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EP2886800A1 - Agencement d'aubages statoriques pour une turbine à gaz et joint d'étanchéité en bande associé - Google Patents

Agencement d'aubages statoriques pour une turbine à gaz et joint d'étanchéité en bande associé Download PDF

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Publication number
EP2886800A1
EP2886800A1 EP13198156.5A EP13198156A EP2886800A1 EP 2886800 A1 EP2886800 A1 EP 2886800A1 EP 13198156 A EP13198156 A EP 13198156A EP 2886800 A1 EP2886800 A1 EP 2886800A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
strip seal
wedge face
groove
leading
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.)
Withdrawn
Application number
EP13198156.5A
Other languages
German (de)
English (en)
Inventor
Asier Oyarbide
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Priority to EP13198156.5A priority Critical patent/EP2886800A1/fr
Publication of EP2886800A1 publication Critical patent/EP2886800A1/fr
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms

Definitions

  • the invention regards a guide vane assembly for a gas turbine.
  • a guide vane assembly is known to consist of a plurality of guide vanes, which are arranged next to each other in a circumferential direction in a gas turbine.
  • Each guide vane comprises an airfoil section which is arranged in an annular gas flow path of the gas turbine, a vane root and a vane tip.
  • the vane root serves to attach the guide vane at an inner shroud or casing, wherein the vane tip serves to assemble the guide vane in an outer casing.
  • strip seals for sealing gaps between adjacent guide vanes.
  • Such strip seals serve to seal gaps between adjacent guide vanes that would allow gas to leave the annular gas flow path of the gas turbine and as well to seal adjacent cavities to fulfil the secondary air system requirements.
  • strip seals are arranged in grooves which are located in wedge faces in the vane root and/or the vane tip.
  • the present invention provides a guide vane assembly which the features of claim 1 and a strip seal with the features of claim 13. Embodiments of the invention are identified in the dependent claims.
  • the invention provides an guide vane assembly with a strip seal which comprises at least one first elongated edge which is arranged in a groove of a first wedge face of a first guide vane and at least one second elongated edge which is arranged in a groove of a second wedge face of a second guide vane that neighbours the first guide vane.
  • the strip seal is designed such that in the assembled state of the guide vane assembly at least one of the first and second edges runs at least partly angular with respect to the wedge face in which it is arranged.
  • At least one of the elongated edges of the strip seal does not run parallel to the wedge face into which it is inserted. This has the effect that such elongated edge of a strip seal does not need to be placed in a groove over its complete length at once. Instead, there is provided a leading geometry which points towards the wedge face. Insertion of such elongated edge of the strip seal into a respective groove is simplified as the leading geometry leads the strip seal into the groove, wherein the strip seal by its own geometry is driven into the right position.
  • the invention thus provides for an improvement in placing an elongated edge of a strip seal into the groove of a wedge face by abandoning a parallel orientation of the elongated edge with respect to the wedge face and by using instead a design of the strip seal in which at least one of the elongated first and second edges run at least partly angular with respect to the wedge face, thereby forming a leading geometry which is inserted first in the respective groove, thereby leading the strip seal along its elongated edge gradually into the groove.
  • the assembly of a strip seal is simplified and the risk of a wrong assembly is reduced.
  • the strip seal forms at least one leading corner at the elongated edge which runs angular with respect to the wedge face. Such leading corner points towards the guide vane in which the groove is located in which the elongated edge is arranged. Such leading corner in one embodiment is located at one of the two ends of the edge. In another embodiment, the leading corner is located between the two ends of the edge.
  • the elongated edge is formed by a straight line.
  • the elongated edge comprises two or more sections, each of which are formed by a straight line, and which run at an angle to each other such that the leading corner is formed where the two sections meet.
  • the elongated edge may not be formed by a straight line or sections of straight lines, but may instead have, e.g., a curved or wavy configuration.
  • the leading corner may be formed by a sharp corner or alternatively may be formed by a rounded corner.
  • the strip seals may include structures that allows to attach the strip seals to each other in an angled configuration.
  • Such structure may be formed, e.g., by respective slots in the strip seals in the crossing area.
  • the leading corner when a strip seal crosses with a further strip seal, the leading corner may be provided in the crossing area.
  • the strip seal comprises a bended region, the leading corner may be provided in the bended region.
