EP2044293B1 - Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation - Google Patents

Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation Download PDF

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Publication number
EP2044293B1
EP2044293B1 EP07785646.6A EP07785646A EP2044293B1 EP 2044293 B1 EP2044293 B1 EP 2044293B1 EP 07785646 A EP07785646 A EP 07785646A EP 2044293 B1 EP2044293 B1 EP 2044293B1
Authority
EP
European Patent Office
Prior art keywords
gap
channel
gas turbine
housing
blades
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.)
Ceased
Application number
EP07785646.6A
Other languages
German (de)
English (en)
Other versions
EP2044293A1 (fr
Inventor
Peter Seitz
Roland Huttner
Karl-Heinz Dusel
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
Publication of EP2044293A1 publication Critical patent/EP2044293A1/fr
Application granted granted Critical
Publication of EP2044293B1 publication Critical patent/EP2044293B1/fr
Ceased 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F05D2300/612—Foam

Definitions

  • the invention relates to a gas turbine, in particular a gas turbine aircraft engine, according to the preamble of claim 1.
  • Gas turbines particularly gas turbine aircraft engines, typically include a plurality of rotating blades in the region of a compressor and a turbine and a plurality of fixed vanes, the blades rotating together with a rotor, and the blades and vanes surrounded by a fixed housing.
  • a plurality of rotating blades in the region of a compressor and a turbine and a plurality of fixed vanes, the blades rotating together with a rotor, and the blades and vanes surrounded by a fixed housing.
  • sealing systems include the so-called sealing systems.
  • blades have no shroud, especially in the compressor. Therefore, the radially outer ends of the blades are exposed to so-called rubbing into the fixed housing direct frictional contact with the housing. Such a rubbing of the tips of the blades into the housing is caused by setting a minimum radial gap by manufacturing tolerances. As is removed by the frictional contact of the tips of the blades on the same material, over the entire circumference of the housing and rotor can set an undesirable gap magnification. To avoid this, it is already known from the prior art to armor the ends of the blades with a hard coating or with abrasive particles.
  • housings with inlet lining are known from the prior art, wherein the inlet lining is typically associated with housing-side shroud segments, which serve as a carrier for the inlet lining, Such shroud segments are also referred to as shrouds.
  • a seal assembly which has an inlet lining and a channel.
  • the inlet lining is provided at the height of the gap between the blade and the housing.
  • the channel has an inlet opening at the level of the gap and an outlet opening at the level of the gap.
  • EP 0 992 656 A1 shows a rotor with blades and a surrounding the rotor housing a turbomachine.
  • the blades have blade ends whose surfaces are approximately parallel to an inner wall of the housing.
  • a channel is provided, which opens in front of and behind the blade ends when viewed in the flow direction.
  • the inlet and outlet openings of the channel correspond to the intermediate gaps between the stator and rotor stages.
  • US2005 / 0226717A1 shows a blade which is partially spaced from a housing inner wall in the radial direction.
  • a channel is provided, which, viewed in the flow direction, opens in front of and behind the blade.
  • a negative pressure gradient which causes a backflow through the channel.
  • the present invention is based on the problem of creating a novel gas turbine with reduced aerodynamic gap losses.
  • This problem is solved by a gas turbine according to claim 1.
  • the gas turbine has at least one channel in order to apply a pressure prevailing on the high pressure side of blades of a rotor at a low pressure side thereof in the region of the gap between the radially outer ends of the blades and the housing and thus to prevent flow through the gap.
  • the channel extends at least in sections in serving as a support for the inlet lining, housing-side shroud segment, such that the channel opens on the high pressure side in the region of the shroud segment outside the gap in a flow channel and on the low pressure side in the region of the inlet lining in the gap to be sealed.
  • Fig. 1 shows a highly schematic section of a gas turbine 10 according to the invention in the region of a high-pressure compressor 11, wherein the high-pressure compressor 11 has a rotating rotor, of which in Fig. 1 a blade 12 is shown.
  • the blades 12 of the rotor of the high-pressure compressor 11 are surrounded by a fixed housing 13, wherein the housing 13 are associated with shroud segments 14 which serve, inter alia, as a carrier for an inlet lining 15.
  • Fig. 1 run during operation of the gas turbine radially outer ends 16 of the blades 12 in the inlet lining 15, so that a gap 17 is formed between the inlet lining 15 and the radially outer ends 16 of the blades.
  • a leakage flow from the high pressure side of the blades 12 to the low pressure side of the same form, wherein in the illustration of Fig. 1 the right side of the blades 12 is the high pressure side in which the pressure P H prevails, and the low pressure side is the left side of the blades on which the pressure P L prevails.
  • the gas turbine 10 has at least one channel 18 to the prevailing on the high pressure side of the blades 12 pressure on the low pressure side thereof in the region of the gap to be sealed 17th to apply.
  • the inlet lining 15 is a gas-permeable inlet lining, which preferably has an open-pored structure.
  • the inlet lining 15 is designed as an open-pored metal foam.
  • the in Fig. 1 channel 18 shown extends at least in sections, in which serves as a carrier for the running-in surface 15, housing-side shroud segment 14, the channel 18 on the high pressure side, where the pressure P H prevails in the area of shroud segment 14 in a flow passage of the high pressure compressor 11 of the gas turbine 10 empties.
  • the channel 16 opens in the region of the inlet lining 15 into the gap 17 to be sealed.
  • a cross-section of the or each channel 18 is preferably dimensioned such that an optionally flowing through the respective channel air in the region of the gap 17 to be sealed acts as sealing air.
  • guide elements z. As baffles or guide grille, be integrated to aerodynamically optimally guide the flowing through the channel 18 sealing air.
  • the invention is not limited to use on high pressure compressors.
  • the invention can also be used on other compressors and on turbines.

