EP2871325B1 - Virole interne d'une turbomachine et distributeur - Google Patents

Virole interne d'une turbomachine et distributeur Download PDF

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Publication number
EP2871325B1
EP2871325B1 EP13192465.6A EP13192465A EP2871325B1 EP 2871325 B1 EP2871325 B1 EP 2871325B1 EP 13192465 A EP13192465 A EP 13192465A EP 2871325 B1 EP2871325 B1 EP 2871325B1
Authority
EP
European Patent Office
Prior art keywords
segment
ring
inner ring
section
carrier segment
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.)
Active
Application number
EP13192465.6A
Other languages
German (de)
English (en)
Other versions
EP2871325A1 (fr
Inventor
Lothar Albers
Georg Zotz
Rudolf Pilzweger
Hermann Becker
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 Aero Engines AG
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 Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13192465.6A priority Critical patent/EP2871325B1/fr
Priority to US14/537,848 priority patent/US9587499B2/en
Publication of EP2871325A1 publication Critical patent/EP2871325A1/fr
Application granted granted Critical
Publication of EP2871325B1 publication Critical patent/EP2871325B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade 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
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to an inner ring of a turbomachine according to the preamble of claim 1. Furthermore, the present invention relates to a stator according to claim 10.
  • inner rings are often attached to guide wheels at the radially inner end, to which seals can be attached.
  • the seals serve to seal the flow medium between upstream and downstream blade regions.
  • For the inner rings there are different embodiments, for example, to realize an attachment of the inner ring on the stator, an attachment of seals on the inner ring, a simple assembly and disassembly for maintenance and repair purposes and cost-effective production.
  • An object of the present invention is to propose an inner ring for turbomachines, which allows easy assembly and disassembly of individual segments of the inner ring and is inexpensive to manufacture. It is another object of the present invention to provide a stator with an inner ring according to the invention.
  • an inner ring of a turbomachine in particular an axial flow machine, and further in particular an axial gas turbine, for attachment to guide vanes and for receiving sealing segments is proposed.
  • the multi-part inner ring has at least one fixing ring and a seal carrier. Both the fixation ring and the seal carrier are subdivided or segmented into at least two segments in the circumferential direction. These fixing ring segments and seal carrier segments are each arranged on the front side relative to one another in the circumferential direction of the inner ring.
  • Fixing ring segment has a relation to the first offset second ring segment paragraph.
  • the second ring segment paragraph is arranged offset from the first ring segment paragraph.
  • the second ring segment shoulder is offset radially relative to the first ring segment shoulder.
  • a first seal carrier segment has a first carrier segment shoulder and a second seal carrier segment has a second carrier segment shoulder which is offset with respect to the first carrier segment shoulder.
  • the second carrier segment shoulder is offset radially relative to the first carrier segment shoulder.
  • the first ring segment paragraph is arranged in a parting plane of the inner ring at least partially end face in the circumferential direction on the second carrier segment paragraph or is this. Furthermore, the second ring segment paragraph lies in this division plane, at least in sections, on the end face in the circumferential direction to the first carrier segment paragraph.
  • first fixing ring segment and the first seal carrier segment are not displaceable, preferably completely or substantially, in the circumferential direction over the dividing plane.
  • the segments are not slidable over the dividing plane because the first ring segment shoulder prevents or blocks displacement by abutment with the second carrier segment shoulder.
  • the second fixing ring segment and the second seal carrier segment are not displaceable, preferably completely or substantially, in the circumferential direction over the dividing plane.
  • the segments are not slidable over the parting plane because the second ring segment shoulder prevents or blocks displacement by abutment with the first carrier segment shoulder.
  • the stator according to the invention has an inner ring according to the invention.
  • Inventive exemplary embodiments may have one or more of the following features.
  • turbomachines may in particular be an axial flow machine.
  • the gas turbine may in particular be an axial gas turbine, for example an aircraft gas turbine.
  • the second ring segment shoulder is offset radially relative to the first ring segment shoulder.
  • the second ring segment paragraph can be arranged offset from the first ring segment paragraph axially, diagonally or in another arrangement.
  • the second carrier segment shoulder is offset radially relative to the first carrier segment shoulder.
  • the second carrier segment shoulder can be arranged offset from the first carrier segment shoulder axially, diagonally or in another arrangement.
  • the inner ring in particular the inner ring fixation ring, is connected to the radially inner end of the vane or attached to the vane.
  • one or more sealing linings are preferably fastened to the radially inner ends of the seal carrier segments.
  • the gaskets may be parts or portions of the inner ring.
  • the inner ring has connecting pins in the circumferential direction for connecting in each case two adjacent fixing rings.
  • the connecting pins are arranged on or in parting planes of the inner ring.
