EP1531234A1 - Virole interne pour les aubes statoriques d'un compresseur de turbine à gaz - Google Patents

Virole interne pour les aubes statoriques d'un compresseur de turbine à gaz Download PDF

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Publication number
EP1531234A1
EP1531234A1 EP04090415A EP04090415A EP1531234A1 EP 1531234 A1 EP1531234 A1 EP 1531234A1 EP 04090415 A EP04090415 A EP 04090415A EP 04090415 A EP04090415 A EP 04090415A EP 1531234 A1 EP1531234 A1 EP 1531234A1
Authority
EP
European Patent Office
Prior art keywords
inner cover
cover tape
sealing
tape according
plastic
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
EP04090415A
Other languages
German (de)
English (en)
Other versions
EP1531234B1 (fr
Inventor
Ingo Jahns
Olaf Lenk
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 EP1531234A1 publication Critical patent/EP1531234A1/fr
Application granted granted Critical
Publication of EP1531234B1 publication Critical patent/EP1531234B1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • F04D29/08—Sealings
    • 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
    • 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
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the invention relates to an inner cover strip for the stator blades a gas turbine, in particular an air turbine, the Means for rotatably supporting the stator blades and for sealing between the rotor stages and with respect to one having secondary air system.
  • a gas turbine In a gas turbine is, for example, in the combustion chamber upstream compressor, between the adjacent Rotor stages each arranged a vane ring.
  • the front steps of the vanes are adjustable.
  • the adjustable vanes are via pivot pins stored in the compressor housing.
  • the inner cover tape At the inner pivot of the Guide vanes, the inner cover tape is arranged. With the adjustable Vanes, the air is diverted so that at an optimum angle to the subsequent rotor stage meets.
  • inner cover tape for the stator blade ring is usually made up of two semicircular ring segments assembled, which also executed divided in the axial direction can be and in this case after mounting through suitable fasteners are connected together.
  • the inner cover tape serves as a rotatable support the respective stator blade via a connected thereto Pivot, which fixed in a in the inner shroud Plain bearing bush is stored.
  • the formation of the inner cover tape made of a metallic material ensures both the required mechanical properties such as stiffness and Strength and also ensures a high resistance against erosion or foreign body impact.
  • a Another important function of the inner cover tape is in its Sealing effect against the rotor to prevent recirculation the compressed air from the area higher Pressure in the area of lower pressure.
  • the inner cover bands of the type described above have about the required strength and thermal expansion properties, but are disadvantageous insofar as their production by forging and subsequent machining time consuming and expensive and the inner cover tape also has a high weight.
  • the production cost is on the other hand very high, that the plain bearing bushes and Seals separately manufactured components are, on the one hand are expensive and also used separately or mounted.
  • the invention is based on the object, an inner cover tape for the stator blades of the compressor of a gas turbine, which has a low weight, simple and inexpensive can be made and over all required Characteristics in terms of thermal expansion, strength, the temperature resistance, resistance to Foreign body action as well as the slide bearing and sealing features.
  • the essential idea of the invention is the training the inner cover band from a known injection molding process or another suitable process, one-piece plastic part, in the achieve the various functions of the inner cover tape additives such as glass and / or carbon fibers and / or Graphite or prefabricated solid inserts that function of the respective part of the inner cover, are involved.
  • certain additives are specific Part of the plastic part, which has a specific Function, concentrated. So is in the of the air flow directly applied area of the inner cover tape a wear protection layer of incorporated in the plastic long fibers or from a prefabricated, when Injection molded molded wear protection plate formed.
  • the plastic integrates a running-in layer, made either of the base material, an accumulation of during manufacture in high concentration introduced additives or from a prefabricated, molded during manufacture Molded part with inlet properties compared to those on the rotor Dense tips exists.
  • the seal to the secondary Air system may be due to the formation of the inner cover tape from a plastic part, preferably with one of these molded elastic sealing lip made due to the additives (concentration or type of additives) the has required elasticity and due to the prevailing Can apply air pressure to a sealing surface.
  • the Plastic also has the beneficial property of being, like required for the inner cover tape, under heat expand.
