in the stiffening wall 4 outer platform 3, a hole provided a hole 16 is provided, in which a (not shown) engages bolts on the housing and the guide vane against gas / flow forces is supported in the circumferential direction.
  • the stiffening wall 4 locally thickened around the bore 16 to reduce the surface pressure.
  • the hole 16 is designed in the axial direction of the engine arrangement as an elongated hole, so that the gas or Flow forces in the axial direction via the rear, hook-like fastening means in the illustration 11 and not through the bolt into the engine housing.
  • FIG. 5 shows the guide vane segment 15 from FIG. 4 in a perspective view, in which the Profile of the blades 2 can be seen. It can also be seen that the Dimensioning of the projection 8 and the receptacle 12 are coordinated so that align the outer and inner platforms 3 and 5 when assembled.
  • the left part of the 5 shows the projections 8 on the outer and inner platforms 3, 5, that in a receptacle 12 of a guide vane 1 of an adjacent guide vane segment 15 is positively received within a lead ring assembly, but is not glued.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP98114445A 1997-08-23 1998-08-01 Aube de guidage pour turbines à gaz Expired - Lifetime EP0899426B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE29715180U 1997-08-23
DE29715180U DE29715180U1 (de) 1997-08-23 1997-08-23 Leitschaufel für eine Gasturbine

Publications (3)

Publication Number Publication Date
EP0899426A2 true EP0899426A2 (fr) 1999-03-03
EP0899426A3 EP0899426A3 (fr) 1999-12-08
EP0899426B1 EP0899426B1 (fr) 2003-04-02

Family

ID=8045040

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98114445A Expired - Lifetime EP0899426B1 (fr) 1997-08-23 1998-08-01 Aube de guidage pour turbines à gaz

Country Status (4)

Country Link
US (1) US6217282B1 (fr)
EP (1) EP0899426B1 (fr)
JP (1) JPH11107704A (fr)
DE (2) DE29715180U1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1219783A3 (fr) * 2000-12-28 2004-02-11 ALSTOM (Switzerland) Ltd Aube statorique pour une turbine axiale
EP2295724A1 (fr) * 2009-08-28 2011-03-16 Siemens Aktiengesellschaft Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques
WO2012041651A1 (fr) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant
EP2617945A1 (fr) * 2012-01-23 2013-07-24 MTU Aero Engines GmbH Rotor pour une turbomachine
ITCO20130004A1 (it) * 2013-02-20 2014-08-21 Nuovo Pignone Srl Metodo per realizzare una girante da segmenti a settore
EP3339608A3 (fr) * 2012-08-27 2018-09-05 United Technologies Corporation Stator en porte-à-faux à feuillure
WO2023247857A1 (fr) * 2022-06-22 2023-12-28 Safran Aircraft Engines Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes

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US6435813B1 (en) * 2000-05-10 2002-08-20 General Electric Company Impigement cooled airfoil
DE10111896B8 (de) * 2001-03-13 2012-06-06 Eads Space Transportation Gmbh Metallischer Ring für die Verbindung zweier rotationssymmetrischer Strukturteile
ATE363018T1 (de) * 2002-08-14 2007-06-15 Volvo Aero Corp Verfahren zur herstellung einer statorkomponente
US7597542B2 (en) * 2005-08-30 2009-10-06 General Electric Company Methods and apparatus for controlling contact within stator assemblies
US7594404B2 (en) * 2006-07-27 2009-09-29 United Technologies Corporation Embedded mount for mid-turbine frame
US8257038B2 (en) * 2008-02-01 2012-09-04 Siemens Energy, Inc. Metal injection joining
US8043044B2 (en) * 2008-09-11 2011-10-25 General Electric Company Load pin for compressor square base stator and method of use
US20100068050A1 (en) * 2008-09-12 2010-03-18 General Electric Company Gas turbine vane attachment
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US8360716B2 (en) * 2010-03-23 2013-01-29 United Technologies Corporation Nozzle segment with reduced weight flange
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
FR2961554B1 (fr) * 2010-06-18 2012-07-20 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine, redresseur de turbomachine et turbomachine comprenant un tel secteur
JP5358559B2 (ja) * 2010-12-28 2013-12-04 株式会社日立製作所 軸流圧縮機
US8784037B2 (en) 2011-08-31 2014-07-22 Pratt & Whitney Canada Corp. Turbine shroud segment with integrated impingement plate
US8784041B2 (en) 2011-08-31 2014-07-22 Pratt & Whitney Canada Corp. Turbine shroud segment with integrated seal
US9028744B2 (en) 2011-08-31 2015-05-12 Pratt & Whitney Canada Corp. Manufacturing of turbine shroud segment with internal cooling passages
US9079245B2 (en) 2011-08-31 2015-07-14 Pratt & Whitney Canada Corp. Turbine shroud segment with inter-segment overlap
US8784044B2 (en) 2011-08-31 2014-07-22 Pratt & Whitney Canada Corp. Turbine shroud segment
EP2666969B1 (fr) * 2012-05-21 2017-04-19 General Electric Technology GmbH Structure de diaphragme de turbine
EP2669477B1 (fr) * 2012-05-31 2017-04-05 General Electric Technology GmbH Carénage pour aubes
US9556746B2 (en) * 2013-10-08 2017-01-31 Pratt & Whitney Canada Corp. Integrated strut and turbine vane nozzle arrangement
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
US10018075B2 (en) 2015-04-22 2018-07-10 General Electric Company Methods for positioning neighboring nozzles of a gas turbine engine
JP6763157B2 (ja) * 2016-03-11 2020-09-30 株式会社Ihi タービンノズル
WO2017158637A1 (fr) * 2016-03-15 2017-09-21 株式会社 東芝 Turbine et aube de stator de turbine
GB2551164B (en) * 2016-06-08 2019-12-25 Rolls Royce Plc Metallic stator vane
US10570773B2 (en) 2017-12-13 2020-02-25 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10502093B2 (en) * 2017-12-13 2019-12-10 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10533454B2 (en) 2017-12-13 2020-01-14 Pratt & Whitney Canada Corp. Turbine shroud cooling
US11274569B2 (en) 2017-12-13 2022-03-15 Pratt & Whitney Canada Corp. Turbine shroud cooling
US10738634B2 (en) * 2018-07-19 2020-08-11 Raytheon Technologies Corporation Contact coupled singlets
JP2021143658A (ja) * 2020-03-13 2021-09-24 東芝エネルギーシステムズ株式会社 タービン静翼
US11365645B2 (en) 2020-10-07 2022-06-21 Pratt & Whitney Canada Corp. Turbine shroud cooling
US12037912B2 (en) 2021-06-18 2024-07-16 Rtx Corporation Advanced passive clearance control (APCC) control ring produced by field assisted sintering technology (FAST)
US20230147399A1 (en) * 2021-06-18 2023-05-11 Raytheon Technologies Corporation Joining individual turbine vanes with field assisted sintering technology (fast)

