EP0214038A1 - Einrichtung um den Einlassquerschnitt einer Turbine zu verändern - Google Patents

Einrichtung um den Einlassquerschnitt einer Turbine zu verändern Download PDF

Info

Publication number
EP0214038A1
EP0214038A1 EP86401803A EP86401803A EP0214038A1 EP 0214038 A1 EP0214038 A1 EP 0214038A1 EP 86401803 A EP86401803 A EP 86401803A EP 86401803 A EP86401803 A EP 86401803A EP 0214038 A1 EP0214038 A1 EP 0214038A1
Authority
EP
European Patent Office
Prior art keywords
blade
flap
ribs
internal face
profile
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
EP86401803A
Other languages
English (en)
French (fr)
Other versions
EP0214038B1 (de
Inventor
Georges Karadimas
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0214038A1 publication Critical patent/EP0214038A1/de
Application granted granted Critical
Publication of EP0214038B1 publication Critical patent/EP0214038B1/de
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
    • 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

Definitions

  • the present invention relates to a device for varying the passage section of a turbine distributor.
  • the section variation is obtained by aerodynamic means.
  • aerodynamic means which are generally inexpensive, cause significant drops in efficiency and disturbances in the ventilation of the blades.
  • the device comprises between the fixed vanes a single articulated monobloc flap which can occupy a retracted position and a position for which the channel is partially closed.
  • the main defect of this method is that it creates large projections in the vein, in the vicinity of the heels of the movable blades when the flaps are in the reduced vein position.
  • the present invention relates to a device for varying the passage section which does not have the drawbacks mentioned above.
  • each blade comprises, on the lower surface, a movable flap mounted pivoting on said blade around a radially disposed axis, said flap, in the rest position, being aligned with the lower surface of the blade, of which it ensures profile continuity and said movable flap has on its internal face ribs arranged parallel to the profile chord, said ribs constituting stiffening members of the flap and fins of thermal radiator.
  • the device according to the invention makes it possible to obtain a variation in the cross section of the gases with a minimum of aerodynamic losses between the so-called “nominal” operation and the operation at other so-called “non-adaptation” conditions, the variation being continuous between the different operating points.
  • FIG. 1 there is shown a blade 1 of a turbine distributor which is provided, on the pressure side and on the half of the profile chord on the trailing edge side, with a movable flap 2 pivotally mounted on said blade around an axis 3 arranged radially.
  • the shutter 2 in the rest position is aligned with the lower surface of the blade, that is to say that the face 2a follows the definition of the lower surface of the profile, optimized to minimize losses.
  • the other side of the flap 2 has ribs 4 arranged parallel to the profile chord which increase its mechanical resistance by ensuring greater rigidity of the flap, and which play the role of radiator fins ensuring an acceleration of the heat exchanges with the cooling air bathing these fins.
  • the height of the fin 2 occupies the entire height of the blade at this location, except the part located near the platforms which has a connecting radius.
  • the blade 1 on which the movable flap 2 is fitted has a face 5 on the upper surface, where the profile is optimized.
  • the blade On the other face 6, the blade has ribs 7 offset from the ribs 4 of the shutter, so that in the "nominal" position the two series of ribs overlap.
  • the pitch and the thickness of the ribs 4 and 7 are such that they provide a space 8 between the tail of the blade and the flap to pass the cooling air.
  • the ribs 4 and 7 are produced so as to constitute a piano hinge.
  • the cooling air which circulates in the main cavity 9 of the blade flows through holes 10 and 11 towards the rear.
  • One of the holes 10 ensuring the cooling of the hinge with its axis 3 and towards the space 8 in the direction of the trailing edge, part of the air, after having cooled the ribs 4, 7 on the lower side, S 'escapes through the holes 13 provided in the flap 2 (Fig. 1,2,3,4) and through the slot 12 located at the trailing edge.
  • one of the holes 11 also cools the hinge and the lower surface, the air escaping from it according to arrow F.
  • This arrangement makes it possible to cool not only the hinge but the entire region of the trailing edge on the lower side, as on the upper side.
  • the flap 2 rests on the blade 1 by means of the ribs 4 which have rectified contact surfaces.
  • the flaps 2 are separated from the rear part of the blade as shown, in broken lines, in FIG. 3.
  • the flap 2 comprises a tab 14 (Fig. 3,4,5) which is in abutment against one of the ends of a lever 15 mounted in an articulated fashion around an axis 16 fixed on the blade 1 , said lever being located above the distributor platform.
  • the lever 15 has a hole 17 in which is engaged a member secured to a ring, not shown in the drawing, and which ensures the connection and the drive of all the levers of all the blades.
  • the control ring is actuated by one or more regulated hydraulic cylinders.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP86401803A 1985-08-14 1986-08-13 Einrichtung um den Einlassquerschnitt einer Turbine zu verändern Expired EP0214038B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8512366 1985-08-14
FR8512366A FR2586268B1 (fr) 1985-08-14 1985-08-14 Dispositif de variation de la section de passage d'un distributeur de turbine

