EP0899426B1 - Leitschaufel für eine Gasturbine - Google Patents
Leitschaufel für eine Gasturbine Download PDFInfo
- Publication number
- EP0899426B1 EP0899426B1 EP98114445A EP98114445A EP0899426B1 EP 0899426 B1 EP0899426 B1 EP 0899426B1 EP 98114445 A EP98114445 A EP 98114445A EP 98114445 A EP98114445 A EP 98114445A EP 0899426 B1 EP0899426 B1 EP 0899426B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide vane
- guide
- platform
- face
- projection
- 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.)
- Expired - Lifetime
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 that sits between an inner platform and an outer platform, the outer platform securing means for attachment to a housing, a vane segment from at least three guide vanes and a guide ring assembly.
- Guide vanes of low pressure turbines are made of metal and are in the development phase generally initially to segments of three or six guide vanes soldered together.
- the profile of the airfoils is like a real gas turbine engine put together several guide vane segments to form a closed guide ring assembly, the individual guide vane segments to compensate for thermal expansion are not rigidly interconnected.
- the guide vanes are attached to their outer platforms in a (engine) housing and releasably together on their inner platforms by metal clips or the like braced. By bracing the inner platforms, this is supposed to Vibration behavior of the airfoils can be improved.
- the use of the Tension clamps as additional components have the disadvantage of being more complex Assembly and higher costs.
- guide vanes are made of mostly carbon fiber reinforced plastics used and examined in so-called aerodynamic "cold" test benches. Such Guide vanes are much faster and cheaper to manufacture than corresponding ones Guide vanes made of metal and are therefore used in the upstream investigations preferably used.
- the guide vanes are made of plastic in the test bench at significantly lower temperatures (approx. 130 ° C) than in real 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 made of metal for those made of plastic, as these are the loads cannot withstand the high, real gas forces. Gluing three or six guide vanes each to form individual guide vane segments the wreath of guiding rings has not solved this problem, like bracing the guide vanes by means of bolts that are in the lateral end faces the outer and inner platforms are provided. The vibration amplitudes were too large and caused the guide vanes to break.
- EP-A-0 654 586 is concerned with guide vane segments made of fiber composite material, each segment having at least two blades and an inner and an outer Platform segment (cover band segment) includes.
- the inner platform segment is designed as a continuously open hollow section with a roughly rectangular cross section, whose curvature is coaxial to the engine axis. At one end the hollow profile is tapered in steps, so that it is largely free of play and positive fits into the open end of an adjacent hollow profile. In this way can adjacent vane segments over their inner platform segments be form-fitted together. Because the continuously open hollow profiles (see also column 3, lines 44 to 46) are still relatively easily deformable (cross-sectional deformation), is the overall dimensional stability resulting in the guide vane ring and stiffness not optimal. The simple, compliant execution of the outer platforms also have a negative impact.
- the invention has for its object a guide vane of the one described Generate genus that has an improved dynamic vibration behavior has, the vibration amplitude of adjacent guide vanes limited and manufacturing technology is easy and inexpensive to manufacture.
- the solution to the problem is characterized in that the outer Platform and the inner platform as torsion and rigid hollow structures are executed, the outer platform being a platform, a stiffening wall, two spaced-apart cross struts and a closed end face and wherein the inner platform is a platform, a reinforcement wall and has a closed end surface that the projections are integral Elements of the closed end faces are narrow, their peripheral contour have forming side faces, and that the open end faces of the platforms with their inner surfaces the receptacles for the projections of a neighboring one Form the guide vane.
- the advantage is: in that e.g. adjacent vanes of adjacent Guide vane segments (e.g. from three interconnected guide vanes) are optimally coupled to one another in the axial direction and by the friction on the contact surfaces creates a damping effect. Also effect the protrusions seal off gaps occurring between the platforms.
- the structural rigidity is also optimized.
- each projection runs perpendicular to the first, generally radial end face the outer or inner platform.
- the side surface of the projection therefore runs in the circumferential direction heavily loaded by the gas flow and enables there damping due to friction on the contact surfaces.
- each projection is preferably at least 3 mm above the first End face of the outer or inner platform, so that a sufficiently large Friction or contact surface with the recording of an adjacent guide vane is present.
- each projection has at least 30% of the (cross-sectional) area the first end face on the respective platform so that the neighboring ones Guide vanes are not only coupled point-to-point and are reliable Limitation of the vibration amplitude is made possible.
