EP0118769B1 - Shrouded multistage turbine - Google Patents

Shrouded multistage turbine Download PDF

Info

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)
French (fr)
Other versions
EP0118769A2 (en
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/en
Publication of EP0118769A3 publication Critical patent/EP0118769A3/en
Application granted granted Critical
Publication of EP0118769B1 publication Critical patent/EP0118769B1/en
Expired legal-status Critical Current

Links

Images

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)

Description

Die Erfindung betrifft eine mehrstufige Deckbandturbine mit Rotorschaufeln, die durch ein Deckband umschlossen sind.The invention relates to a multi-stage shroud turbine with rotor blades, which are enclosed by a shroud.

Die Auslegung mehrstufiger Turbinen erfolgt üblicherweise derart, daß die Strömung die einzelnen Turbinenstufen jeweils mit nur geringem Drall bzw. ohne Drall verläßt. Die nachfolgende Turbinenstufe wird für entsprechende drallarme Anströmung ausgelegt. Die Leckluft über die Deckbanddichtung sowie gegebenenfalls die aus den Rotorschaufeln austretende Kühlluft besitzen dagenen hohen Drall. Diese Luft vermischt sich hinter der Turbinenstufe mit der drallarmeren Hauptströmung und verursacht im Gehäusebereich eine Fehlanströmung des nachfolgenden Leitrades. Infolge des nicht genutzten Dralls der Kühl-/Leckluft sowie wegen der Fehlanströmung der nachfolgenden Turbinenstufe treten merkliche Leistungsverluste auf.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. As a result of 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.

Es wurde bereits versucht, dieses Problem durch sogenannte "Tip Fences" zu lösen. Dies sind kurze Schaufelstummel auf der Deckbandaußenseite, die aus der Kühl-/Leckluft einen Teil des Dralls herausnehmen und dadurch gleichzeitig zur Leistungsverbesserung nutzen. Solche Schaufelstummel am Rotor haben jedoch zur Folge, daß der Druck am Austritt der Kühlluft aus den Rotorschaufeln erhöht ist, die Schaufelkühlung also beeinträchtigt wird. Eine höhere Kühlluftmenge und/oder erhöhter Kühlluftlieferdruck wird dadurch erforderlich. Im übrigen führen die Schaufelstummel am Deckband des Rotors zu einem höheren Schaufelgewicht und damit zu erhöhten Scheibenrandlasten, verursachen also auch Festigkeitsprobleme, insbesondere deshalb, weil die Schaufelstummel sich im Betrieb zusammen mit den Rotorschaufeln hochtourig drehen.Attempts have already been made to solve this problem by means of “tip fences”. These are short blade stubs on the outside of the shroud, which remove part of the swirl from the cooling / leakage air and at the same time use it to improve performance. However, such blade stubs on the rotor have the result that the pressure at the outlet of the cooling air from the rotor blades is increased, so that the blade cooling is impaired. A higher cooling air quantity and / or increased cooling air delivery pressure is required. Otherwise, the blade stubs on the cover band of the rotor lead to a higher blade weight and thus to increased disk edge loads, and therefore also cause strength problems, in particular because the blade stubs rotate at high speed together with the rotor blades during operation.

Sowohl in der deutschen Offenlegungsschrift 20 00 314 als auch in der US Patentschrift 35 75 523 sind Labyrinth-Dichtungen für den Spalt zwischen Nabe und Rotor einer Axial-Strömungsmaschine beschrieben, die zwecks Verstärkung des Abdichtungseffektes eine Pumpwirkung von der Niederdruckseite zur Hochdruckseite erzeugen.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.

Aufbauend auf dem Stand der Technik ist es Aufgabe der Erfindung, eine mehrstufige Deckbandturbine mit Rotorschaufeln der eingangs genannten art zu schaffen, bei der im Betrieb praktisch keine Leistungsverluste durch Fehlanströmung der nachfolgenden Turbinenstufe auftreten, und zwar mit Hilfe einfacher Mittel, die das dynamische Laufverhalten des Rotors nicht beeeinträchtigen.Based on the prior art, it is an object of the invention to provide a multi-stage shroud turbine with rotor blades of the type mentioned, in which there are practically no performance losses due to incorrect flow to the subsequent turbine stage, using simple means that the dynamic running behavior of the Do not interfere with the rotor.

