EP2360352A2 - Joint d'étanchéité sans vis d'une turbine à gaz - Google Patents

Joint d'étanchéité sans vis d'une turbine à gaz Download PDF

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Publication number
EP2360352A2
EP2360352A2 EP11001144A EP11001144A EP2360352A2 EP 2360352 A2 EP2360352 A2 EP 2360352A2 EP 11001144 A EP11001144 A EP 11001144A EP 11001144 A EP11001144 A EP 11001144A EP 2360352 A2 EP2360352 A2 EP 2360352A2
Authority
EP
European Patent Office
Prior art keywords
outer ring
inner ring
ring
holding elements
assembly according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP11001144A
Other languages
German (de)
English (en)
Other versions
EP2360352B1 (fr
EP2360352A3 (fr
Inventor
Thomas Schiessl
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
Publication of EP2360352A2 publication Critical patent/EP2360352A2/fr
Publication of EP2360352A3 publication Critical patent/EP2360352A3/fr
Application granted granted Critical
Publication of EP2360352B1 publication Critical patent/EP2360352B1/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
    • 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
    • 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
    • F05D2240/55—Seals
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb

Definitions

  • the invention relates to an interstage seal arrangement of a gas turbine, and more particularly to a gas turbine having a screwless interstage seal construction.
  • the prior art shows constructions in which the interstage seal assembly consists of two rings which are either individually secured to the vanes independently of each other or which are bolted together.
  • Another known embodiment is the division into two half-rings, which must be mounted after screwing the rotor disks.
  • split interstage seal rings an increased amount of processing is required. In particular, elaborate milling work is necessary. Such an assembly is matched with respect to their elements, so that individual elements (for example, half-rings) can not be replaced individually. Furthermore, such a system-inherently non-rotationally symmetrical construction is exposed during operation to asymmetrical thermal expansions, so that such components can deform from a circular shape into an oval shape. As a result, an increased cold gap may be required and thus result in increased leakage.
  • the invention has for its object to provide an intermediate stage seal arrangement of a gas turbine of the type mentioned, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and in particular has good structural properties.
  • the interstage seal arrangement has a (radially) outer ring, which is held both axially by guide vanes Also centered and thus stored, and a (radial) inner ring which is mounted on the outer ring comprises.
  • the terms (radially) outer and (radial) inner refer to the axis of rotation or machine axis.
  • front and rear reference is made to the direction of flow of the gas turbine, front thus means closer to the inlet region, while rear means closer to the outlet.
  • each of the rings namely the outer ring and the inner ring, is provided with at least one sealing area to perform the function of an interstage seal arrangement.
  • the invention provides that the inner ring on the outer ring by at least three radial tongue and groove connections, referred to below Radialnutenzentritation centered and is secured against rotation in the circumferential direction.
  • the planes of symmetry of all tongue and groove joints must all contain the main axis of rotation of the components involved to prevent deformation or damage. This principle corresponds to the state of the art and is u.a. also used for the centering of the outer ring by the vanes. It allows different thermal expansions of the components involved while ensuring coaxiality.
  • the circumferential groove in the outer ring can be designed for inserting retaining elements.
  • the circumferential groove is provided either over the entire peripheral region or over part of its circumference with a larger axial width, which makes it possible to introduce additional holding elements in addition to the strip of the guide vane.
  • additional holding elements At the periphery, for example, three such holding elements are provided which are sufficient to secure the inner ring against axial slipping when the engine is at a standstill.
  • the outer ring and / or the inner ring is provided at the respective contact area with a ring bead-shaped sealing projection.
  • inwardly facing retaining elements which are formed on the strip of the vane itself, either as pins which are pressed into radial bores of the strip, or as extensions of portions of the strip in the radial direction ,
  • retaining elements are pressed into radial holes of the outer ring and these pin-like holding elements take over the retention function for the inner ring.
  • the pin-like holding elements can be designed so that they ensure both the centering between guide vanes and outer ring and between the outer and inner ring.
  • the Fig. 1 shows a first embodiment in which an outer interstage seal ring 1 and an inner interstage seal ring 3 are provided, which respectively include respective sealing portions 4, 5, 6.
