EP1319844A1 - Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compressuer haute pression d'une turbine à gaz - Google Patents

Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compressuer haute pression d'une turbine à gaz Download PDF

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Publication number
EP1319844A1
EP1319844A1 EP02023209A EP02023209A EP1319844A1 EP 1319844 A1 EP1319844 A1 EP 1319844A1 EP 02023209 A EP02023209 A EP 02023209A EP 02023209 A EP02023209 A EP 02023209A EP 1319844 A1 EP1319844 A1 EP 1319844A1
Authority
EP
European Patent Office
Prior art keywords
cover body
bearing ring
support element
ring according
mounting
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
EP02023209A
Other languages
German (de)
English (en)
Other versions
EP1319844B1 (fr
Inventor
Norbert Wolf
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 EP1319844A1 publication Critical patent/EP1319844A1/fr
Application granted granted Critical
Publication of EP1319844B1 publication Critical patent/EP1319844B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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

Definitions

  • the invention relates to a bearing ring for storage of blade feet of adjustable stator blades in the high pressure compressor a gas turbine, and in particular on a bearing ring according to the features of the preamble of Main claim.
  • the invention relates to a bearing ring (Shroud), as it is especially the case with high-pressure compressors in modern turbofan engines for internal storage of the adjustable stator blades is used in the field of high pressure compressors.
  • Such bearing rings or shrouds are usually made Aluminum, made of steel alloys or titanium. A Construction of this type is shown, for example, in US Pat. No. 5,062,767 A.
  • the bearing rings are usually made up of two parts, so that a front and a rear base body are present are. These basic bodies are each ring-shaped.
  • Weight reduction is an axial annulus, which for example, is turned out. Air turbulence, vibrations and to reduce noise, becomes the annulus provided with a rubber filling in the prior art. This is applied by means of a vulcanization process.
  • the invention has for its object a bearing ring to create the type mentioned, which with a simple structure and simple, inexpensive to manufacture the disadvantages avoids the prior art and in particular a has low weight.
  • the object is achieved by the combination of features of the main claim solved, the sub-claims show more advantageous embodiments of the invention.
  • annular cover body in the opening area an annular cover body is arranged in the annular space, which is provided with mounting recesses. Still is provided that in the intermediate area between the mounting recess the cover body and the associated mounting hole of the base body, a tubular support element is arranged.
  • the bearing ring according to the invention is characterized by a number significant benefits.
  • Another major advantage is that there are no age-prone ones Materials such as rubber reach. This increases reliability as well the lifespan.
  • Another advantage is the weight reduction to be achieved, because far less material is required than with a filling with rubber or other filling materials.
  • cover body according to the invention for covering in the mouth area of the annulus are not used constructive changes to the base body required. It is thus possible to remove existing basic bodies after removal to convert the rubber filling accordingly.
  • cover body at all times can be easily removed and reinserted, for example during maintenance or other work.
  • the cover body essentially in the form of a flat ring is formed. This can be done in simpler Made for example from a metallic sheet be made, for example, of aluminum or titanium. Especially It is also favorable if the cover body at least on its Is profiled edges. A crimp or a Edge can thus be a particularly advantageous clamping or lead to a press fit so that the cover body is reliable can be used in the annulus.
  • stiffening measures such as beads or the like be used.
  • the support element is preferably cup-shaped or cone-shaped educated. It can be made just like the cover body a metal sheet, by rolling or deep drawing or be produced using a similar forming process. It when the free edge area of the Support element for holding the cover body is profiled, for example bent or flanged. The support element is anchored thus the cover body and clamps it against the Basic body in front, so that there is a secure attachment.
  • the pre-tensioning is done by means of connecting screws, which too serve to brace the two base bodies of the bearing ring.
  • the dimensioning of the support body is preferably so chosen that they are slightly shorter than the depth of the Annulus of the basic body. The gap dimension can, for example 0.5 mm. The screw connection thus results in a Preload of the cover body.
  • cover body and the support elements can be in one piece or be formed in several parts. Instead of the production described made of metallic materials, it is also possible Cover body and / or the support elements made of plastic or to produce similar material, for example by means of a Spraying process.
  • Area A marks the positioning of a bearing ring for the storage of stator blades 2.
  • the schematically indicated components can be omitted because they are known from the prior art.
  • Fig. 2 is a perspective exploded view Shown from the prior art bearing ring shown one front base 3 and a rear base 4 includes.
  • the two base bodies 3, 4 are each on the end face turned out and with a rubber filling 12 in the formed here Annulus 5 provided.
  • In the two basic bodies 1, 2 are each half recesses 14 made (see Fig. 3) serve to support bushings 13, which in turn store a blade root 1 of the respective stator blade 2.
  • the stator blades 2 are rotatable in a known manner, around the To be able to change the angle of attack. This is the performance of the compressor or compressor to the operating conditions customizable.
  • the two base bodies 3, 4 are screwed together by means of a variety of screws 15 and nuts 16.
  • corresponding mounting holes 6 are provided in the base bodies 3, 4.
  • FIG. 4 shows a simplified sectional view of the invention Design of the bearing ring. This includes how already described, a front body 3 and one rear base body 4. These are each with the named Provide mounting holes 6. 4 also shows the two substantially U-shaped annular spaces 5, each axially are open.
  • FIG. 4 is a substantially flat, annular cover body 7 (see also Fig. 5 and 6), which provided with a corresponding number of mounting recesses 8 is aligned with the mounting holes 6 to the To be able to carry out screws 15.
  • a hat-shaped or cup-shaped support element 9 which, as well 7 with a central recess 17 is provided in order to be able to carry out the screw 15.
  • an edge 10 of the cover body 7 is profiled or bent to ensure a tight fit to ensure in the annulus 5.
  • Edge area 11 of support element 9 bent or profiled, to hold and pretension the cover body 7.
  • the length of the support element 9 is slightly smaller than the available depth in the annular space 5, so that when tightening the screw 15 a corresponding bracing of the cover body 7 results.
  • FIG. 6 shows a partial perspective view of the ring-shaped one Cover body 7, while in the illustration of FIG. 5 in a schematic manner, the individual support elements 9 additionally to the cover body 7 are shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP02023209A 2001-12-13 2002-10-16 Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz Expired - Fee Related EP1319844B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10161292A DE10161292A1 (de) 2001-12-13 2001-12-13 Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
DE10161292 2001-12-13