Gelöst wird die der Erfindung zugrunde liegende Aufgabe dadurch, daß der Leckluftstrom aus dem Spalt und der Kühlluftstrom aus den Laufschaufeln zusammengeführt und in einem am Gehäuse (4) in Axialrichtung der Turbine (1) zur Niederdruckseite versetzt und fest angeordneten Gitter (5) umgelenkt und an die Hauptströmung der Turbine angepaßt werden, bevor sie in eine nachgeordnete stationäre Turbinenstufe (6) eintreten.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).

Das Umlenkgitter ist zweckmäßigerweise ein geschlossenes Rundband mit inneren Schaufelstummeln. Vorteilhafterweise ist das rückwärtige Ende des Deckbandes so ausgebildet, daß es mit dem geschlossenen Rundband eine berührungsfreie Dichtung bildet. Das Umlenkgitter ist vorzugsweise am Gehäuse lösbar befestigt. Zur Erleichterung des Einbaus bzw. des Auswechselns kann das geschlossene Rundband aus mehreren Segmenten zusammengesetzt sein.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.

Des weiteren kann in erfindundsgemäßer Weiterbildung vorgesehen sein, daß das Umlenkgitter in Axialrichtung der Turbine bezüglich des Schaufelrotors zur Niederdruckseite hin versetzt angeordnet ist, so daß die niederdruckseitice Umfangskante des Deckbands etwa in der Axialmitte des Umlenkgitters liegt.Furthermore, in a further development according to the invention it can be provided that 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.

Die Schaufelstummel können hinsichtlich der Anströmung verstellbar angeordnet sein.The blade stubs can be arranged so as to be adjustable with regard to the flow.

Durch die Erfindung kann mithin die Leckluft durch die Deckbanddichtung und die aus den Rotorscnaufein radial austretende Kühlluftströmung an die drallärmere Hauptströmung hinter den Rotorschaufeln im Bereich vor einer nachgeordneten Turbinenstufe angepaßt werden, wodurch eine Fehlanströmung der nachfolgenden Turbinenstufe verhindert wird und dadurch praktisch keine Leistungsverluste auftreten. Das Umlenkgitter kann hinsichtlich Festigkeit und Gewicht geringer dimensioniert bzw. ausgestaltet werden als bei rotierenden "Tip Fences" nach dem Stand der Technik. Darüber hinaus verursacht das Umlenkgitter ein Absinken des Druckes zwischen Deckband und Gehäuse. Für die Schaufelkühlung steht somit ein größeres Drückgefälle zur Verfügung, die Kühleffektivität wird erhöht. Es ist daher möglich, die Kühlluftmenge und/oder den Kühlluftlieferdruck abzusenken bzw. das Kühlkonzept der Schaufeln zu vereinfachen.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. In addition, 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.

Die Erfindung wird nachfolgend anhand eines ausführungsbeispiels unter Bezugnahme auf die Zeichnung näher erläutert; es zeigt

  • Fig. 1 einen axialen schematischen Teilschnitt durch eine mehrstufige Deckbandturbine, und
  • Fig. 2 einen schematischen Schnitt längs der Linie A-A der Fig 1.
The invention is explained in more detail using an exemplary embodiment with reference to the drawing; it shows
  • Fig. 1 shows an axial schematic partial section through a multi-stage shroud turbine, and
  • 2 shows a schematic section along the line AA of FIG. 1.