  • an outer interstage seal ring 1 and an inner interstage seal ring 3 are provided, which respectively include respective sealing portions 4, 5, 6.
  • sealing portions 4, 5, 6 With regard to the dimensioning of the construction of the sealing regions 4, 5, 6, reference may be made to the prior art.
  • the outer ring 1 comprises a circumferentially extending, radially outwardly open groove 12, in which a radially inwardly facing bar 11 of a foot of a guide vane 2 is inserted.
  • the guide vanes 2 are formed according to the prior art and segmented in the circumferential direction, wherein in each case a plurality of guide vanes 2 may have a common foot 16.
  • the Fig. 1 to 3 further show a disc 17 of a stage 1 of a turbine with rotor blades 19, and a disc 18 of a stage 2, which is located downstream of the intermediate stage seal assembly according to the invention, with rotor blades 20.
  • the discs 17, 18 and the rotor blades 19, 20 can the state the technique be referenced.
  • the outer ring 1 comprises a circumferentially extending, radially outwardly open groove 12 (see above), which is provided in the axial direction with an additional, widening groove 15, which merges into a recess 14 which extends radially inwardly opens.
  • a holding element 7 is inserted, which (see Fig. 2 ) Is T-shaped and the foot 21 passes through the recess 14. The Retaining element 7 is held by the strip 11 after its assembly and thus extends with its foot radially inwards.
  • the inner ring 3 Radially inward to the outer ring 1, the inner ring 3 is arranged. This rests against an annular projection 10 of the outer ring 1 and is thus supported in the axial direction.
  • the annular projection 10 thus forms an abutment leg and fixes the inner ring 3, wherein the inner ring 3 is provided on its radial outer side with a space for thermal expansion relative to the outer ring 1.
  • the inner ring 3 is fixed by the holding element 7. Distributed over the circumference, for example, three such retaining elements 7 are provided.
  • the Fig. 2 shows in simplified representation a view along the line AA-AA of Fig. 1 , As a result, it can be seen that the retaining element 7 is inserted into the groove 15 and is thus fixed radially, so that a reliable condition is ensured during operation of the gas turbine.
  • the construction according to the invention has the advantage that when mounting the interstage seal arrangement or the gas turbine, the inner ring 3 can be mounted on the outer ring 1 in a simple manner. Subsequently, the holding elements 7 are then inserted and the guide vanes 2 inserted.
  • the nose 28 on the inner ring 3 can be used in vertical mounting for holding the inner ring 3.
  • Fig. 3 shows a modified embodiment in which a holding element 8 is formed as a pin-shaped extension of the strip 11, which passes through the recess 14 and thus directly secures the inner ring 3 against displacement forward when the vane 2 is mounted. From the representation of Fig. 3 Thus, it follows that the several retaining elements 8 uniformly distributed around the circumference are part of the strip 11 (guide blade rail) and thus serve simultaneously as axial retaining elements for both the outer ring and the inner ring.
  • the respective holding element 9 is formed in the form of a pin which is pressed into a radial bore of the strip 11.
  • FIGS. 5 and 6 show by way of example a further modification variant of the solution according to the invention.
  • the same parts are again provided with the same reference numerals.
  • the inner 3 and outer 1 ring are brought into the illustrated position.
  • At least 3 holding elements 22 are now introduced from the outside into radial bores of the outer ring 1, wherein an inner part 26 of the holding element 22 engages in a groove of the inner ring 3.
  • all holding elements 22 are finally pressed into their stop in the outer ring 1, wherein a central part 25 of the holding member 22 and the corresponding bore in the outer ring 1 are designed as a press fit.
  • both rings 1, 3 are secured against each other and centered.
  • An outer part 23 of at least 3 holding elements 22 finally engages in radial grooves 27 of the guide blade 11, whereby the centering of the outer ring 1 and thus the entire assembly is ensured by the guide vanes 2.
  • recesses 24 are provided on the holding element, to which a removal tool can be attached.
  • a significant advantage results according to the invention in that the choice of material for the outer ring and for the inner ring can be optimized separately and thus, for example, an optimal splitting behavior for the inner ring, while the outer ring, a high temperature resistant material can be selected.
  • Another advantage may result in a weight saving as well as a reduction of the components and an associated reduction of the assembly costs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11001144.2A 2010-02-12 2011-02-11 Joint d'étanchéité sans vis d'une turbine à gaz Active EP2360352B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201010007724 DE102010007724A1 (de) 2010-02-12 2010-02-12 Schraubenlose Zwischenstufendichtung einer Gasturbine

Publications (3)