  • the fixing ring segments have no further pins, shoulders, parallel keys or the like in order to support or fix the fixing ring segments, for example, against radially adjacent further inner ring segments.
  • the first Fixtechniksringsegment supported on the one hand against the second Fixtechniksringsegment in the circumferential direction in a first parting plane additionally supports the first Ringsegmentabficient the first Fixtechniksringsegments against the second Susegmentabficient of the second seal carrier segment from, in particular in the first parting plane.
  • the first seal carrier segment is supported on the one hand against the second seal carrier segment in the circumferential direction in a parting plane, in particular in the first parting plane, on the other hand supports the first Susegmentabsatz the first seal carrier segment against the second ring segment paragraph of the second Fix istsringsegments from, in particular in the first division level.
  • the first ring segment shoulder is integrally connected to the first fixing ring segment and / or the second ring segment shoulder is integrally connected to the second fixing ring segment.
  • An integral connection is understood in particular to be a one-piece connection, for example a one-piece component that is manufactured as a component by casting or that is machined as a component.
  • the first ring segment shoulder is connected to the first fixing ring segment and / or the second ring segment shoulder to the second fixing ring segment by means of a joining method, for example by means of welding or soldering.
  • the first carrier segment shoulder is integrally connected to the first seal carrier segment and / or the second carrier segment shoulder is integrally connected to the second seal carrier segment.
  • the first and second fixing ring segments and / or the first and second seal carrier segments each have a circumferential angle of 180 degrees. With a circumferential angle of 180 degrees, the two halves can support each other. In particular, the two peripheral halves are not supported by any other components. The circumferential securing of the two peripheral halves thus takes place in particular at a dividing plane for the seal carrier segments.
  • the fixing ring segments are supported on guide blade pins.
  • Vanes may be pins or pins at the radially inner end of the vane to connect the vanes to the fixation ring segments.
  • the first and second fixing ring segments and / or the first and second seal carrier segments each have a circumferential angle of 120 degrees or 90 degrees or 60 degrees or another angle.
  • the first carrier segment shoulder is arranged at the radially outer end of the seal carrier segment.
  • the first carrier segment shoulder is arranged on a dividing plane of the inner ring and bears against a radially outer end arranged on the front side ring segment paragraph of a Fix mich michsringsegments.
  • This fixation ring segment can be arranged adjacent to the seal carrier segment in the circumferential direction.
  • the first and / or the second carrier segment shoulder and / or the first and / or the second ring segment shoulder each extend over the entire circumferential length of the respective seal carrier segment or fixing ring segment.
  • the seal carrier segment and / or the Fix istsringsegment can be advantageously prepared in this embodiment as a rotating part.
  • the respective rotary part, the seal carrier and / or the fixing ring can be divided after the first production step as a rotary part, for example, in two 180 degree segments, which can be used in each case in an inner ring.
  • the carrier segment shoulders and / or the ring segment shoulders each extend over a smaller circumferential length with respect to the circumferential length of the respective seal carrier segment or fixing ring segment.
  • the paragraphs may extend over 10 or 20 degrees in the circumferential direction, wherein the segments include, for example, 180 degrees.
  • the first and / or second carrier segment shoulder is disposed on an axially downstream, radially extending portion of the respective seal carrier segment.
  • This section can be referred to as a so-called bulkhead.
  • the ratio of the axial width to the radial extent of the section is 1: 6 or less, for example 1:10, 1:20 or 1:30, the axial width being determined without the carrier segment shoulder.
  • the axial width is about 4 mm and the radial extent of the section about 24 mm, or the axial width is about 3 mm and the radial extent of the section about 18 mm.
  • the first and / or the second fixing ring segment has at least one hole in the circumferential direction at one or both front end (s).
  • This hole can be a receptacle or a recess.
  • the bore is provided and configured in particular for receiving a pin for connecting the Fix istsringsegmente.
  • the pens can be in two or more Be parting planes of the inner ring the same or different.
  • the pins may have different lengths or have different diameters.
  • the pins are designed identically in all graduation planes.
  • the first and / or the second seal carrier segment has inlet seals for sealing against a flow medium of the axial flow machine.
  • all seal carrier segments on their radially inner side inlet seals are on their radially inner side inlet seals.
  • the stator is connected to a housing of an axial compressor, in particular a high-pressure axial compressor.
  • the inner ring has no pin (or other positioning arrangement or positioning aid, in particular for the Fix istsringsegmente)
  • Some or all embodiments according to the invention may have one, several or all of the advantages mentioned above and / or below.
  • the seal carrier segments can be pushed in the assembly of the inner ring according to the invention on the Fix istsringsegmente in the circumferential direction.