Die schematisch in Fig. 1 dargestellte mehrstufige Deckbandturbine 1 ist im wesentlichen in bekannter weise konzipiert. Sie besitzt im Hochdruckabschnitt einen Schaufelrotor 2 mit äußerem Deckband 3. Die nachfolgende Turbinenstufe (Leitrad) ist mit dem Bezugszeichen 6 bezeichnet. Zwischen dem Deckband 3 des Schaufelrotors 2 und dem Umfangsgehäuse 4 ist ein stationäres Umlenkgitter 5 angeordnet, das im Teilschnitt im einzelnen in Fig. 2 veranschaulicht ist. Das Umlenkgitter besitzt innere Schaufelstummel 7 und hat mithin Leitradfunktion. Insbesondere ist das Umlenkgitter 5 - bezogen auf die Axialanordnung der Turbine 1 - so angeordnet, daß die niederdruckseitige radial äußere Umfangskante 8 des Deckbands 3 in etwa in axialer Mitte des Umlenkgitters 5 liegt und dicht, jedoch berührungsfrei an die Abdeckung 10 der Schaufelstummel 7 angrenzt. Die Schaufelstunmel 7 gemäß Fig. 2 sind so angestellt bzw. angeordnet, daß die aus dem Schaufelrotor 2 radial außen austretende Kühlluft und die durch die Deckbanddichtung 9 durchtretende Leckluft an die drallärmere Hauptströmung nach dem Schaufelrotor 2 angepaßt wird, so daß keine Fehlanströmung der nachfolgenden Turbinenstufe 6 eintritt.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. In particular, 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.

Claims (7)

1. Multi-stage turbine, particularly gas turbine, with a housing and rotating therein, a rotor of the bladed rotor discs (2) which are enclosed by a shroud band (3) and which are adjacent to stationary stages (6) with guide blades in the housing (4), whereby at least in the first stage the blades of a rotor disc have cooling air passing radially outwards through them, the cooling air being conducted over the shroud band (3) into the gap between the rotor (2) and the housing (4), characterised in that the stream of air leaking from the gap and the stream of cooling air from the blades converge and deflected in a grid (5) which is rigidly disposed on the housing (4) offset in relation to the low pressure side in the axial direction of the turbine (1), being adapted to the main flow of the turbine before entering a downstream stationary turbine stage (6).
2. Shroud band turbine according to Claim 1, characterised in that the deflecting grid (5) is a closed round band having inner blade stumps (7).
3. Shroud band turbine according to Claim 1 or Claim 2, characterised in that the downstream end of the shroud band (3) is so constructed that it forms with the closed round band a contact- free seal.
4. Shroud band turbine according to Claims 1 to 3, characterised in that the deflecting grid (5) is detachably fixed on the housing (4).
5. Shroud band turbine according to Claims 1 to 4, characterised in that the closed round band is composed of several parts.
6. Shroud band turbine according to Claims 1 to 5, characterised in that the deflecting grid (5) is disposed so that it is sufficiently staggered in an axial direction of the turbine (1) and in relation to the blade rotor (2) towards the low pressure side that the peripheral edge (8) of the shroud band (3) which is on the low pressure side lies substantially in the axial centre of the deflecting grid (5).
7. Shroud band turbine according to Claims 2 to 4, characterised in that the blade stumps (7) are disposed so as to be variable with reference to the incident flow.
EP84101311A 1983-03-08 1984-02-09 Shrouded multistage turbine Expired EP0118769B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3308140A DE3308140C2 (en) 1983-03-08 1983-03-08 Multi-stage gas turbine
DE3308140 1983-03-08

Publications (3)

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

Family

ID=6192827

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84101311A Expired EP0118769B1 (en) 1983-03-08 1984-02-09 Shrouded multistage turbine

Country Status (4)

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

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2570764B1 (en) * 1984-09-27 1986-11-28 Snecma DEVICE FOR AUTOMATICALLY CONTROLLING THE PLAY OF A TURBOMACHINE LABYRINTH SEAL
DE3509192A1 (en) * 1985-03-14 1986-09-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München FLOWING MACHINE WITH MEANS FOR CONTROLLING THE RADIAL GAP
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
WO1993005275A1 (en) * 1991-08-30 1993-03-18 Airflow Research And Manufacturing Corporation Forward skew fan with rake and chordwise camber corrections
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 (en) * 2006-06-05 2007-12-13 Toshiba Corp Axial flow turbine stage and axial flow turbine
US8568095B2 (en) * 2006-12-29 2013-10-29 Carrier Corporation Reduced tip clearance losses in axial flow fans
DE102009033754A1 (en) * 2009-07-17 2011-01-20 Rolls-Royce Deutschland Ltd & Co Kg Axial compressor with a flow pulse generator
JP2011106474A (en) * 2011-03-04 2011-06-02 Toshiba Corp Axial flow turbine stage and axial flow turbine
WO2012160586A1 (en) * 2011-05-20 2012-11-29 株式会社 日立製作所 Casing shroud for turbo machine
US20130230379A1 (en) * 2012-03-01 2013-09-05 General Electric Company Rotating turbomachine component having a tip leakage flow guide
JP5985351B2 (en) * 2012-10-25 2016-09-06 三菱日立パワーシステムズ株式会社 Axial flow turbine
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 (en) 2019-08-14 2021-02-22 Avio Polska Spółka Z Ograniczoną Odpowiedzialnością Seal reducing flow leakage inside a gas turbine engine