  • the placement of the leading corner in a crossing area or in a bended area is associated with the advantage that the leading corner can guide and lead the strip seal into the respective grooves of both strip seals that cross each other or of both parts of the strip seal that are before and behind the bended region.
  • both the first elongated edge and the second elongated edge comprise a leading corner.
  • the leading corners at both the first and the second elongated edges are arranged in a symmetrical configuration. This provides for a fool-prove design which allows to assemble a strip seal without having to consider if a particular of the elongated edges of the strip seal needs to be arranged in a particular groove. Due to the symmetrical configuration, the strip seal can be turned 180 degrees without harm to the assembly process.
  • the strip seal has a flat planar configuration or a flat corrugated configuration.
  • a flat configuration means that the strip seal essentially extends in two dimensions, with its extension in the third dimension being much smaller that its extension in the two other dimensions.
  • the strip seal may be stamped out of a metal sheet or other flat structure.
  • a feature that the strip seal may have a flat planar configuration means that the strip seal extends in a plane.
  • Such strip seals are used in connection with grooves which extend along a straight line.
  • the strip seal may have a corrugated, wavy or curved configuration. Such strip seal is used if the respective groove is not formed by a straight line but also has a corrugated, wavy or curved configuration.
  • first wedge face and/or the second wedge face are planar.
  • the invention is not limited to any specific form of the wedge face which may take any complex geometry.
  • the first wedge face and/or the second wedge face, accordingly, may also be non-planar.
  • the strip seal is defined such that in the assembled state of the guide vane assembly one of the first and second edges runs angled with respect to the wedge face in which it is arranged and the other one of the first and second edges runs parallel with respect to the wedge face in which it is arranged.
  • the guide vanes of the guide vane assembly of the present invention may be formed by nozzle guide vanes.
  • the principles of the invention can be applied in a similar manner to any other guide vane which is assembled with other guide vanes to form a guide vane assembly such as a stator wheel.
  • the guide vanes could, e.g., also be guide vanes in a compressor of a gas engine such as compressor inlet guide vanes or compressor outlet guide vanes.
  • the invention further provides for a strip seal for use in a guide vane assembly.
  • the strip seal is designed such that at least one of its edges forms a leading geometry such that, when the strip seal is inserted into a groove of a wedge face, the leading geometry leads insertion of the strip seal into the groove.
  • leading geometry may be a leading corner.
  • Fig. 1 shows a cross-sectional view of a turbine section of a jet engine, in which the present invention may be embodied.
  • the turbine section comprises rotor blades 15 and nozzle guide vanes 1, wherein Fig. 1 depicts two rotor blades 15 and one nozzle guide vane 1.
  • the rotor blades 15 and nozzle guide vanes 1 are located in an annular gas flow path 16 of the turbine section, in which gas flows in a direction 17.
  • Each nozzle guide vane 1 comprises an airfoil section 110 arranged in the annular gas flow path 16, a vane root or vane inner platform 120 and a vane tip or vane outer platform 130.
  • the vane root 120 is fastened to a structure 19 of an inner casing and the vane tip 130 is fastened to an outer casing 18.
  • each guide vane 1 comprises in a wedge face 121 of its vane root 120 and in a wedge face 131 of its vane tip 130 a groove 2 which serves to receive and hold a seal strip, as will be explained below.
  • the groove 2 may be formed of different sections 2a, 2b, 2c, 2d, 2e. Strip seals inserted into the grooves 2a, 2b, 2c, 2d, 2e serve to seal a gap that exist between neighbouring nozzle guide vanes 1, when a plurality of nozzle guide vanes 1 are arranged next to each other in a circumferential direction to form a stator wheel.
  • Fig. 2 shows an exemplary embodiment of a guide vane 1 which comprises an airfoil section 110 and vane root or vane inner platform 120.
  • the vane root 120 comprises a wedge face 121 which faces a corresponding wedge face of a neighbouring guide vane when in the assembled state.
  • the wedge face 121 there are provided grooves 2 which form different groove sections 2a, 2b, 2c.
  • the grooves may have a straight or curved or wavy form.
  • a respective strip seal is to be inserted.
  • Fig. 3A, 3B illustrate the insertion of a strip seal 30 in grooves of two wedge faces of neighbouring guide vanes 1, 1' according to the state of the art to indicate the problems associated with state of the art strip seals.
  • a strip seal 30 has a generally flat, elongated configuration and comprises two elongated edges, a first elongated edge 310 and a second elongated edge 320.
  • the two elongated edges 310, 320 are formed by straight lines which run parallel to each other.
  • the strip seal 30 further includes two narrow sides which, however, are not of relevance in the present context.