  • the seal carrier segments may then be advantageously secured against circumferential displacement or rotation (circumferential rotation) by means of the radially offset carrier segment and annular segment shoulders so as not to interfere with the circumferentially adjacent one of the dividing planes in the intended operation of the guide vanes in the gas turbine Can push fixation ring.
  • Such a shift beyond the dividing plane could complicate the dismantling of housing halves (split case) with the inner rings or completely block.
  • the structural design of the bulkhead can advantageously be optimized with regard to the bending stiffness of the seal carrier by means of the inner ring according to the invention.
  • a higher bending stiffness of the seal carrier can reduce the so-called "cording effect".
  • a "cording effect” is a thermal effect, especially in the case of fixing rings, which can lead to a three-dimensional deformation of the inner rings at the dividing planes. These deformations can lead to a stronger inlet of sealing fins in the inlet seals, which can increase the sealing gaps and leaks. Larger leaks can reduce the efficiency.
  • the targeted design of the bulkhead eg axial width, radial extent
  • the bending stiffness of the seal carrier can be increased.
  • a higher bending stiffness can counteract the "cording effect", whereby a radially lower inlet of the sealing fins into the inlet seal at the parting planes can be reduced.
  • the efficiency can be positively influenced.
  • the bending stiffness can be further optimized advantageously.
  • Fig. 1 shows an inner ring 100 according to the invention in a frontal plan view of a Fixtechniksringsegment 1 and a seal carrier segment 3.
  • the plane of the plan view is a parting plane of the inner ring 100th
  • Inner ring 100 is attached at its radially outer end to the radially inner end of a vane 5.
  • the inner ring 100 also has inlet seals 7 (or inlet seal linings).
  • the fixing ring segment 1 and the seal carrier segment 3 are pushed one into the other in the circumferential direction.
  • the fixing ring segment 1 has a slide 9, which is guided in a guide 11 of the seal carrier segment 3.
  • the seal carrier segment 3 has a radially extending section 13 with an integral carrier segment shoulder 15.
  • the radially extending portion 13 is also referred to as a bulkhead 13.
  • the fixing ring segment 1 has a bore 17 for connecting two adjacent fixing ring segments 1 on.
  • a pin 31 (s. FIG. 6 and 7 ) are inserted to connect the two Fixtechniksringsegmente 1 frontally in the parting plane with each other.
  • Fig. 2 shows a frontal plan view of the seal carrier segment 3 of the inner ring 100 according to the invention with radially outer carrier segment paragraph 15th
  • the individual dimensions of the bulkhead wall 13 can substantially influence or change the bending stiffness of the seal carrier segment 3.
  • the bulkhead wall can be characterized, for example, by the ratio of the axial width 19 to the radial extent 21.
  • the flexural rigidity of the bulkhead can be further influenced and optimized by the axial width 23 and radial length 25 of the carrier segment paragraph 15.
  • the carrier segment shoulder 15 in FIG Fig. 3 is radially offset from the carrier segment paragraph 15 in Fig. 2 ,
  • Fig. 4 shows a frontal plan view of the fixing ring segment 1 of the inner ring 100 according to the invention with a radially outer ring segment paragraph 27th
  • This fixing ring segment 1 with the radially outer ring segment shoulder 27 is for receiving the seal carrier segment 3 (see Fig. 3 ) intended.
  • the seal carrier segment 3 is initially rotationally displaceable in the circumferential direction. However, if a further seal carrier segment 3 rests against the fixing ring segment 1, the further seal carrier segment 3 can no longer be moved rotationally relative to the first seal carrier segment 3. Thus, the circumferential security in the division level, in which abut the frontal segments, reached.
  • the bore 17 is provided for receiving a pin for connecting two adjacent Fix istsringsegmente 1.
  • Fig. 5 shows an end-face view of a fixing ring segment of the inner ring 100 according to the invention with a radially inner ring segment shoulder 27th
  • This fixing ring segment 1 is provided for receiving the seal carrier segment 3, which is rotationally displaceable in the circumferential direction.
  • Fig. 6 shows a perspective view of an inner ring 100 according to the invention with two seal carrier segments 3 and a Fix istsringsegment first
  • the seal carrier segment 3 (in Fig. 6 the rear seal carrier segment 3) is pushed onto the fixing ring segment 1.
  • the seal carrier segment 3 (in Fig. 6 the front seal carrier segment 3) with the carrier segment paragraph 15 against the ring segment paragraph 27 of the fixing segment 1 from.
  • the rear and front seal carrier segment 3 are designed differently, due to the radially offset carrier segment paragraphs 15.
  • the radially staggered carrier segment paragraphs 15 and the radially offset arranged ring segment paragraphs 27 (in Fig. 6 If only one ring segment shoulder 27 is shown), they can not shift beyond the dividing plane 29 and thus form a circumferential securing device.
  • a pin 31 is used to connect the fixing ring segment 1 with another fixing ring segment 1 can.
  • the depressions 33 are provided and configured for connecting the guide blade 5 to the fixing ring segment 1 of the inner ring 100 according to the invention.
  • Fig . 7 shows a further perspective view of an inner ring 100 according to the invention with two seal carrier segments 3 and a Fix istsringsegment first
  • the fixing ring segment 1 has a radially inner ring segment shoulder 27 (corresponding to FIG Fig. 5 ) on.
  • the carrier segment shoulder 15 of the front seal carrier segment 3 is supported against the ring segment shoulder 27 and prevents displacement of the seal carrier segment 3 beyond the dividing plane 29 in the circumferential direction.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (11)

