EP0118769B1 - Turbine à plusieurs étages avec bandages extérieurs - Google Patents

Turbine à plusieurs étages avec bandages extérieurs Download PDF

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Publication number
EP0118769B1
EP0118769B1 EP84101311A EP84101311A EP0118769B1 EP 0118769 B1 EP0118769 B1 EP 0118769B1 EP 84101311 A EP84101311 A EP 84101311A EP 84101311 A EP84101311 A EP 84101311A EP 0118769 B1 EP0118769 B1 EP 0118769B1
Authority
EP
European Patent Office
Prior art keywords
turbine
band
shroud band
shroud
rotor
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.)
Expired
Application number
EP84101311A
Other languages
German (de)
English (en)
Other versions
EP0118769A2 (fr
EP0118769A3 (en
Inventor
Martin Dr.-Ing. Albers
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 GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen 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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0118769A2 publication Critical patent/EP0118769A2/fr
Publication of EP0118769A3 publication Critical patent/EP0118769A3/de
Application granted granted Critical
Publication of EP0118769B1 publication Critical patent/EP0118769B1/fr
Expired 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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

Definitions

  • the invention relates to a multi-stage shroud turbine with rotor blades, which are enclosed by a shroud.
  • Multi-stage turbines are usually designed in such a way that the flow leaves the individual turbine stages with only a small swirl or without swirl.
  • the subsequent turbine stage is designed for the corresponding low-swirl flow.
  • the leakage air via the cover band seal and, if applicable, the cooling air emerging from the rotor blades have this high swirl.
  • This air mixes behind the turbine stage with the lower-swirl main flow and causes an incorrect flow against the following stator in the housing area.
  • the unused swirl of the cooling / leakage air and because of the incorrect inflow of the subsequent turbine stage there is a noticeable loss of performance.
  • Labyrinth seals for the gap between the hub and rotor of an axial flow machine are described both in German laid-open specification 20 00 314 and in US Pat. No. 35 75 523, which generate a pumping effect from the low-pressure side to the high-pressure side in order to reinforce the sealing effect.
  • the object on which the invention is based is achieved in that the leakage air flow from the gap and the cooling air flow from the rotor blades are brought together and offset in a housing (4) in the axial direction of the turbine (1) to the low-pressure side and deflected fixed grille (5) and be adapted to the main flow of the turbine before they enter a downstream stationary turbine stage (6).
  • the deflection grid is expediently a closed round belt with inner blade stubs.
  • the rear end of the shroud is advantageously designed such that it forms a contact-free seal with the closed round belt.
  • the deflection grid is preferably releasably attached to the housing.
  • the closed round belt can be composed of several segments to facilitate installation or replacement.
  • the deflection grid is arranged offset in the axial direction of the turbine with respect to the blade rotor to the low pressure side, so that the low pressure side peripheral edge of the cover band lies approximately in the axial center of the deflection grid.
  • the blade stubs can be arranged so as to be adjustable with regard to the flow.
  • the invention therefore allows the leakage air to be adapted through the shroud seal and the cooling air flow radially emerging from the rotor blades to the less swirling main flow behind the rotor blades in the area in front of a downstream turbine stage, thereby preventing an incorrect flow against the subsequent turbine stage and thereby practically no performance losses occurring.
  • the deflection grating can be dimensioned or designed to be smaller in terms of strength and weight than in the case of rotating "tip fences" according to the prior art.
  • the deflection grid causes a drop in pressure between the cover band and the housing. A larger pressure drop is available for blade cooling and the cooling efficiency is increased. It is therefore possible to reduce the cooling air quantity and / or the cooling air delivery pressure or to simplify the cooling concept of the blades.
  • the multi-stage shroud turbine 1 shown schematically in FIG. 1 is essentially designed in a known manner. In the high-pressure section, it has a blade rotor 2 with an outer shroud 3. The subsequent turbine stage (stator) is designated by reference number 6. A stationary deflection grating 5 is arranged between the shroud 3 of the blade rotor 2 and the peripheral housing 4, which is illustrated in detail in FIG. 2 in a partial section.
  • the Deflection grid has inner blade stub 7 and therefore has a stator function.
  • the deflection grid 5 - based on the axial arrangement of the turbine 1 - is arranged such that the low-pressure, radially outer peripheral edge 8 of the shroud 3 lies approximately in the axial center of the deflection grid 5 and is tightly but non-contact adjacent to the cover 10 of the blade stub 7.
  • the blade tunnels 7 according to FIG. 2 are adjusted or arranged so that the cooling air emerging radially from the blade rotor 2 and the leakage air passing through the shroud seal 9 are adapted to the less swirling main flow downstream of the blade rotor 2, so that there is no incorrect flow to the subsequent turbine stage 6 occurs.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (7)