Publication Number Publication Date
EP2360352A2 true EP2360352A2 (fr) 2011-08-24
EP2360352A3 EP2360352A3 (fr) 2017-08-09
EP2360352B1 EP2360352B1 (fr) 2018-08-08

Family

ID=43708799

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11001144.2A Active EP2360352B1 (fr) 2010-02-12 2011-02-11 Joint d'étanchéité sans vis d'une turbine à gaz

Country Status (2)

Country Link
EP (1) EP2360352B1 (fr)
DE (1) DE102010007724A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2650482A1 (fr) * 2012-01-20 2013-10-16 General Electric Company Joint de trajet d'écoulement proche avec des bras flexibles axialement
EP2696039A1 (fr) * 2012-08-10 2014-02-12 MTU Aero Engines GmbH Étage de turbine à gaz
GB2540233A (en) * 2015-03-02 2017-01-11 Rolls Royce Plc Seal arrangement
EP3517734A1 (fr) * 2018-01-29 2019-07-31 MTU Aero Engines GmbH Module d'étanchéité pour une turbomachine
EP3885536A1 (fr) * 2020-03-25 2021-09-29 MTU Aero Engines AG Composant de turbine à gaz
CN116399526A (zh) * 2023-06-05 2023-07-07 中国航发四川燃气涡轮研究院 一种航空发动机导向叶片周向封严效果验证装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012014109A1 (de) 2012-07-17 2014-01-23 Rolls-Royce Deutschland Ltd & Co Kg Zwischenscheibendichtung einer Gasturbine
FR3106626B1 (fr) * 2020-01-24 2022-06-10 Safran Aircraft Engines Basculement differencié entre rotor et stator aux entrefers rotor-stator dans un compresseur de turbomachine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR957575A (fr) * 1946-10-02 1950-02-23
US5224822A (en) * 1991-05-13 1993-07-06 General Electric Company Integral turbine nozzle support and discourager seal
DE19931765A1 (de) * 1999-07-08 2001-01-11 Rolls Royce Deutschland Zweistufige oder mehrstufige Axialturbine einer Gasturbine
DE10214624C1 (de) * 2001-10-29 2003-03-27 Man Turbomasch Ag Ghh Borsig Vorrichtung zur Abdichtung in Turbomaschinen
JP3911571B2 (ja) * 2002-05-21 2007-05-09 川崎重工業株式会社 ガスタービンのシール方法およびシール構造
GB0424883D0 (en) * 2004-11-11 2004-12-15 Rolls Royce Plc Seal structure
FR2908153B1 (fr) * 2006-11-07 2011-05-13 Snecma Dispositif d'accrochage d'un distributeur (8) d'une turbine, turbine les comportant, et moteur d'aeronef en etant equipe

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2650482A1 (fr) * 2012-01-20 2013-10-16 General Electric Company Joint de trajet d'écoulement proche avec des bras flexibles axialement
US9080456B2 (en) 2012-01-20 2015-07-14 General Electric Company Near flow path seal with axially flexible arms
EP2696039A1 (fr) * 2012-08-10 2014-02-12 MTU Aero Engines GmbH Étage de turbine à gaz
GB2540233A (en) * 2015-03-02 2017-01-11 Rolls Royce Plc Seal arrangement
EP3517734A1 (fr) * 2018-01-29 2019-07-31 MTU Aero Engines GmbH Module d'étanchéité pour une turbomachine
US20190234225A1 (en) * 2018-01-29 2019-08-01 MTU Aero Engines AG Module for a turbomachine
US10844737B2 (en) * 2018-01-29 2020-11-24 MTU Aero Engines AG Additively manufactured module for a turbomachine
EP3885536A1 (fr) * 2020-03-25 2021-09-29 MTU Aero Engines AG Composant de turbine à gaz
US11585242B2 (en) 2020-03-25 2023-02-21 MTU Aero Engines AG Gas turbine component
CN116399526A (zh) * 2023-06-05 2023-07-07 中国航发四川燃气涡轮研究院 一种航空发动机导向叶片周向封严效果验证装置
CN116399526B (zh) * 2023-06-05 2023-09-01 中国航发四川燃气涡轮研究院 一种航空发动机导向叶片周向封严效果验证装置

Also Published As

Publication number Publication date
EP2360352B1 (fr) 2018-08-08
DE102010007724A1 (de) 2011-08-18
EP2360352A3 (fr) 2017-08-09

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