- the projection with play in the exception of the neighboring one is seated or fitted so that, for example, one another adjacent guide vanes of adjacent guide vane segments as a result of Thermal expansion can move away from each other and towards each other without any problems.
- An inner surface adjacent to the second end surface runs most preferably the recording in the assembled state parallel to the side surface of the projection, so that a secure frictional contact between the inner surface of the receptacle and the side surface the lead is guaranteed.
- 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 can be examined in so-called aerodynamic "cold" test benches. This makes it clear faster and less expensive test data for the calibration of aerodynamic design processes determine than is the case when using metal guide vanes.
- Experimental guide vanes made of plastic can also be glued to guide vane segments connect from three or six guide vanes.
- the side surface of the tab offers adhesive surfaces that are in contrast to the first and second end surfaces the outer and inner platforms are not subjected to tension / compression, but to shear become. This is the much cheaper form of stress for adhesive bonds.
- FIG. 1 shows an exemplary embodiment of the guide vane according to the invention, designated by 1, which is made of carbon fiber reinforced plastic and manufactured by injection molding is.
- a guide vane 1 is used in so-called aerodynamic "cold" test benches Fast and inexpensive 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 inner platforms 3 and 5 are on one first end face 7 is provided with a projection 8, each of which over the first end face 7 has about 3 mm protruding side surface 9.
- the airfoil 2 with its between the outer and inner platform 3 or 5 extending longitudinal extent substantially in the radial direction the engine assembly arranged.
- 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 fastening means 11 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. 3 in particular on the inner platform 5 or the vibration amplitude of the reinforcement wall 6, which is clearly recognizable at the guide vane 1 according to the invention arranged in a guide ring assembly is thereby effective limits that each of the projection 8 in the receptacle 12 of an adjacent guide vane 1 is positively received. In addition, 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 blades 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 tensile / compression second end face 7 or 13.
- a plurality of guide vane segments 15 are used to form an annular guide ring assembly assembled, which 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 interlocking causes by 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 a seal of the gaps between adjacent guide vane ice segments.
- each guide vane 1 of a guide vane segment 15 is in the stiffening wall 4 outer platform 3, a bore 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 as an elongated hole in the axial direction of the engine arrangement, so that the gas or Flow forces in the axial direction over the hook-like fastening means at the rear 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 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)
Description
- Fig. 1
- einen Längsschnitt in perspektivischer Darstellung eines Ausführungsbeispiels der erfindungsgemäßen Leitschaufel,
- Fig. 2
- eine Seitenansicht der Leitschaufel aus Fig. 1,
- Fig. 3
- eine Seitenansicht der schwingenden Leitschaufel aus Fig. 1 und 2,
- Fig.
- 4 einen Längsschnitt in perspektivischer Darstellung eines Leitschaufelsegments aus drei Leitschaufeln gemäß Fig. 1 bis 3 und
- Fig. 5
- eine perspektivische Darstellung des Leitschaufelsegments aus Fig. 4.
Claims (18)
- Leitschaufel (1) für eine Gasturbine, insbesondere eine Niederdruckturbine, mit einem Schaufelblatt (2), das sich zwischen einer inneren Plattform (5) und einer äußeren Plattform (3) erstreckt, wobei die äußere Plattform (3) Befestigungsmittel (11) zur Anbringung an einem Gehäuse aufweist, mit in eine Umfangsrichtung weisenden Stirnflächen (7) und mit in die entgegengesetzte Umfangsrichtung weisenden Stirnflächen (13) an beiden Plattformen (3,5), mit Vorsprüngen (8) an den einen Stirnflächen (7) und mit Aufnahmen (12) an den anderen Stirnflächen (13) für eine zumindest axial formschlüssige Verbindung mit benachbarten Leitschaufeln über entsprechende Vorsprünge und Aufnahmen; dadurch gekennzeichnet, dass die äußere Plattform (3) und die innere Plattform (5) als torsionsund biegesteife Hohlstrukturen ausgeführt sind, wobei die äußere Plattform (3) eine Plattform (3'), eine Versteifungswand (4), zwei mit Abstand zueinander verlaufende Querstreben (10) und eine geschlossene Stirnfläche (7) aufweist, und wobei die innere Plattform (5) eine Plattform (5'), eine Verstärkungswand (6) und eine geschlossene Stirnfläche (7) aufweist, dass die Vorsprünge (8) integrale Elemente der geschlossenen Stirnflächen (7) sind und schmale, ihre Umfangskontur bildende Seitenflächen (9) aufweisen, und dass die offenen Stirnflächen (13) der Plattformen (3,5) mit ihren Innenflächen (14) unmittelbar die Aufnahmen (12) für die Vorsprünge einer benachbarten Leitschaufel bilden.
