EP1694943A2 - Turbomoteur, notamment turbine a gaz - Google Patents

Turbomoteur, notamment turbine a gaz

Info

Publication number
EP1694943A2
EP1694943A2 EP04802843A EP04802843A EP1694943A2 EP 1694943 A2 EP1694943 A2 EP 1694943A2 EP 04802843 A EP04802843 A EP 04802843A EP 04802843 A EP04802843 A EP 04802843A EP 1694943 A2 EP1694943 A2 EP 1694943A2
Authority
EP
European Patent Office
Prior art keywords
housing
guide
guide pins
fork
turbomachine
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
EP04802843A
Other languages
German (de)
English (en)
Other versions
EP1694943B1 (fr
Inventor
Gerhard BRÜCKNER
Manfred Feldmann
Bernd Kislinger
Joachim Wulf
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 GmbH
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 GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1694943A2 publication Critical patent/EP1694943A2/fr
Application granted granted Critical
Publication of EP1694943B1 publication Critical patent/EP1694943B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1. Furthermore, the invention relates to an assembly device for a turbomachine.
  • Turbomachines for example gas turbines, have a rotor and a stator, the rotor rotating together with the rotating blades and the stator having a housing and guide blades.
  • the rotor blades assigned to the rotor rotate with respect to the stationary housing and the stationary guide blades of the stator.
  • the guide vanes form guide vane rings and the rotor blades form rotor vane rings, with one rotor vane ring each being positioned between two guide vane rings arranged one behind the other in the direction of flow.
  • the guide vane rings adjoin the housing with a radially outer end, in particular with an outer shroud, and with a radially inner end, in particular with an inner shroud, on the rotor.
  • the guide vane rings must be attached to the housing of the turbomachine and spoke centered in relation to the housing.
  • DE 98 07 247 A1 discloses such a turbomachine, bearing journals being provided for centering and fixing the guide vane rings.
  • the bearing journals fixed to the housing penetrate the housing of the turbomachine and engage bearing bushes assigned to the guide vane rings in the guide vane rings for centering the spoke.
  • the guide pins penetrate the housing of the turbomachine in the radial direction, a longitudinal central axis of the bearing bushes therefore runs parallel to the radial direction of the turbomachine, the corresponding bearing bushes also being aligned in the radial direction of the turbomachine.
  • seal carriers are positioned between two adjacent guide vane rings, the seal carriers being suspended in the outer shrouds of the guide vane rings.
  • the present invention is based on the problem of creating a new type of turbomachine.
  • This problem is solved in that the turbomachine mentioned at the outset is further developed by the features of the characterizing part of patent claim 1.
  • the guide pins extend approximately perpendicular to the Geotrou ⁇ se, wherein the guide pins assigned to the housing projecting into the ends of the radially outer ends of the guide vane, engage fork-shaped elements.
  • the guide pins run approximately perpendicular to the housing and obliquely to the radial direction and axial direction of the turbomachine.
  • both the guide vane rings and seal carriers are spoke-centered with the aid of the guide pins and / or the fork-shaped elements, each fork-shaped element preferably delimits at least two recesses or receiving spaces, with the guide pins in a first recess and with projections of the seal carriers in engage a second recess.
  • the two recesses of the fork-shaped elements are positioned next to one another in the circumferential direction.
  • the guide pins for the spoke centering of the guide vane rings are aligned perpendicular to the housing of the turbomachine, the guide pins accordingly do not run in the radial direction of the turbomachine, but on the one hand at an angle to the radial direction and on the other hand at an angle to the axial direction of the turbomachine.