  • the additives present in the plastic material In addition, however, also ensure that the thermal expansion of the inner cover strip to the thermal expansion of the adjacent Components, is adjusted.
  • the one-piece made of plastic with the necessary additives or prefabricated inserts by injection molding or other suitable method produced inner shroud will be appropriate the heat load capacity of the plastic used, preferably in the first stages of the compressor of a jet turbine. Particularly advantageous are the low weight and the simple, cost-effective production of such a trained Inner shroud.
  • the material supply spatially and temporally, so controlled that in certain areas of the mold plastic material with a given proportion of additives passes.
  • Prefabricated inserts for certain functional areas of the mold are in the mold is inserted and during the casting process in the plastic material formed.
  • the inner cover tape consists of two semicircular plastic parts, the total of the annular inner shroud form.
  • the plastic parts can also be divided axially be. In this case, the two parts after joining held together during assembly by a screw, by a direct in the plastic or in a molded into the plastic part threaded bushing engaging screw.
  • connecting with Bolts and nuts is the plastic part in this area by additives or one formed in both halves Bush solidified.
  • Fig. 1 for a better understanding of the integration of the inner cover tape shown in the compressor, according to the state
  • the art trained compressor usually includes a Rotor 1 with several formed by a rotor blade ring Rotor stages and each one of the relevant rotor stage upstream, comprising a stator blade ring Stator.
  • Fig. 1 shows a rotor blade 2 of the first rotor stage and one of these upstream stator blade 3.
  • Die Stator blade 3 is connected via an inner connected thereto and outer pivots 4 and 5 in an undivided metallic Inner shroud 6 and the compressor housing 7 rotatable and adjustable to store due to the position of the Stator vane a desired air angle for the to be able to set the next rotor stage.
  • the inner pivot 4 is mounted in a slide bushing 8.
  • On a housing part 9 of the aircraft turbine is to seal against the secondary Air system attached to a static (first) seal 10, the with a sealing surface on the inner shroud 6 in sealing Active compound is.
  • a dynamic (second) seal 11 is provided between the inner shroud and the rotor stage.
  • the plastic part additionally contain graphite in the area the bearing of the inner pivot 4 and the dynamic Seal 11 the sliding and inlet properties improve.
  • the dynamic seal 11 includes one of the Material of the plastic part existing inlet layer (Sliding layer) 12, which formed with the rotor 1 sealing tips 13 is in contact. As shown in FIG.
  • the inlet layer also from a prefabricated insert 14 from another Material with inlet and sliding properties exist, the molded during injection molding in the plastic part.
  • a sliding bush (not shown) form fit be integrated into the plastic part. It is beyond that possible that additives with certain properties in concentrated form in the storage or inlet layer area of the plastic part are introduced to be integral with the plastic a highly effective sliding layer or shrinkage layer form. An example of this is in 2 a on the air guide side of the inner cover tape. 6 concentrated in the plastic from this area Additive formed wear protection layer 15.
  • wear protection layer 15 may also be in the plastic part molded insert during injection molding, for example a metal sheet, his.
  • the static (first) seal 10 consists of a molded from the plastic part Sealing lip, which is due to its flexural elastic properties and also under the effect of on the side of first rotor stage of high pressure elastic to the opposite fixed sealing part 16 of the housing part 9 applies.
  • various fibers for example glass, coal and / or Metal fibers provided. To achieve the desired Functions, these fibers can be in the desired location are introduced with different lengths, e.g. are desirable for the wear-resistant layer long fibers, while for the adjustment of the basic mechanical strength and the thermal expansion behavior short fibers sufficient are.
  • FIG. 3 of an axially divided formed inner band consisting of two separate, in one piece by injection molding or other suitable method manufactured plastic parts (inner cover halves 6a, 6b) is only the first (static) seal 10 in Form of the sealing lip provided and to the first inner shroud half 6a molded.
  • the two inner shroud halves 6a, 6b are by screw connections, each consisting of a Screw and a nut, held together.
  • a certain strength in this area can also achieved by a high additive content (fiber content) become.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04090415A 2003-11-17 2004-11-01 Virole interne pour les aubes statoriques d'un compresseur de turbine à gaz Ceased EP1531234B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10353810A DE10353810A1 (de) 2003-11-17 2003-11-17 Innendeckband für die Statorschaufeln des Verdichters einer Gasturbine
DE10353810 2003-11-17