Publications (2)

Publication Number Publication Date
EP0214038A1 true EP0214038A1 (de) 1987-03-11
EP0214038B1 EP0214038B1 (de) 1989-03-08

Family

ID=9322221

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86401803A Expired EP0214038B1 (de) 1985-08-14 1986-08-13 Einrichtung um den Einlassquerschnitt einer Turbine zu verändern

Country Status (4)

Country Link
US (1) US4705452A (de)
EP (1) EP0214038B1 (de)
DE (1) DE3662292D1 (de)
FR (1) FR2586268B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2262314A (en) * 1991-12-10 1993-06-16 Rolls Royce Plc Air cooled gas turbine engine aerofoil.
US10363510B1 (en) 2018-06-01 2019-07-30 Ford Global Technologies, Llc Climate control filter monitoring system and method of monitoring the useful life of a climate control system filter

Families Citing this family (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2218746B (en) * 1988-05-17 1992-06-17 Rolls Royce Plc A nozzle guide vane for a gas turbine engine
US5207558A (en) * 1991-10-30 1993-05-04 The United States Of America As Represented By The Secretary Of The Air Force Thermally actuated vane flow control
ES2063636B1 (es) * 1992-04-23 1997-05-01 Turbo Propulsores Ind Conjunto de alabes de estator para motores de turbina de gas.
FR2707338B1 (fr) * 1993-07-07 1995-08-11 Snecma Aube de turbomachine à cambrure variable.
US5931636A (en) * 1997-08-28 1999-08-03 General Electric Company Variable area turbine nozzle
GB2411440B (en) * 2004-02-24 2006-08-16 Rolls Royce Plc Gas turbine nozzle guide vane
US7644585B2 (en) * 2004-08-31 2010-01-12 The United States Of America As Represented By The Administrator Of The U.S. Environmental Protection Agency Multi-stage turbocharging system with efficient bypass
US7305826B2 (en) * 2005-02-16 2007-12-11 Honeywell International , Inc. Axial loading management in turbomachinery
US7491030B1 (en) 2006-08-25 2009-02-17 Florida Turbine Technologies, Inc. Magnetically actuated guide vane
DE102008049358A1 (de) * 2008-09-29 2010-04-01 Mtu Aero Engines Gmbh Axiale Strömungsmaschine mit asymmetrischem Verdichtereintrittsleitgitter
US9650903B2 (en) * 2009-08-28 2017-05-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
US8042483B2 (en) * 2009-09-18 2011-10-25 The United States Of America As Represented By The Secretary Of The Navy Apparatus for control of stator wakes
US8919119B2 (en) * 2011-08-16 2014-12-30 Ford Global Technologies, Llc Sliding vane geometry turbines
EP2961934B1 (de) 2013-02-26 2020-02-19 Rolls-Royce North American Technologies, Inc. Gasturbinenkomponente mit variabler geometrie
EP2905425B1 (de) 2014-02-06 2019-07-10 United Technologies Corporation Verstellbare schaufel und dichtungsanordnung
US10030669B2 (en) * 2014-06-26 2018-07-24 General Electric Company Apparatus for transferring energy between a rotating element and fluid
DE102014213633A1 (de) * 2014-07-14 2016-01-14 Siemens Aktiengesellschaft Verstellbarer Düsenring
US10502089B2 (en) 2014-09-22 2019-12-10 United Technologies Corporation Gas turbine engine variable stator vane
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
US10578028B2 (en) 2015-08-18 2020-03-03 General Electric Company Compressor bleed auxiliary turbine
US10711702B2 (en) 2015-08-18 2020-07-14 General Electric Company Mixed flow turbocore
US20170051680A1 (en) * 2015-08-18 2017-02-23 General Electric Company Airflow injection nozzle for a gas turbine engine
US10267159B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North America Technologies Inc. System and method for creating a fluidic barrier with vortices from the upstream splitter
US10267160B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North American Technologies Inc. Methods of creating fluidic barriers in turbine engines
US9915149B2 (en) 2015-08-27 2018-03-13 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier on the low pressure side of a fan blade
US10233869B2 (en) 2015-08-27 2019-03-19 Rolls Royce North American Technologies Inc. System and method for creating a fluidic barrier from the leading edge of a fan blade
US10280872B2 (en) 2015-08-27 2019-05-07 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier from the upstream splitter
US9976514B2 (en) 2015-08-27 2018-05-22 Rolls-Royce North American Technologies, Inc. Propulsive force vectoring
US20170057649A1 (en) 2015-08-27 2017-03-02 Edward C. Rice Integrated aircraft propulsion system
US10125622B2 (en) 2015-08-27 2018-11-13 Rolls-Royce North American Technologies Inc. Splayed inlet guide vanes
US10718221B2 (en) 2015-08-27 2020-07-21 Rolls Royce North American Technologies Inc. Morphing vane
JP6694950B2 (ja) * 2016-03-30 2020-05-20 三菱重工エンジン＆ターボチャージャ株式会社 可変容量型ターボチャージャ
US10480326B2 (en) * 2017-09-11 2019-11-19 United Technologies Corporation Vane for variable area turbine
US10934883B2 (en) * 2018-09-12 2021-03-02 Raytheon Technologies Cover for airfoil assembly for a gas turbine engine
US11788429B2 (en) 2021-08-25 2023-10-17 Rolls-Royce Corporation Variable tandem fan outlet guide vanes
US11802490B2 (en) 2021-08-25 2023-10-31 Rolls-Royce Corporation Controllable variable fan outlet guide vanes
US11879343B2 (en) 2021-08-25 2024-01-23 Rolls-Royce Corporation Systems for controlling variable outlet guide vanes
US11686211B2 (en) 2021-08-25 2023-06-27 Rolls-Royce Corporation Variable outlet guide vanes