  • the ends of the guide pins protruding into the housing therefore also run obliquely to the axial direction and radial direction of the turbomachine and interact with fork-shaped elements in the region of the guide vane rings, the fork-shaped elements being at least partially open in the radial direction and axial direction of the turbomachine in order to engage the Enabling housing protruding ends of the guide pins into the fork-shaped elements.
  • the mounting device according to the invention is defined in claim 13.
  • FIG. 2 a highly schematic detail of the arrangement according to FIG. 1 in the area of an outer shroud of a guide vane grille and an “outer airseal” seal in a perspective view;
  • the present invention is described in greater detail below with reference to FIGS. 1 to 3.
  • the present invention is generally suitable for all turbo machines or turbo machines with a rotor and stator.
  • the invention is suitable for use in a compressor or a turbine of a gas turbine, in particular an aircraft engine.
  • FIG. 1 shows a partial, axial longitudinal section through a low-pressure turbine.
  • FIG. 1 shows a section of a low-pressure turbine 10 in the area of two guide vane rings 11 and 12 and two rotor blade rings 13 and 14.
  • the guide Blade rings 1 1 and 12 and blade rings 13 and 14 are alternately positioned one behind the other in the axial direction of the low-pressure turbine 10.
  • the axial direction of the low-pressure turbine 10 is shown in FIG. 1 by an arrow 15, the radial direction thereof by an arrow 16.
  • Each of the guide vane rings 11 and 12 is formed by a plurality of guide vanes 17 arranged next to one another in the circumferential direction of the low-pressure turbine 10, FIG. 1 only showing the radially outer ends 18 of the guide vanes 17. So-called outer shrouds 19 are formed in the region of the radially outer ends 18 of the guide vanes V.
  • the guide vane rings 11 and 12 are assigned to a stator of the low-pressure turbine 10, the stator also comprising a housing 20 in addition to the guide vanes 17 of the guide vane rings 11 and 12.
  • the housing 20 and the guide vane rings 11 and 12 are designed to be stationary, the rotor vane rings 13 and 14 assigned to a rotor rotating relative to the stationary guide vane rings 11 and 12 and the fixed housing 20.
  • Each of the rotating rotor blade rings 13 and 14 is formed by a plurality of rotor blades 21 arranged side by side in the circumferential direction of the low-pressure turbine 10, FIG. 1 again showing only the radially outer ends 22 of the rotor blades 21. In the region of the radially outer ends 22 of the rotor blades 21, so-called outer shrouds 23 are again formed.
  • the centering and fixing of the guide vane rings 11 and 12 takes place via bearing journals or guide pins 24, the guide pins 24 running approximately perpendicular to the housing 20.
  • a longitudinal central axis 25 of the guide pins 24 is approximately perpendicular to the housing 20 and accordingly runs obliquely to the radial direction (arrow 16) and axial direction (arrow 15) of the low-pressure turbine 10.
  • the guide pins 24 protrude at ends 26 the housing 20 into it and engage for centering and fixing the guide vane rings 1 1 and 12 in fork-shaped elements 27 which are assigned to the outer cover bands 19 of the guide vane rings 1 1 and 12.
  • a plurality of fork-shaped elements 27 are positioned over the circumference of the outer shrouds of the guide vane rings 11 and 12, with a corresponding guide in each of the fork-shaped elements 27 of a guide vane ring 11 and 12.
  • tion pin 24 engages, the guide pins 24 are arranged corresponding to the fork-shaped elements 27 distributed over the circumference of the housing.
  • At least three guide pins 24, which are arranged distributed over the circumference of the low-pressure turbine 10 and which cooperate with corresponding fork-shaped elements 27 in the area of the outer shrouds 19 of the guide vane rings 11 and 12, are required for centering the spokes of a guide vane ring 11 or 12.
  • seven such pairs of guide pins 24 and fork-shaped elements 27 are arranged distributed over the circumference of the low-pressure turbine 10 per guide vane ring 11 and 12.