  1. Virole (100) d'une turbomachine, pour la fixation sur les aubes de guidage (5) de la turbomachine et pour la réception de segments d'étanchéité (7), avec des anneaux de fixation et des supports de joint d'étanchéité, où les anneaux de fixation sont subdivisés en au moins deux segments (1) d'anneau de fixation et les supports de joint d'étanchéité en au moins deux segments (3) de support de joint d'étanchéité, chacun en direction périphérique de la turbomachine, et où les segments (1) d'anneau de fixation et les segments (3) de support de joint d'étanchéité sont disposés frontalement les uns par rapport aux autres en direction périphérique,
    caractérisée en ce que :
    un premier segment (1) d'anneau de fixation présente un premier épaulement (27) de segment d'anneau, en ce qu'un deuxième segment (1) d'anneau de fixation présente un deuxième épaulement (27) de segment d'anneau décalé par rapport au premier épaulement (27) de segment d'anneau, en ce qu'un premier segment (3) de support de joint d'étanchéité présente un premier épaulement (15) de segment de support, en ce qu'un deuxième segment (3) de support de joint d'étanchéité présente un deuxième épaulement (15) de segment de support radialement décalé par rapport au premier épaulement (15) de segment de support, en ce que le premier épaulement (15) de segment de support est au moins partiellement en butée frontale contre le deuxième épaulement (27) de segment d'anneau dans un plan de séparation (29) de la virole (100), et en ce que le deuxième épaulement (15) de segment de support est au moins partiellement en butée frontale contre le premier épaulement (27) de segment d'anneau dans le plan de séparation (29), le premier épaulement (27) de segment d'anneau étant raccordé d'un seul tenant au premier segment (1) d'anneau de fixation et/ou le deuxième épaulement (27) de segment d'anneau étant raccordé d'un seul tenant au deuxième segment (1) d'anneau de fixation et/ou le premier épaulement (15) de segment de support étant raccordé d'un seul tenant au premier segment (3) de support de joint d'étanchéité et/ou le deuxième épaulement (15) de segment de support étant raccordé d'un seul tenant au deuxième segment (3) de support de joint d'étanchéité.
  2. Virole (100) selon la revendication 1, dans laquelle le premier et le deuxième segment (1) d'anneau de fixation présentent chacun un angle circonférentiel de 180° et/ou le premier et le deuxième segment (3) de support de joint d'étanchéité présentent chacun un angle circonférentiel de 180°.
  3. Virole (100) selon l'une des revendications précédentes, dans laquelle le premier épaulement (15) de segment de support est disposé à l'extrémité radialement extérieure du segment (3) de support de joint d'étanchéité et/ou le premier épaulement (27) de segment d'anneau est disposé à l'extrémité radialement extérieure du segment (1) d'anneau de fixation.
  4. Virole (100) selon l'une des revendications précédentes, dans laquelle le premier et/ou le deuxième épaulement (15) de segment de support et/ou le premier et/ou le deuxième épaulement (27) de segment d'anneau s'étendent respectivement sur toute la longueur périphérique du segment (3) de support de joint d'étanchéité ou du segment (1) d'anneau de fixation.
  5. Virole (100) selon l'une des revendications précédentes, dans laquelle le premier et/ou le deuxième épaulement (15) de segment de support sont disposés sur une partie (13), axialement en aval et à extension radiale, du segment (3) de support de joint d'étanchéité respectif.
  6. Virole (100) selon la revendication précédente, dans laquelle le rapport entre l'extension radiale et la largeur axiale de la partie (13) est au moins de 6:1.
  7. Virole (100) selon l'une des revendications précédentes, dans laquelle le premier et/ou le deuxième segment (1) d'anneau de fixation présentent au moins un alésage à une ou aux deux extrémités frontales en direction périphérique, l'alésage (17) étant prévu et configuré pour le logement d'une goupille (31) pour le raccord du segment (1) d'anneau de fixation.
  8. Virole (100) selon l'une des revendications précédentes, dans laquelle le premier et/ou le deuxième segment (3) de support de joint d'étanchéité présentent des joints d'entrée (7) réalisant une étanchéité par rapport à un fluide d'écoulement de la turbomachine axiale.
  9. Virole (100) selon l'une des revendications précédentes, dans laquelle les segments (3) de support de joint d'étanchéité et/ou les segments (1) d'anneau de fixation sont réalisés comme pièces rotatives.
  10. Stator d'une turbomachine avec des aubes de guidage (5) présentant une virole (100) selon l'une des revendications précédentes.
  11. Stator selon la revendication 10, ledit stator pouvant être raccordé à un carter d'un compresseur, en particulier d'un compresseur axial à haute pression.
EP13192465.6A 2013-11-12 2013-11-12 Virole interne d'une turbomachine et distributeur Active EP2871325B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13192465.6A EP2871325B1 (fr) 2013-11-12 2013-11-12 Virole interne d'une turbomachine et distributeur
US14/537,848 US9587499B2 (en) 2013-11-12 2014-11-10 Inner ring of a fluid flow machine and stator vane array

