EP0899426A2 - Aube de guidage pour turbines à gaz - Google Patents
Aube de guidage pour turbines à gaz Download PDFInfo
- 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
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
- 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)
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)
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 |
Families Citing this family (35)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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) |
Citations (4)
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 |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3442442A (en) * | 1966-12-02 | 1969-05-06 | Gen Electric | Mounting of blades in an axial flow compressor |
CH488928A (de) * | 1968-03-22 | 1970-04-15 | Sulzer Ag | Leitschaufelbefestigung in Turbomaschinen |
US4832568A (en) * | 1982-02-26 | 1989-05-23 | General Electric Company | Turbomachine airfoil mounting assembly |
US5848874A (en) * | 1997-05-13 | 1998-12-15 | United Technologies Corporation | Gas turbine stator vane assembly |
-
1997
- 1997-08-23 DE DE29715180U patent/DE29715180U1/de not_active Expired - Lifetime
-
1998
- 1998-08-01 EP EP98114445A patent/EP0899426B1/fr not_active Expired - Lifetime
- 1998-08-01 DE DE59807705T patent/DE59807705D1/de not_active Expired - Fee Related
- 1998-08-06 JP JP10223253A patent/JPH11107704A/ja active Pending
- 1998-08-24 US US09/138,983 patent/US6217282B1/en not_active Expired - Fee Related
Patent Citations (4)
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)
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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