  • the fork-shaped elements 27 in the area of the outer shrouds 19 of the guide vane rings 11 and 12 are at least partially open in the radial direction and in the axial direction of the low-pressure turbine 10 in order to enable the ends 26 of the guide pins 24 protruding into the housing 20 to engage in the fork-shaped elements 27 ,
  • the fork-shaped elements 27 of the guide vane rings 1 1 and 12 together with the guide pins 24 not only fix and center the guide vane rings 1 1 and 12 on the housing, but rather also fix and center the seal carriers 28 between them adjacent outer shrouds 18 adjacent guide vane rings 1 1 and 12 are arranged.
  • the seal carriers 28 carry sealing bodies 29 designed as honeycomb seals, which cooperate with so-called sealing fins 30 in the region of the outer shrouds 23 of the rotor rings 13 and 14 and seal a gap between the radially outer ends 22 of the rotor blades 21 and the housing 20 cause the low pressure turbine 10.
  • FIG. 2 shows a fork-shaped element 27 in the region of an outer shroud 19 of a guide vane ring and a section of a seal carrier 28, the so-called outer Airseal seal forms.
  • the fork-shaped element 27 has two recesses 31 and 32.
  • the two recesses 31 and 32 are partially open both in the radial direction and in the axial direction of the low-pressure turbine 10 and are arranged next to one another in the circumferential direction thereof.
  • the ends of the guide pins 24 engage in a first recess 31.
  • At least one stop is provided, the or each stop preferably being integrated in one of the fork-shaped elements 27.
  • the or each stop limits the axial mobility of the guide vane rings 1 1 and 12 to a minimum.
  • the guide pins 24 or bearing journals are assigned to the housing 20 of the low-pressure turbine 10 and project with their free ends 26 into the interior of the low-pressure turbine 10.
  • bores are integrated in the housing 20, the bores running perpendicular to the housing 20.
  • Nuts 34 are assigned to the guide pins 24 on the outside of the housing 20. With loosened nuts 34, the guide pins 24 can move within the bores of the housing 20, whereas with tightened nuts 34 the guide pins 24, in particular the free ends 26 thereof, are fixed in their relative position to the housing 20.
  • FIG 3 shows a section of the housing 20 of the low-pressure turbine 10 together with two guide pins 24 and a mounting device 35 according to the invention, the mounting device 35 aligning or adjusting the guide pins 24 or the free ends 26 of the guide pins 24 relative to the housing 20 serves. Alignment or adjustment of the free ends 26 of the guide pins 24 is necessary with regard to the later assembly or spoke centering of the guide vane rings 11 and 12 so that the free ends 26 of the guide pins 24 are inserted into the recesses 31 of the fork-shaped elements 27 in a positionally accurate manner can be.
  • the mounting device 35 has a plate-shaped base body 36. At least two recesses 37 are integrated in the plate-shaped base body 36. To align or adjust the free ends 26 of the guide pins 24, the guide pins 24 are inserted with their free ends 26 into the recesses 37 of the plate-shaped base body 36 of the mounting device 35. 3, for this purpose the plate-shaped base body 36 of the mounting device 35 is brought into engagement with the free ends 26 of the guide pins 24 on an inner side 38 of the housing 20 such that the ends 26 bring the base body 36 perpendicular to a plane defined by the plate-shaped base body 36 penetrate and are held against rotation in the recesses 37 of the plate-shaped base body 36.
  • the assembly device 35 can be brought out of engagement with the free ends 26 by the assembly device 35 tangential to that through the plate-shaped base body 36 defined level is brought out of engagement with the free ends 26 of the guide pins.
  • the assembly device 34 is accordingly moved such that it is moved in the plane defined by the plate-shaped base body 36 and the free ends 26 are moved out of the recesses 37 within the plate-shaped base body 36.
  • To handle the To facilitate assembly device 35 it has a handle 40 which extends approximately perpendicular to the plate-shaped base body 36.