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 (en) * 1956-03-28 1958-05-12 Improvements to compressible fluid turbines
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
DE2000314A1 (en) * 1970-01-05 1971-07-15 Ulrich Hundrieser Gap sealing between stator and rotor in compressors and turbines
CH529914A (en) * 1971-08-11 1972-10-31 Mo Energeticheskij Institut Turbine stage
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 (en) * 1974-03-21 1979-07-12 Maschinenfabrik Augsburg-Nuernberg Ag, 8500 Nuernberg Device for dynamic stabilization of the rotor of a high-speed compressor
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 (en) * 1981-12-26 1983-07-06 Toshiba Corp Construction of moving blade in axial flow fluid machine
JPS58165201U (en) * 1982-04-30 1983-11-02 三菱重工業株式会社 Turbine blade seal structure

Also Published As

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

Similar Documents

Publication Publication Date Title
EP0118769B1 (en) Shrouded multistage turbine
DE2718693C3 (en) Bypass arrangement for reducing the noise of a fan stage of a gas turbine jet engine
DE2221895C3 (en) Device for supplying cooling air into cooling channels of the rotor blades of a gas turbine impeller
EP0924386B1 (en) Method and device to seal off the space between a rotor and a stator
EP0903468B1 (en) Gap sealing device
DE2554010A1 (en) DEVICE AND METHOD FOR SUPPLYING COOLING AIR TO TURBINE VANES
DE4422700A1 (en) Diffuser for turbomachinery
EP0417433B1 (en) Axial turbine
DE2423385B2 (en) Rotor for a supersonic centrifugal compressor
EP2824282A1 (en) Gas turbine with high pressure turbine cooling system
EP2138727A2 (en) Blade shrouds with outlet
CH688867A5 (en) Axial flow turbine.
DE1220204B (en) Axial turbo machine, in particular axial gas turbine
EP0799973A1 (en) Wall contour for an axial turbomachine
EP2103783A2 (en) Compactor stator with partial cover band
EP0992656B1 (en) Turbomachine to compress or expand a compressible medium
DE3523469A1 (en) Contact-free controlled-gap seal for turbo-machines
CH678352A5 (en)
DE4433289A1 (en) Axial gas turbine
DE3031553A1 (en) GAS TURBINE WHEEL.
DE3315477A1 (en) DUST SEPARATOR
EP3561228B1 (en) Turbomachine and blade, blade segment and assembly for a turbomachine
DE19814627C2 (en) Extraction of cooling air from the diffuser part of a compressor in a gas turbine
DE3907308A1 (en) BLADE FOR A BLOWER
EP1001138B1 (en) Turbine blade tip sealing

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Designated state(s): CH DE FR GB IT LI SE

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Designated state(s): CH DE FR GB IT LI SE

17P Request for examination filed

Effective date: 19850522

17Q First examination report despatched

Effective date: 19860205

ITF It: translation for a ep patent filed

Owner name: BARZANO' E ZANARDO MILANO S.P.A.

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI SE

REF Corresponds to:

Ref document number: 3463070

Country of ref document: DE

Date of ref document: 19870514

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Effective date: 19880210

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Effective date: 19880229

Ref country code: CH

Effective date: 19880229

26N No opposition filed
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 19890131

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 19890227

Year of fee payment: 6

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19890419

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Effective date: 19900209

GBPC Gb: european patent ceased through non-payment of renewal fee
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Effective date: 19901031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19901101

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

EUG Se: european patent has lapsed

Ref document number: 84101311.3

Effective date: 19880927