Publications (2)

Publication Number Publication Date
EP1531234A1 true EP1531234A1 (fr) 2005-05-18
EP1531234B1 EP1531234B1 (fr) 2006-11-29

Family

ID=34428781

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04090415A Ceased EP1531234B1 (fr) 2003-11-17 2004-11-01 Virole interne pour les aubes statoriques d'un compresseur de turbine à gaz

Country Status (3)

Country Link
US (1) US7287957B2 (fr)
EP (1) EP1531234B1 (fr)
DE (2) DE10353810A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007085230A1 (fr) * 2006-01-28 2007-08-02 Mtu Aero Engines Gmbh Segment d'aube de guidage d'une turbine a gaz et procede pour sa fabrication
EP1998006A2 (fr) 2007-05-31 2008-12-03 United Technologies Corporation Mécanisme de rétention pour aube de guidage d'admission
US8403630B2 (en) 2007-08-10 2013-03-26 Rolls-Royce Deutschland Ltd & Co Kg Blade shroud with fluid barrier jet generation
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
EP2966269A1 (fr) * 2014-07-08 2016-01-13 MTU Aero Engines GmbH Système de protection contre l'usure pour une turbomachine, procedé et compresseur

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2922950B1 (fr) * 2007-10-31 2014-05-09 Snecma Cartouche de materiau abradable
GB2455785B (en) * 2007-12-21 2009-11-11 Rolls Royce Plc Annular component
US8500394B2 (en) 2008-02-20 2013-08-06 United Technologies Corporation Single channel inner diameter shroud with lightweight inner core
US8177494B2 (en) * 2009-03-15 2012-05-15 United Technologies Corporation Buried casing treatment strip for a gas turbine engine
EP2586989B1 (fr) * 2011-10-27 2015-04-29 Techspace Aero S.A. Virole composite co-injectée de compresseur de turbomachine axiale
GB2496887A (en) * 2011-11-25 2013-05-29 Rolls Royce Plc Gas turbine engine abradable liner
JP6078353B2 (ja) 2013-01-23 2017-02-08 三菱日立パワーシステムズ株式会社 ガスタービン
US10221718B2 (en) 2013-09-09 2019-03-05 United Technologies Corporation Fan cases and manufacture methods
WO2015077011A1 (fr) 2013-11-19 2015-05-28 United Technologies Corporation Extension de carénage interne à éléments multiples pour une turbomachine
DE102015202070A1 (de) * 2015-02-05 2016-08-25 MTU Aero Engines AG Gasturbinenbauteil
US9777593B2 (en) 2015-02-23 2017-10-03 General Electric Company Hybrid metal and composite spool for rotating machinery
US10260527B2 (en) 2016-05-17 2019-04-16 General Electric Company Method and system for mitigating rotor bow
US10900371B2 (en) 2017-07-27 2021-01-26 Rolls-Royce North American Technologies, Inc. Abradable coatings for high-performance systems
US10858950B2 (en) 2017-07-27 2020-12-08 Rolls-Royce North America Technologies, Inc. Multilayer abradable coatings for high-performance systems
DE102018106102A1 (de) * 2018-03-15 2019-09-19 Universität Stuttgart Leitschaufeleinrichtungen für eine Gasturbine und Gasturbine
US10808565B2 (en) * 2018-05-22 2020-10-20 Rolls-Royce Plc Tapered abradable coatings

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1366075A (en) * 1970-09-16 1974-09-11 Secr Defence Bladed fluid flow machines
US3849023A (en) * 1973-06-28 1974-11-19 Gen Electric Stator assembly
EP0171329A1 (fr) * 1984-08-08 1986-02-12 RATIER-FIGEAC, Société dite: Aube fixe pour réacteurs
GB2203197A (en) * 1987-04-07 1988-10-12 Mtu Muenchen Gmbh Axial guide vane assembly for compressors
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
EP0602631A1 (fr) * 1992-12-18 1994-06-22 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Procédé pour la construction d'une rangée d'aubes statoriques, en particulier pour un compresseur axial

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4655682A (en) * 1985-09-30 1987-04-07 United Technologies Corporation Compressor stator assembly having a composite inner diameter shroud
US5421703A (en) * 1994-05-25 1995-06-06 General Electric Company Positively retained vane bushing for an axial flow compressor
US6425736B1 (en) * 1999-08-09 2002-07-30 United Technologies Corporation Stator assembly for a rotary machine and method for making the stator assembly
DE10161292A1 (de) * 2001-12-13 2003-06-26 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1366075A (en) * 1970-09-16 1974-09-11 Secr Defence Bladed fluid flow machines
US3849023A (en) * 1973-06-28 1974-11-19 Gen Electric Stator assembly
EP0171329A1 (fr) * 1984-08-08 1986-02-12 RATIER-FIGEAC, Société dite: Aube fixe pour réacteurs
GB2203197A (en) * 1987-04-07 1988-10-12 Mtu Muenchen Gmbh Axial guide vane assembly for compressors
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
EP0602631A1 (fr) * 1992-12-18 1994-06-22 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Procédé pour la construction d'une rangée d'aubes statoriques, en particulier pour un compresseur axial

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007085230A1 (fr) * 2006-01-28 2007-08-02 Mtu Aero Engines Gmbh Segment d'aube de guidage d'une turbine a gaz et procede pour sa fabrication
EP1998006A2 (fr) 2007-05-31 2008-12-03 United Technologies Corporation Mécanisme de rétention pour aube de guidage d'admission
EP1998006A3 (fr) * 2007-05-31 2012-05-16 United Technologies Corporation Mécanisme de rétention pour aube de guidage d'admission
US8403630B2 (en) 2007-08-10 2013-03-26 Rolls-Royce Deutschland Ltd & Co Kg Blade shroud with fluid barrier jet generation
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
EP2966269A1 (fr) * 2014-07-08 2016-01-13 MTU Aero Engines GmbH Système de protection contre l'usure pour une turbomachine, procedé et compresseur

Also Published As

Publication number Publication date
US7287957B2 (en) 2007-10-30
DE502004002161D1 (de) 2007-01-11
US20050220612A1 (en) 2005-10-06
DE10353810A1 (de) 2005-06-23
EP1531234B1 (fr) 2006-11-29

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