- Leitschaufel nach Anspruch 1, dadurch gekennzeichnet, dass die Seitenfläche (9) jedes Vorsprungs (8) rechtwinklig zur ersten Stirnfläche (7) verläuft.
- Leitschaufeln nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Seitenfläche (9) jedes Vorsprungs (8) wenigstens 3 mm über die erste Stirnfläche (7) vorsteht.
- Leitschaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Seitenfläche (9) jedes Vorsprungs (8) wenigstens 5mm über die erste Stirnfläche (7) vorsteht.
- Leitschaufel nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeder Vorsprung (8) bzw. jede Aufnahme (12) wenigstens 30% der (Querschnitts-)Fläche der ersten bzw. zweiten Stirnfläche (7 bzw. 13) an der jeweiligen Plattform (3,5) ausmacht.
- Leitschaufel nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass jeder Vorsprung (8) wenigstens 50% der (Querschnitts-)Fläche der ersten Stirnfläche (7) an der jeweiligen Plattform (3,5) ausmacht.
- Leitschaufel nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeder Vorsprung (8) mit Spiel in der Aufnahme (12) sitzt.
- Leitschaufel nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die an die zweite Stirnfläche (13) angrenzende Innenfläche (14) jeder Aufnahme (12) im montierten Zustand parallel zu der Seitenfläche (9) des Vorsprungs (8) verläuft.
- Leitschaufel nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Versteifungswand (4) im wesentlichen parallel zur Plattform (3') verläuft.
- Leitschaufel nach Anspruch 9, dadurch gekennzeichnet, dass sich die Querstreben (10) über die gesamte Breite (B) der Plattform (3') erstrecken.
- Leitschaufel nach Anspruch 9 oder 10, dadurch gekennzeichnet, dass die Wandstärken der Plattformen (3',5'), Verstärkungs- und Versteifungswand (4,6) und Querstreben (10) jeweils konstant sind.
- Leitschaufel nach einem der Ansprüche 9 bis 11, dadurch gekennzeichnet, dass die Wandstärken der Plattformen (3',5'), Verstärkungs- und Versteifungswand (4,6) und Querstreben (10) jeweils annähernd gleich sind.
- Leitschaufel nach einem der vorhergehenden Ansprüche, gekennzeichnet durch eine einstückige Ausbildung.
- Leitschaufel nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Leitschaufel (1) aus faserverstärktem Kunststoff besteht.
- Leitschaufel nach einem der Ansprüche 1 bis 13, dadurch gekennzeichnet, dass die Leitschaufel (1) aus Metall besteht.
- Leitschaufelsegment aus wenigstens drei Leitschaufeln nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass jeweils zwei Vorsprünge (8) in zwei Aufnahmen (12) einer benachbarten Leitschaufel (1) formschlüssig aufgenommen sind, und benachbarte Leitschaufeln (1) wenigstens an der Seitenfläche (9) jedes Vorsprungs (8) miteinander verklebt sind.
- Leitschaufelsegment nach Anspruch 16, dadurch gekennzeichnet, dass wenigstens eine Leitschaufel (1) in der Versteifungswand (4) eine Bohrung (16) in Radialrichtung aufweist, in die ein gehäuseseitiger Bolzen eingreift.
- Leitkranzverbund aus Leitschaufelsegmenten nach Anspruch 16 oder 17, dadurch gekennzeichnet, dass jeweils zwei Vorsprünge (8) in zwei Aufnahmen (12) einer Leitschaufel (1) eines benachbarten Leitschaufelsegments (15) formschlüssig aufgenommen sind.