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)

Abstract

L'invention concerne un turbomoteur, notamment une turbine à gaz, qui comprend un stator et un rotor, le rotor étant doté d'aubes (21) et le stator étant pourvu d'un carter (20) et d'aubes fixes (17). Les aubes fixes (17) forment des couronnes (11, 12) dont les extrémités radiales externes (18) sont contiguës au carter (20) et les extrémités radiales internes sont adjacentes au rotor. Les couronnes d'aubes fixes sont centrées par rayons au moyen de tourillons ou de chevilles (24) associés au carter (20) qu'ils traversent. Selon l'invention, les chevilles (24) sont pratiquement perpendiculaires au carter (20), et leurs extrémités (26) qui pénètrent dans le carter sont en prise avec des éléments (27) fourchus associés aux extrémités radiales externes (18) des couronnes (11, 12) d'aubes fixes.
EP04802843.5A 2003-12-19 2004-11-27 Turbomachine Active EP1694943B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10359730A DE10359730A1 (de) 2003-12-19 2003-12-19 Turbomaschine, insbesondere Gasturbine
PCT/DE2004/002634 WO2005059312A2 (fr) 2003-12-19 2004-11-27 Turbomoteur, notamment turbine a gaz

Publications (2)

Publication Number Publication Date
EP1694943A2 true EP1694943A2 (fr) 2006-08-30
EP1694943B1 EP1694943B1 (fr) 2013-05-29

Family

ID=34672913

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04802843.5A Active EP1694943B1 (fr) 2003-12-19 2004-11-27 Turbomachine

Country Status (5)

Country Link
US (1) US7704042B2 (fr)
EP (1) EP1694943B1 (fr)
CA (1) CA2548489A1 (fr)
DE (1) DE10359730A1 (fr)
WO (1) WO2005059312A2 (fr)

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DE102009037620A1 (de) * 2009-08-14 2011-02-17 Mtu Aero Engines Gmbh Strömungsmaschine
US8316523B2 (en) * 2009-10-01 2012-11-27 Pratt & Whitney Canada Corp. Method for centering engine structures
RU2543101C2 (ru) * 2010-11-29 2015-02-27 Альстом Текнолоджи Лтд Осевая газовая турбина
US8905711B2 (en) * 2011-05-26 2014-12-09 United Technologies Corporation Ceramic matrix composite vane structures for a gas turbine engine turbine
US9175571B2 (en) 2012-03-19 2015-11-03 General Electric Company Connecting system for metal components and CMC components, a turbine blade retaining system and a rotating component retaining system
US9896971B2 (en) * 2012-09-28 2018-02-20 United Technologies Corporation Lug for preventing rotation of a stator vane arrangement relative to a turbine engine case
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case
ES2581511T3 (es) * 2013-07-15 2016-09-06 Mtu Aero Engines Gmbh Turbomáquina, segmento de sellado y segmento de álabe de guía
DE102014209057A1 (de) 2014-05-14 2015-11-19 MTU Aero Engines AG Gasturbinengehäuseanordnung
JP5717904B1 (ja) * 2014-08-04 2015-05-13 三菱日立パワーシステムズ株式会社 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法
EP2998517B1 (fr) * 2014-09-16 2019-03-27 Ansaldo Energia Switzerland AG Agencement d'étanchéité au niveau de l'interface entre une chambre de combustion et une turbine d'une turbine à gaz et turbine à gaz avec un tel agencement d'étanchéité
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DE102016201766A1 (de) * 2016-02-05 2017-08-10 MTU Aero Engines AG Leitschaufelsystem für eine Strömungsmaschine
US10415414B2 (en) * 2016-03-16 2019-09-17 United Technologies Corporation Seal arc segment with anti-rotation feature
EP3228837B1 (fr) * 2016-04-08 2019-08-28 Ansaldo Energia Switzerland AG Ensemble de composants de moteur turbomachine
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US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
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US11939888B2 (en) * 2022-06-17 2024-03-26 Rtx Corporation Airfoil anti-rotation ring and assembly

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Also Published As

Publication number Publication date
DE10359730A1 (de) 2005-07-14
WO2005059312A3 (fr) 2005-09-01
WO2005059312A2 (fr) 2005-06-30
EP1694943B1 (fr) 2013-05-29
US7704042B2 (en) 2010-04-27
CA2548489A1 (fr) 2005-06-30
US20070122270A1 (en) 2007-05-31

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