  • Each of the guide vanes 1, 1' comprise, e.g., in the vain root and/or in the vain tip, a wedge face 121, 121' with one or several grooves as discussed with respect to Figs. 1 and 2 .
  • the strip seal is first inserted along its elongated edge 320 into the respective groove of wedge face 121'. Afterwards, the subassembly consisting of guide vane 1' and strip seal 30 is to be assembled into the groove of the opposite guide vane 1. Because of the parallel orientation of the two edges 310, 320, to achieve this, edge 310 needs to be assembled and inserted into the respective groove of wedge face 121 along the complete length of the edge 310 at the same time. Therefore, such assembly is difficult and involves a considerable assembly time. Also, there is the risk of errors and of damaging the strip seal along its elongated edge 310. After the assembly has been completed, as is shown in Fig. 3B , the gap between the two neighbouring guide vanes 1, 1' has been sealed by means of the seal strip 30.
  • Fig. 4A to 4 E show five embodiments of a strip seal which are in accordance with the present invention.
  • the strip seal of each embodiments is formed such that at least one of its edges forms a leading geometry in the form of a leading edge such that, when the strip seal is inserted into a groove of a wedge face, the leading geometry leads the insertion of the strip seal into the groove and, this way, improves the assembly time and reduces the risk of errors.
  • a strip seal 3 which has two elongated edges 31, 32, which are each formed by a straight line, without the two edges 31, 32 being parallel. More particular, while the edge 32 runs parallel to a wedge face into which it is to be inserted, the edge 31 runs angular with respect to such wedge face, thereby forming a leading geometry in form of a leading edge 20 at one of its ends. Assembly of such strip seal in grooves of two neighbouring guide vanes will be explained with respect to Figs. 5A to 5D below.
  • Fig. 4B shows an embodiment of a strip seal 4 which has two elongated edges 41, 42, wherein one of the elongated edges 41 is comprised of two straight sections 411, 412, which are arranged at an angle to each other and thus form a leading corner 20 which points towards the wedge face into which the strip seal 4 is to be inserted. Accordingly, in this embodiment, a leading corner is provided that is located between the upper and lower ends, i.e., the narrow faces of the strip seal 4.
  • Fig. 4C to 4E show embodiments of a strip seal in which a leading corner is provided on both elongated edges of the strip seal, wherein the leading corners are arranged in a symmetrical configuration.
  • a strip seal 5 has two elongated edges 51, 52 which each form a leading corner 20 at one of its ends and on opposite ends.
  • Fig. 4D shows a strip seal 6 which comprises two elongated edges 61, 62, which each consist of two straight sections 611, 612 und 621, 622 which form two leading corners 20 at a location between the two ends of the strip seal 6.
  • the lengths of the sections 611, 612, 621, 622 is essentially the same, such that the leading corners 20 are arranged opposite to each other.
  • Fig. 4E shows an embodiment of a strip seal 7 which is similar to the embodiment of Fig. 4D , except that the length of the straight sections 711, 712 forming elongated edge 71 and of the straight sections 721, 722 forming elongated edge 72 are different, such that the leading corners 20 formed at the two elongated edges 71, 72 are offset, but in a symmetrical configuration.
  • Fig. 5A shows the assembly of a strip seal 3 according to Fig. 4A into adjacent guide vanes 1, 1'.
  • the wedge faces 121, 121' of two adjacent guide vanes 1, 1' are directed towards each other.
  • Each wedge face 121, 121' comprises a groove (not shown in Fig. 5A ).
  • strip seal 3 In between the two wedge faces 121, 121' is arranged strip seal 3.
  • an operator In a first step, according to Fig. 5B , an operator assembles the strip seal 3 along its elongated edge 32 - that runs parallel to wedge face 121' - into groove 2'.
  • Such subassembly is then assembled into the opposite guide vane 1, wherein strip seal 3 needs to be inserted along elongated edge 31 into the respective groove of wedge face 121.
  • the operator positions the leading corner 20 (see Fig. 5C ) in the groove 2' of the adjacent guide vane 1, and then pushes the two guide vanes 1, 1' together, as seen in Fig. 5D .
  • the strip seal 3 is led automatically into the groove 2 of guide vane 1, within automatic correct positioning of the edge 31 of strip seal 3 in groove 2 of guide vane 1. This way, assembly time is reduced, the risk of errors is reduced and the risk of damaging parts is also reduced.
  • groove 2 in guide vane 1 in which the edge 31 of strip seal 3 is inserted needs to be formed differently than groove 2' of guide vane 1' in that it needs to be provided with more depth towards the leading corner 20.
  • the groove in the guide vane needs to be formed such that its depth corresponds to the form and width of the strip seal which is inserted into the groove.
  • the machining time for producing the groove will be slightly increased. Also as the strip seal 3 is provided with a leading corner 20, the weight of the strip seal is increased compared to a state of the art strip seal as shown in Fig. 3 . However, both of these effects are negligible.