Publications (2)

Publication Number Publication Date
EP1319844A1 true EP1319844A1 (fr) 2003-06-18
EP1319844B1 EP1319844B1 (fr) 2009-12-02

Family

ID=7709105

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02023209A Expired - Fee Related EP1319844B1 (fr) 2001-12-13 2002-10-16 Bague extérieure pour recevoir des pieds d'aubes de volets redresseurs dans un compresseur haute pression d'une turbine à gaz

Country Status (3)

Country Link
US (1) US6790000B2 (fr)
EP (1) EP1319844B1 (fr)
DE (2) DE10161292A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007134585A1 (fr) * 2006-05-23 2007-11-29 Mtu Aero Engines Gmbh Turbocompresseur en montage axial
EP1705341A3 (fr) * 2005-03-05 2009-03-25 Rolls-Royce plc Anneau pivot
EP2261467A3 (fr) * 2009-06-05 2013-07-31 United Technologies Corporation Ensemble d'enveloppe de diamètre interne pour structure d'aube d'entrée variable dans une turbine à gaz
FR3009335A1 (fr) * 2013-07-30 2015-02-06 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine
WO2015149732A2 (fr) 2014-03-31 2015-10-08 MTU Aero Engines AG Couronne d'aubes fixes, bague intérieure et turbomachine

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10353810A1 (de) * 2003-11-17 2005-06-23 Rolls-Royce Deutschland Ltd & Co Kg Innendeckband für die Statorschaufeln des Verdichters einer Gasturbine
DE10358421A1 (de) * 2003-12-13 2005-07-07 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
US7665959B2 (en) * 2005-07-20 2010-02-23 United Technologies Corporation Rack and pinion variable vane synchronizing mechanism for inner diameter vane shroud
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring variable vane synchronizing mechanism for inner diameter vane shroud
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7690889B2 (en) * 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
US7510369B2 (en) * 2005-09-02 2009-03-31 United Technologies Corporation Sacrificial inner shroud liners for gas turbine engines
EP1811134A1 (fr) * 2006-01-23 2007-07-25 ABB Turbo Systems AG Dispositif de guidage réglable
US7713022B2 (en) * 2007-03-06 2010-05-11 United Technologies Operations Small radial profile shroud for variable vane structure in a gas turbine engine
US8777561B2 (en) 2010-11-05 2014-07-15 Hamilton Sundstrand Corporation Compressor shroud having a retention cover channel for receiving a retention cover
US9957832B2 (en) 2012-02-28 2018-05-01 United Technologies Corporation Variable area turbine
EP2644833A1 (fr) * 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
EP3971402A1 (fr) 2012-09-20 2022-03-23 Raytheon Technologies Corporation Module de système d'engrenage d'entraînement de soufflante et mécanisme d'accouplement d'aube de guidage d'entrée
WO2014143445A2 (fr) * 2013-02-10 2014-09-18 United Technologies Corporation Enveloppe de recouvrement d'aube fixe à incidence variable
WO2015077011A1 (fr) 2013-11-19 2015-05-28 United Technologies Corporation Extension de carénage interne à éléments multiples pour une turbomachine
FR3014152B1 (fr) * 2013-11-29 2015-12-25 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
US10072746B2 (en) * 2015-05-05 2018-09-11 Valeo Embrayages Stator assembly of hydrokinetic torque converter, and method for making the same
EP3176386B1 (fr) 2015-12-04 2021-01-27 MTU Aero Engines GmbH Système de virole interne, virole interne, boîtier intermédiaire et turbomachine associés
DE102016215807A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Innenring für einen Leitschaufelkranz einer Strömungsmaschine
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
DE102017209682A1 (de) * 2017-06-08 2018-12-13 MTU Aero Engines AG Axial geteilter Turbomaschinen-Innenring
US10526911B2 (en) * 2017-06-22 2020-01-07 United Technologies Corporation Split synchronization ring for variable vane assembly
DE102018203442A1 (de) * 2018-03-07 2019-09-12 MTU Aero Engines AG Innenring für eine Turbomaschine, Leitschaufelkranz mit einem Innenring, Turbomaschine und Verfahren zur Herstellung eines Innenrings
BE1026411B1 (fr) * 2018-06-21 2020-01-30 Safran Aero Boosters Sa Virole extérieure de turbomachine
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
US11608747B2 (en) 2021-01-07 2023-03-21 General Electric Company Split shroud for vibration reduction
US11572794B2 (en) 2021-01-07 2023-02-07 General Electric Company Inner shroud damper for vibration reduction
US11629606B2 (en) * 2021-05-26 2023-04-18 General Electric Company Split-line stator vane assembly
CN113898419A (zh) * 2021-10-10 2022-01-07 中国航发沈阳发动机研究所 一种进气机匣结构及其组装方法
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