Landscapes

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

Claims (3)

  1. Turbine à gaz, en particulier moteur d'aéronef à turbine à gaz, doté d'au moins un compresseur, d'au moins une chambre de combustion et d'au moins une turbine, le ou les compresseurs et/ou la ou les turbines comprenant un rotor entouré d'un carter fixe et comprenant des aubes directrices, et une garniture de rodage (15) étant affectée au carter,
    caractérisée en ce
    que la turbine à gaz comporte au moins un canal (18) pour appliquer une pression régnant sur le côté haute pression d'aubes directrices (12) d'un rotor sur un côté basse pression de celles-ci dans la zone d'une fente (17) entre les extrémités (16) situées radialement à l'extérieur des aubes directrices (12) et le carter (13) et donc pour éviter un écoulement à travers la fente (17),
    de manière à ce que le ou les canaux (18) du côté basse pression dans la zone de la garniture de rodage (15) débouchent dans la fente (17) à étanchéifier, et
    en ce que le ou les canaux (18) s'étendent au moins en partie dans un segment annulaire d'enveloppe (14) côté carter, servant de support à la garniture de rodage (15) de manière à ce que le canal (18) du côté haute pression dans la zone du segment annulaire d'enveloppe (14) débouche dans un canal d'écoulement à l'extérieur de la fente (17).
  2. Turbine à gaz selon la revendication 1,
    caractérisée en ce que
    la garniture de rodage (15) est perméable aux gaz et possède une structure à pores ouverts.
  3. Turbine à gaz selon la revendication 1 ou 2,
    caractérisée en ce que
    la garniture de rodage (15) est conçue sous forme de mousse métallique.
EP07785646.6A 2006-07-26 2007-07-18 Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation Ceased EP2044293B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006034424A DE102006034424A1 (de) 2006-07-26 2006-07-26 Gasturbine
PCT/DE2007/001276 WO2008011864A1 (fr) 2006-07-26 2007-07-18 Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation

Publications (2)

Publication Number Publication Date
EP2044293A1 EP2044293A1 (fr) 2009-04-08
EP2044293B1 true EP2044293B1 (fr) 2018-06-13

Family

ID=38663013

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07785646.6A Ceased EP2044293B1 (fr) 2006-07-26 2007-07-18 Turbine à gaz dotée d'un segment annulaire comprenant un canal de recirculation

Country Status (5)

Country Link
US (1) US8092148B2 (fr)
EP (1) EP2044293B1 (fr)
CA (1) CA2657190C (fr)
DE (1) DE102006034424A1 (fr)
WO (1) WO2008011864A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876549B2 (en) 2019-04-05 2020-12-29 Pratt & Whitney Canada Corp. Tandem stators with flow recirculation conduit

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008019331A1 (de) * 2008-04-16 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Einlaufdichtung für den Kompressor eines Gasturbinentriebwerks
CN101858229A (zh) * 2010-04-29 2010-10-13 中国燃气涡轮研究院 发动机热定心承力型导向器
WO2012052740A1 (fr) * 2010-10-18 2012-04-26 University Of Durham Dispositif d'étanchéité pour réduire la fuite de fluide dans une turbine
US9726084B2 (en) 2013-03-14 2017-08-08 Pratt & Whitney Canada Corp. Compressor bleed self-recirculating system
DE102014213911A1 (de) 2014-07-17 2016-01-21 MTU Aero Engines AG Aerogel-Auskleidungselement für Strömungsmaschinen
US9789536B2 (en) 2015-01-20 2017-10-17 United Technologies Corporation Dual investment technique for solid mold casting of reticulated metal foams
US9737930B2 (en) 2015-01-20 2017-08-22 United Technologies Corporation Dual investment shelled solid mold casting of reticulated metal foams
US9789534B2 (en) 2015-01-20 2017-10-17 United Technologies Corporation Investment technique for solid mold casting of reticulated metal foams
US9884363B2 (en) 2015-06-30 2018-02-06 United Technologies Corporation Variable diameter investment casting mold for casting of reticulated metal foams
US9731342B2 (en) 2015-07-07 2017-08-15 United Technologies Corporation Chill plate for equiax casting solidification control for solid mold casting of reticulated metal foams

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US3063694A (en) * 1959-08-04 1962-11-13 Joy Mfg Co Apparatus for cleaning gases from ferrous metallurgical operations
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876549B2 (en) 2019-04-05 2020-12-29 Pratt & Whitney Canada Corp. Tandem stators with flow recirculation conduit

Also Published As

Publication number Publication date
DE102006034424A1 (de) 2008-01-31
US20090324384A1 (en) 2009-12-31
US8092148B2 (en) 2012-01-10
CA2657190A1 (fr) 2008-01-31
CA2657190C (fr) 2015-06-23
WO2008011864A1 (fr) 2008-01-31
EP2044293A1 (fr) 2009-04-08

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