  • Figs. 6A to 6D show the assembly of a strip seal 4 in accordance with the embodiment of Fig. 4B .
  • the sequence of steps is similar as in Figs. 5A to 5D .
  • the strip seal is arranged with its elongated edge 42 which runs parallel to the wedge face 121' of guide vane 1' into the respective groove.
  • the such formed subassembly is assembled to the opposite guide vane 1.
  • the sharp corner 20 of the strip seal 4 is positioned in the groove of the opposite guide vane 1 and the two guide vanes 1, 1' are than pushed together, wherein the sharp, leading corner 20 of strip seal 4 leads the strip seal 4 along the edge 41 into the groove of guide vane 1, see Figs. 5C and 5D .
  • the wedge faces 121, 121' of guide vanes 1, 1' were formed as a planar surface.
  • the wedge faces 121, 121' can alternatively have a non-planar form and implement complex geometries that require wavy shapes of strip seals.
  • Figs. 7A to 7D and Figs. 8A to 8D show two corresponding embodiments in which the wedge faces 121, 121' of two adjacent guide vanes 1, 1' are non-planar, but correspond to each other to only have a minimal gap in between two adjacent guide vanes 1, 1' when assembled.
  • a strip seal 8 which comprises two elongated edges 81, 82, which each comprise two straight sections 811, 812, 821, 822.
  • the edge 82 with section 821, 822 runs parallel to the respective surface 121 of guide vane 1'.
  • edge 81 runs at least partly, namely, in the area of section 812 angular with respect to the wedge face 121 which comprises the groove into which the strip seal 8 is to be inserted.
  • the operator For assembly, the operator assembles the strip seal 8 along edge 82 into the respective groove in wedge face 121' of guide vane 1'. Afterwards, the operator positions the leading corner 20 of edge 81 in the groove of the adjacent guide vane 1 in wedge face 121 and then pushes the guide vanes 1, 1' together. The assembly does follow the same principles as discussed before.
  • a strip seal 9 with elongated edges 91, 92 which are each comprised of two straight sections 911, 912, 921, 922.
  • the sections 921, 922 run parallel to areas of the wedge face 121' of guide vane 1' with include a groove into which the strip seal 9 is to be inserted.
  • the elongated edge 91 arranged next to wedge face 121 of guide vane 1 is formed such that it does not run parallel to the corresponding wedge face 121, but instead forms a leading corner 20.
  • the assembly resembles the assembly in Figs.
  • Fig. 9B shows an embodiment in which a first strip seal 10 is crossed by a second strip seal 11, wherein, e.g., strip seal 10 is arranged in groove 2a of Fig. 2 and strip seal 11 is arranged in groove 2c of Fig. 2 .
  • the two strip seals 10, 11 are joined to each other in a crossing area 20.
  • the strip seals may have specific structure such as slots (not shown) which allow assembly of the two strip seals 10, 11 together.
  • the leading corner 20 is provided in the crossing area 40. Both the strip seal 10 and the strip seal 11 form the leading corner 20.
  • strip seal structure consisting of strip seal 10 and strip seal 11 can be inserted into two grooves (such as grooves 2a, 2c of Fig. 2 ) at the same time, again with the advantage that the leading corner 20 leads the strip seals 10, 11 into the respective grooves and provides for an improved assembly.
  • additional strip seals are connected to strip seal 10 in other crossing areas forming further leading corners.
  • Fig. 9A shows a state of the art strip seal combination of strip seals 30, 31 without the inventive features.
  • Fig. 10B shows a further embodiment of a strip seal 12, wherein the strip seal 12 includes a first region 12a which is essentially planar, a second region 12b which is bent, and a third region 12c which is essentially planar again.
  • the strip seal 12 includes a first region 12a which is essentially planar, a second region 12b which is bent, and a third region 12c which is essentially planar again.
  • the leading corner 20 As the leading corner 20 is provided in the bended region 12d, the leading corner 20 improves insertion of the strip seal 12 into a respective groove both along the area 12a and along the area as 12b.
  • FIG. 10A shows a strip seal 32 with a bended region 32b and two planar regions 32a, 32c without the inventive features.
  • the form of the strip seal may differ from the forms shown in the described embodiments.
  • the leading geometry does to have to be in the form of a sharp corner but may have a curved form instead.
  • the wedge faces of the guide vanes may have other and more complex geometries than those shown schematically in the Figures. Accordingly, other implementations are within the scope of the following claims.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13198156.5A 2013-12-18 2013-12-18 Agencement d'aubages statoriques pour une turbine à gaz et joint d'étanchéité en bande associé Withdrawn EP2886800A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13198156.5A EP2886800A1 (fr) 2013-12-18 2013-12-18 Agencement d'aubages statoriques pour une turbine à gaz et joint d'étanchéité en bande associé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13198156.5A EP2886800A1 (fr) 2013-12-18 2013-12-18 Agencement d'aubages statoriques pour une turbine à gaz et joint d'étanchéité en bande associé