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US3824034A (en) * 1971-05-03 1974-07-16 Mtu Friedrichshafen Gmbh Guide blade ring
US4514141A (en) * 1982-04-08 1985-04-30 S.N.E.C.M.A. Safety stop for a variable setting stator blade pivot
US5328327A (en) * 1991-12-11 1994-07-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator for directing the inlet of air inside a turbo-engine and method for mounting a vane of said stator
US5636968A (en) * 1994-08-10 1997-06-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for assembling a circular stage of pivoting vanes
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane
US6129512A (en) * 1998-03-05 2000-10-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Circular stage of vanes connected at internal ends thereof by a connecting ring

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FR2582720B1 (fr) * 1985-05-29 1989-06-02 Snecma Procede de realisation de pivot d'aube de turbomachine et aube de stator le comportant
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US5279031A (en) * 1988-12-06 1994-01-18 Alliedsignal Inc. High temperature turbine engine structure
US5062767A (en) * 1990-04-27 1991-11-05 The United States Of America As Represented By The Secretary Of The Air Force Segmented composite inner shrouds
US5421703A (en) 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
CA2231986A1 (fr) * 1997-01-10 1999-09-12 Masahito Kataoka Pale fixe a secteur porte-aubes integre et methode de fabrication
US6164903A (en) * 1998-12-22 2000-12-26 United Technologies Corporation Turbine vane mounting arrangement

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3824034A (en) * 1971-05-03 1974-07-16 Mtu Friedrichshafen Gmbh Guide blade ring
US4514141A (en) * 1982-04-08 1985-04-30 S.N.E.C.M.A. Safety stop for a variable setting stator blade pivot
US5328327A (en) * 1991-12-11 1994-07-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator for directing the inlet of air inside a turbo-engine and method for mounting a vane of said stator
US5636968A (en) * 1994-08-10 1997-06-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Device for assembling a circular stage of pivoting vanes
US6129512A (en) * 1998-03-05 2000-10-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Circular stage of vanes connected at internal ends thereof by a connecting ring
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1705341A3 (fr) * 2005-03-05 2009-03-25 Rolls-Royce plc Anneau pivot
US7802963B2 (en) 2005-03-05 2010-09-28 Rolls-Royce Plc Pivot ring
WO2007134585A1 (fr) * 2006-05-23 2007-11-29 Mtu Aero Engines Gmbh Turbocompresseur en montage axial
US8376692B2 (en) 2006-05-23 2013-02-19 Mtu Aero Engines Gmbh Turbo compressor in an axial type of construction
EP2261467A3 (fr) * 2009-06-05 2013-07-31 United Technologies Corporation Ensemble d'enveloppe de diamètre interne pour structure d'aube d'entrée variable dans une turbine à gaz
US8951010B2 (en) 2009-06-05 2015-02-10 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
FR3009335A1 (fr) * 2013-07-30 2015-02-06 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine
GB2518945A (en) * 2013-07-30 2015-04-08 Snecma A device for guiding variable pitch diffuser vanes of a turbine engine
US9926944B2 (en) 2013-07-30 2018-03-27 Snecma Device for guiding variable pitch diffuser vanes of a turbine engine
GB2518945B (en) * 2013-07-30 2020-04-08 Snecma A device for guiding variable pitch diffuser vanes of a turbine engine
WO2015149732A2 (fr) 2014-03-31 2015-10-08 MTU Aero Engines AG Couronne d'aubes fixes, bague intérieure et turbomachine
US10364827B2 (en) 2014-03-31 2019-07-30 MTU Aero Engines AG Guide vane ring, guide vane, inner ring and turbomachine

Also Published As

Publication number Publication date
DE50214035D1 (de) 2010-01-14
DE10161292A1 (de) 2003-06-26
EP1319844B1 (fr) 2009-12-02
US6790000B2 (en) 2004-09-14
US20030113204A1 (en) 2003-06-19

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