1°) Turbine à plusieurs étages, notamment turbine à gaz, avec un boîtier et un rotor, de disques de rotor (2) munis d'ailettes tournant dans ce boîtier, ces disques étant entourés d'une bande de recouvrement (3) étant voisins d'étages stationnaires (6) munis d'aubes directrices dans le boîtier (4), cependant qu'au moins dans le premier étage, les aubes mobiles d'un disque de rotor sont traversées radialement vers l'extérieur par l'air de refroidissementet cet air de refroidissementestcanalisé par l'intermédiaire de la bande de recouvrement (3) dans l'intervalle entre le rotor (2) et le boîtier (4), turbine caractérisée en ce que l'écoulement de l'air de fuite en provenance de l'intervalle et l'écoulement de l'air de refroidissement en provenance des aubes mobiles sont rassemblés, sont déviés dans une grille (5) décalée sur le boîtier (4) en direction axiale dela turbine (1) vers le côté basse pression et disposée à poste fixe, ces écoulements sont adaptés à l'écoulement principal de la turbine avant qu'ils pénètrent dans un étage fixe (6) de la turbine disposé à la suite.
2°) Turbine à bande de recouvrement selon la revendication 1, caractérisée en ce que la grille de déviation (5) est une bande ronde fermée avec destronçons d'aubes internes (7).
3°) Turbine à bande de recouvrement selon la revendication 1 ou la revendication 2, caractérisée en ce que l'extémité aval de la bande de recouvrement (3) est conformée de façon qu'elle constitue avec la bande ronde fermée un joint d'étanchéité sans contact.
4°) Turbine à bande de recouvrement selon les revendications 1 à 3, caractérisée en ce que la grille de déviation (5) est fixée de façon amovible sur le boîtier (4).
5°) Turbiné à bandé de recouvrement selon les revendications 1 à 4, caractérisée en ce que la bande ronde fermée est composée de plusieurs parties.
6°) Turbine à bande de recouvrément selon les revendications 1 à 5, caractérisée en ce que la grille de déviation (5) est décalée en diréction axiale de la turbine (1) par rapport au rotor à aubes (1) vers le côté basse pression dans une mesure telle que le bord périphérique côté basse pression (8) de la bande de recouvrement (3) se situe à peu près dans le milieu axial de la grillé de déviation (5).
7°) Turbine à bande de recouvrement selon les revendications 2 à 4, caractérisée en ce que les tronçons d'aubes (7) sont réglables par rapport à l'écoulément d'entrée.
EP84101311A 1983-03-08 1984-02-09 Turbine à plusieurs étages avec bandages extérieurs Expired EP0118769B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3308140 1983-03-08
DE3308140A DE3308140C2 (de) 1983-03-08 1983-03-08 Mehrstufige Gasturbine

Publications (3)

Publication Number Publication Date
EP0118769A2 EP0118769A2 (fr) 1984-09-19
EP0118769A3 EP0118769A3 (en) 1985-04-24
EP0118769B1 true EP0118769B1 (fr) 1987-04-08

Family

ID=6192827

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84101311A Expired EP0118769B1 (fr) 1983-03-08 1984-02-09 Turbine à plusieurs étages avec bandages extérieurs

Country Status (4)