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 EP0899426A2 (de) | 1999-03-03 |
EP0899426A3 EP0899426A3 (de) | 1999-12-08 |
EP0899426B1 true EP0899426B1 (de) | 2003-04-02 |
Family
ID=8045040
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98114445A Expired - Lifetime EP0899426B1 (de) | 1997-08-23 | 1998-08-01 | Leitschaufel für eine Gasturbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US6217282B1 (de) |
EP (1) | EP0899426B1 (de) |
JP (1) | JPH11107704A (de) |
DE (2) | DE29715180U1 (de) |
Cited By (1)
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CN103422903A (zh) * | 2012-05-21 | 2013-12-04 | 阿尔斯通技术有限公司 | 涡轮隔板构造 |
Families Citing this family (40)
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US6435813B1 (en) * | 2000-05-10 | 2002-08-20 | General Electric Company | Impigement cooled airfoil |
RU2272151C2 (ru) * | 2000-12-28 | 2006-03-20 | Альстом Текнолоджи Лтд | Лопатка статора осевой турбины |
DE10111896B8 (de) * | 2001-03-13 | 2012-06-06 | Eads Space Transportation Gmbh | Metallischer Ring für die Verbindung zweier rotationssymmetrischer Strukturteile |
AU2003242165A1 (en) * | 2002-08-14 | 2004-03-03 | Volvo Aero Corporation | Method for manufacturing a stator component |
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 |
EP2295724B1 (de) * | 2009-08-28 | 2012-02-29 | Siemens Aktiengesellschaft | Leitschaufel für eine axial durchströmbare Turbomaschine und zugehörige Leitschaufelanordnung |
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 |
DE102010041808B4 (de) * | 2010-09-30 | 2014-10-23 | Siemens Aktiengesellschaft | Schaufelkranzsegment, Strömungsmaschine sowie Verfahren zu deren Herstellung |
JP5358559B2 (ja) * | 2010-12-28 | 2013-12-04 | 株式会社日立製作所 | 軸流圧縮機 |
US8784041B2 (en) | 2011-08-31 | 2014-07-22 | Pratt & Whitney Canada Corp. | Turbine shroud segment with integrated seal |
US9079245B2 (en) | 2011-08-31 | 2015-07-14 | Pratt & Whitney Canada Corp. | Turbine shroud segment with inter-segment overlap |
US8784037B2 (en) | 2011-08-31 | 2014-07-22 | Pratt & Whitney Canada Corp. | Turbine shroud segment with integrated impingement plate |
US9028744B2 (en) | 2011-08-31 | 2015-05-12 | Pratt & Whitney Canada Corp. | Manufacturing of turbine shroud segment with internal cooling passages |
US8784044B2 (en) | 2011-08-31 | 2014-07-22 | Pratt & Whitney Canada Corp. | Turbine shroud segment |
ES2668268T3 (es) * | 2012-01-23 | 2018-05-17 | MTU Aero Engines AG | Rotor para una turbomáquina y procedimiento para su fabricación |
EP2669477B1 (de) * | 2012-05-31 | 2017-04-05 | General Electric Technology GmbH | Deckplatte für Schaufeln |
US10309235B2 (en) | 2012-08-27 | 2019-06-04 | United Technologies Corporation | Shiplap cantilevered stator |
ITCO20130004A1 (it) * | 2013-02-20 | 2014-08-21 | Nuovo Pignone Srl | Metodo per realizzare una girante da segmenti a settore |
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 (ja) | 2016-03-15 | 2017-09-21 | 株式会社 東芝 | タービン及びタービン静翼 |
GB2551164B (en) * | 2016-06-08 | 2019-12-25 | Rolls Royce Plc | Metallic stator vane |
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 |
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 |
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 |
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FR3137120A1 (fr) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Ensemble aubagé de turbomachine comportant des moyens de limitations de vibrations entre plateformes |
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-
1997
- 1997-08-23 DE DE29715180U patent/DE29715180U1/de not_active Expired - Lifetime
-
1998
- 1998-08-01 DE DE59807705T patent/DE59807705D1/de not_active Expired - Fee Related
- 1998-08-01 EP EP98114445A patent/EP0899426B1/de not_active Expired - Lifetime
- 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
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103422903A (zh) * | 2012-05-21 | 2013-12-04 | 阿尔斯通技术有限公司 | 涡轮隔板构造 |
CN103422903B (zh) * | 2012-05-21 | 2015-11-25 | 阿尔斯通技术有限公司 | 涡轮隔板构造 |
Also Published As
Publication number | Publication date |
---|---|
DE59807705D1 (de) | 2003-05-08 |
DE29715180U1 (de) | 1997-10-16 |
US6217282B1 (en) | 2001-04-17 |
EP0899426A2 (de) | 1999-03-03 |
EP0899426A3 (de) | 1999-12-08 |
JPH11107704A (ja) | 1999-04-20 |
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