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DE485833C (de) * 1929-11-08 J A Maffei A G Verfahren zur Herstellung von Schauflungen fuer Turbomaschinen, insbesondere fuer Dampf- oder Gasturbinen
US2801076A (en) * 1952-11-18 1957-07-30 Parsons & Marine Eng Turbine Turbine nozzles
GB918692A (en) * 1958-07-11 1963-02-13 Ass Elect Ind Improvements relating to turbine nozzle blocks
EP0654586A1 (fr) * 1993-11-19 1995-05-24 United Technologies Corporation Arrangement des aubes statoriques

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CH488928A (de) * 1968-03-22 1970-04-15 Sulzer Ag Leitschaufelbefestigung in Turbomaschinen
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Publication number Priority date Publication date Assignee Title
DE485833C (de) * 1929-11-08 J A Maffei A G Verfahren zur Herstellung von Schauflungen fuer Turbomaschinen, insbesondere fuer Dampf- oder Gasturbinen
US2801076A (en) * 1952-11-18 1957-07-30 Parsons & Marine Eng Turbine Turbine nozzles
GB918692A (en) * 1958-07-11 1963-02-13 Ass Elect Ind Improvements relating to turbine nozzle blocks
EP0654586A1 (fr) * 1993-11-19 1995-05-24 United Technologies Corporation Arrangement des aubes statoriques

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1219783A3 (fr) * 2000-12-28 2004-02-11 ALSTOM (Switzerland) Ltd Aube statorique pour une turbine axiale
EP2295724A1 (fr) * 2009-08-28 2011-03-16 Siemens Aktiengesellschaft Aube statorique pour une turbomachine à flux axial et agencement associé d'aubes statoriques
CN102003219A (zh) * 2009-08-28 2011-04-06 西门子公司 可轴向通流的涡轮机的导向叶片及其导向叶片装置
CN102003219B (zh) * 2009-08-28 2013-12-18 西门子公司 可轴向通流的涡轮机的导向叶片及其导向叶片装置
US8622708B2 (en) 2009-08-28 2014-01-07 Siemens Aktiengesellschaft Stator blade for a turbomachine which is exposable to axial throughflow, and also stator blade arrangement for it
WO2012041651A1 (fr) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant
CN103119249A (zh) * 2010-09-30 2013-05-22 西门子公司 叶片环扇段、流体机械及其制造方法
US9657581B2 (en) 2012-01-23 2017-05-23 Mtu Aero Engines Gmbh Rotor for a turbomachine
EP2617945A1 (fr) * 2012-01-23 2013-07-24 MTU Aero Engines GmbH Rotor pour une turbomachine
US10309235B2 (en) 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator
EP3339608A3 (fr) * 2012-08-27 2018-09-05 United Technologies Corporation Stator en porte-à-faux à feuillure
ITCO20130004A1 (it) * 2013-02-20 2014-08-21 Nuovo Pignone Srl Metodo per realizzare una girante da segmenti a settore
US9945388B2 (en) 2013-02-20 2018-04-17 Nuovo Pignone Srl Method for making an impeller from sector segments
RU2661690C2 (ru) * 2013-02-20 2018-07-19 Нуово Пиньоне СРЛ Способ изготовления рабочего колеса из секторальных сегментов
CN105209208A (zh) * 2013-02-20 2015-12-30 诺沃皮尼奥内股份有限公司 用于从用扇形节段制造叶轮的方法
WO2014128169A1 (fr) * 2013-02-20 2014-08-28 Nuovo Pignone Srl Procédé de fabrication d'un impulseur à partir de segments de secteur
WO2023247857A1 (fr) * 2022-06-22 2023-12-28 Safran Aircraft Engines Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes
FR3137120A1 (fr) * 2022-06-22 2023-12-29 Safran Aircraft Engines Ensemble aubagé de turbomachine comportant des moyens de limitations de vibrations entre plateformes

Also Published As

Publication number Publication date
JPH11107704A (ja) 1999-04-20
DE59807705D1 (de) 2003-05-08
EP0899426A3 (fr) 1999-12-08
DE29715180U1 (de) 1997-10-16
US6217282B1 (en) 2001-04-17
EP0899426B1 (fr) 2003-04-02

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