Country Link
US (1) US4571937A (fr)
EP (1) EP0118769B1 (fr)
JP (1) JPS59168202A (fr)
DE (2) DE3308140C2 (fr)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2570764B1 (fr) * 1984-09-27 1986-11-28 Snecma Dispositif de controle automatique du jeu d'un joint a labyrinthe de turbomachine
DE8507551U1 (fr) * 1985-03-14 1990-10-11 Mtu Muenchen Gmbh
US4791784A (en) * 1985-06-17 1988-12-20 University Of Dayton Internal bypass gas turbine engines with blade cooling
US4863348A (en) * 1987-02-06 1989-09-05 Weinhold Wolfgang P Blade, especially a rotor blade
US5489186A (en) * 1991-08-30 1996-02-06 Airflow Research And Manufacturing Corp. Housing with recirculation control for use with banded axial-flow fans
DE69228189T2 (de) * 1991-08-30 1999-06-17 Airflow Res & Mfg Ventilator mit vorwärtsgekrümmten schaufeln und angepasster schaufelkrümmung und -anstellung
GB2340189A (en) * 1998-08-04 2000-02-16 Siemens Plc A turbomachine shroud seal having baffles
US20050200080A1 (en) * 2004-03-10 2005-09-15 Siemens Westinghouse Power Corporation Seal for a turbine engine
JP2007321721A (ja) * 2006-06-05 2007-12-13 Toshiba Corp 軸流タービン段落および軸流タービン
US8568095B2 (en) * 2006-12-29 2013-10-29 Carrier Corporation Reduced tip clearance losses in axial flow fans
DE102009033754A1 (de) * 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Axialverdichter mit einem Strömungsimpulserzeuger
JP2011106474A (ja) * 2011-03-04 2011-06-02 Toshiba Corp 軸流タービン段落および軸流タービン
WO2012160586A1 (fr) * 2011-05-20 2012-11-29 株式会社 日立製作所 Virole de corps pour turbo-machine
US20130230379A1 (en) * 2012-03-01 2013-09-05 General Electric Company Rotating turbomachine component having a tip leakage flow guide
JP5985351B2 (ja) * 2012-10-25 2016-09-06 三菱日立パワーシステムズ株式会社 軸流タービン
US9593691B2 (en) * 2013-07-19 2017-03-14 General Electric Company Systems and methods for directing a flow within a shroud cavity of a compressor
GB201519869D0 (en) * 2015-11-11 2015-12-23 Rolls Royce Plc Shrouded turbine blade
US10590786B2 (en) 2016-05-03 2020-03-17 General Electric Company System and method for cooling components of a gas turbine engine
PL430870A1 (pl) 2019-08-14 2021-02-22 Avio Polska Spółka Z Ograniczoną Odpowiedzialnością Uszczelnienie do zmniejszania wycieku przepływu wewnątrz silnika z turbiną gazową

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US881474A (en) * 1906-08-14 1908-03-10 Belliss & Morcom Ltd Turbine-motor.
FR1155958A (fr) * 1956-03-28 1958-05-12 Perfectionnements aux turbines à fluide compressible
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
DE2000314A1 (de) * 1970-01-05 1971-07-15 Ulrich Hundrieser Spaltabdichtung zwischen Stator und Rotor bei Kompressoren und Turbinen
GB1364511A (en) * 1971-08-11 1974-08-21 Mo Energeticheskij Institut Turbines
GB1423833A (en) * 1972-04-20 1976-02-04 Rolls Royce Rotor blades for fluid flow machines
GB1426049A (en) * 1972-10-21 1976-02-25 Rolls Royce Rotor blade for a gas turbine engine
US3867061A (en) * 1973-12-26 1975-02-18 Curtiss Wright Corp Shroud structure for turbine rotor blades and the like
US4273510A (en) * 1974-03-21 1981-06-16 Maschinenfabrik Augsburg-Nunberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
DE2462465B2 (de) * 1974-03-21 1979-07-12 Maschinenfabrik Augsburg-Nuernberg Ag, 8500 Nuernberg Einrichtung zum dynamischen Stabilisieren des Läufers eines hochtourigen Verdichters
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
GB1514613A (en) * 1976-04-08 1978-06-14 Rolls Royce Blade or vane for a gas turbine engine
JPS53136106A (en) * 1977-05-02 1978-11-28 Toshiba Corp Leakage preventive arrangement for axial flow machine
JPS5447907A (en) * 1977-09-26 1979-04-16 Hitachi Ltd Blading structure for axial-flow fluid machine
US4224011A (en) * 1977-10-08 1980-09-23 Rolls-Royce Limited Cooled rotor blade for a gas turbine engine
JPS578302A (en) * 1980-06-19 1982-01-16 Hitachi Ltd Internal stage structure of multistage axial-flow machine
US4424001A (en) * 1981-12-04 1984-01-03 Westinghouse Electric Corp. Tip structure for cooled turbine rotor blade
JPS58113504A (ja) * 1981-12-26 1983-07-06 Toshiba Corp 軸流流体機械の動翼構造
JPS58165201U (ja) * 1982-04-30 1983-11-02 三菱重工業株式会社 タ−ビン翼のシ−ル構造

Also Published As

Publication number Publication date
DE3463070D1 (en) 1987-05-14
JPS59168202A (ja) 1984-09-21
US4571937A (en) 1986-02-25
EP0118769A2 (fr) 1984-09-19
EP0118769A3 (en) 1985-04-24
DE3308140A1 (de) 1984-09-13
DE3308140C2 (de) 1985-12-19

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