Publications (1)

Publication Number Publication Date
EP2886800A1 true EP2886800A1 (fr) 2015-06-24

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EP13198156.5A Withdrawn EP2886800A1 (fr) 2013-12-18 2013-12-18 Agencement d'aubages statoriques pour une turbine à gaz et joint d'étanchéité en bande associé

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2998514A3 (fr) * 2014-07-31 2016-05-25 United Technologies Corporation Joint de plateforme d'aube assemblable en position inversée
EP3034805A1 (fr) * 2014-12-17 2016-06-22 United Technologies Corporation Joint à languette ayant une partie radiale conique et section d'un moteur à turbine à gaz ayant un tel joint à languette
EP3584410A1 (fr) * 2018-06-19 2019-12-25 General Electric Company Joint incurvé pour composants de turbine à gaz adjacents
US10890079B2 (en) 2018-12-04 2021-01-12 Raytheon Technologies Corporation Gas turbine engine arc segments with arced walls
DE102019211815A1 (de) * 2019-08-07 2021-02-11 MTU Aero Engines AG Turbomaschinenschaufel

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5868398A (en) * 1997-05-20 1999-02-09 United Technologies Corporation Gas turbine stator vane seal
US6162014A (en) * 1998-09-22 2000-12-19 General Electric Company Turbine spline seal and turbine assembly containing such spline seal
WO2004074640A1 (fr) * 2003-02-19 2004-09-02 Alstom Technology Ltd Systeme de joint notamment destine a des segments d'ailettes de turbines a gaz
EP1798380A2 (fr) * 2005-12-16 2007-06-20 General Electric Company Tuyère de turbine avec joint à languette
US20090269188A1 (en) * 2008-04-29 2009-10-29 Yves Martin Shroud segment arrangement for gas turbine engines
EP2679770A1 (fr) * 2012-06-26 2014-01-01 Siemens Aktiengesellschaft Bande d'étanchéité pour plate-forme de turbine à gaz

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5868398A (en) * 1997-05-20 1999-02-09 United Technologies Corporation Gas turbine stator vane seal
US6162014A (en) * 1998-09-22 2000-12-19 General Electric Company Turbine spline seal and turbine assembly containing such spline seal
WO2004074640A1 (fr) * 2003-02-19 2004-09-02 Alstom Technology Ltd Systeme de joint notamment destine a des segments d'ailettes de turbines a gaz
EP1798380A2 (fr) * 2005-12-16 2007-06-20 General Electric Company Tuyère de turbine avec joint à languette
US20090269188A1 (en) * 2008-04-29 2009-10-29 Yves Martin Shroud segment arrangement for gas turbine engines
EP2679770A1 (fr) * 2012-06-26 2014-01-01 Siemens Aktiengesellschaft Bande d'étanchéité pour plate-forme de turbine à gaz

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2998514A3 (fr) * 2014-07-31 2016-05-25 United Technologies Corporation Joint de plateforme d'aube assemblable en position inversée
EP3034805A1 (fr) * 2014-12-17 2016-06-22 United Technologies Corporation Joint à languette ayant une partie radiale conique et section d'un moteur à turbine à gaz ayant un tel joint à languette
US10196913B1 (en) 2014-12-17 2019-02-05 United Technologies Corporation Featherseal having tapered radial portion
EP3584410A1 (fr) * 2018-06-19 2019-12-25 General Electric Company Joint incurvé pour composants de turbine à gaz adjacents
US11047248B2 (en) 2018-06-19 2021-06-29 General Electric Company Curved seal for adjacent gas turbine components
US11773739B2 (en) 2018-06-19 2023-10-03 General Electric Company Curved seal for adjacent gas turbine components
US10890079B2 (en) 2018-12-04 2021-01-12 Raytheon Technologies Corporation Gas turbine engine arc segments with arced walls
DE102019211815A1 (de) * 2019-08-07 2021-02-11 MTU Aero Engines AG Turbomaschinenschaufel

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