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13192465.6A EP2871325B1 (fr) 2013-11-12 2013-11-12 Virole interne d'une turbomachine et distributeur

Publications (2)

Publication Number Publication Date
EP2871325A1 EP2871325A1 (fr) 2015-05-13
EP2871325B1 true EP2871325B1 (fr) 2016-04-06

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EP13192465.6A Active EP2871325B1 (fr) 2013-11-12 2013-11-12 Virole interne d'une turbomachine et distributeur

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US (1) US9587499B2 (fr)
EP (1) EP2871325B1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3025124B1 (fr) * 2014-08-28 2016-09-30 Snecma Procede de fabrication de supports d'anneaux d'organe de turbomachine
US10358932B2 (en) * 2015-06-29 2019-07-23 United Technologies Corporation Segmented non-contact seal assembly for rotational equipment
DE102016215784A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Positionierungselement mit Aussparungen für eine Leitschaufelanordnung
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
US11879480B1 (en) 2023-04-07 2024-01-23 Rolls-Royce North American Technologies Inc. Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2452590A1 (fr) * 1979-03-27 1980-10-24 Snecma Garniture d'etancheite amovible pour segment de distributeur de turbomachine
US4767267A (en) * 1986-12-03 1988-08-30 General Electric Company Seal assembly
US6910854B2 (en) * 2002-10-08 2005-06-28 United Technologies Corporation Leak resistant vane cluster
GB0505978D0 (en) * 2005-03-24 2005-04-27 Alstom Technology Ltd Interlocking turbine blades
GB2426301B (en) * 2005-05-19 2007-07-18 Rolls Royce Plc A seal arrangement
DE102011102598A1 (de) * 2011-05-27 2012-11-29 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer Wabendichtung, Wabendichtung sowie Strömungsmaschine
FR2981602B1 (fr) * 2011-10-25 2017-02-17 Snecma Propulsion Solide Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs
EP2666969B1 (fr) * 2012-05-21 2017-04-19 General Electric Technology GmbH Structure de diaphragme de turbine

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US9587499B2 (en) 2017-03-07
EP2871325A1 (fr) 2015-05-13
US20150132124A1 (en) 2015-05-14

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