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE733286C (de) * 1935-09-14 1943-03-24 Schuechtermann & Kremer Baum A Grubenluefter
FR942182A (fr) * 1945-12-28 1949-02-01 Rolls Royce Perfectionnements aux compresseurs centrifuges de suralimentation des moteurs à combustion interne
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
FR1151368A (fr) * 1955-06-17 1958-01-29 Schweizerische Lokomotiv Couronne d'aubes directrices de turbine, avec aubes réglables
US2856758A (en) * 1955-10-31 1958-10-21 Douglas Aircraft Co Inc Variable nozzle cooling turbine
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
DE2416724A1 (de) * 1973-04-09 1974-10-17 Colchester Woods Leitfluegelanordnung
US3992128A (en) * 1975-06-09 1976-11-16 General Motors Corporation Variable diffuser

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE659211C (de) * 1936-08-25 1938-04-28 Brandenburgische Motorenwerke Verfahren zur Aufrechterhaltung gleichen Druckes in der Foerderleitung eines Ladegeblaeses fuer Flugmotoren
US2866313A (en) * 1950-04-14 1958-12-30 Power Jets Res & Dev Ltd Means for cooling turbine-blades by liquid jets
US3442493A (en) * 1965-10-22 1969-05-06 Gen Electric Articulated airfoil vanes
DE1601613A1 (de) * 1967-08-03 1970-12-17 Motoren Turbinen Union Turbinenschaufel,insbesondere Turbinenleitschaufel fuer Gasturbinentriebwerke
US4053256A (en) * 1975-09-29 1977-10-11 United Technologies Corporation Variable camber vane for a gas turbine engine
US4193738A (en) * 1977-09-19 1980-03-18 General Electric Company Floating seal for a variable area turbine nozzle
US4297077A (en) * 1979-07-09 1981-10-27 Westinghouse Electric Corp. Cooled turbine vane
US4378960A (en) * 1980-05-13 1983-04-05 Teledyne Industries, Inc. Variable geometry turbine inlet nozzle

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE733286C (de) * 1935-09-14 1943-03-24 Schuechtermann & Kremer Baum A Grubenluefter
FR942182A (fr) * 1945-12-28 1949-02-01 Rolls Royce Perfectionnements aux compresseurs centrifuges de suralimentation des moteurs à combustion interne
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
FR1151368A (fr) * 1955-06-17 1958-01-29 Schweizerische Lokomotiv Couronne d'aubes directrices de turbine, avec aubes réglables
US2856758A (en) * 1955-10-31 1958-10-21 Douglas Aircraft Co Inc Variable nozzle cooling turbine
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
DE2416724A1 (de) * 1973-04-09 1974-10-17 Colchester Woods Leitfluegelanordnung
US3992128A (en) * 1975-06-09 1976-11-16 General Motors Corporation Variable diffuser

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2262314A (en) * 1991-12-10 1993-06-16 Rolls Royce Plc Air cooled gas turbine engine aerofoil.
US10363510B1 (en) 2018-06-01 2019-07-30 Ford Global Technologies, Llc Climate control filter monitoring system and method of monitoring the useful life of a climate control system filter

Also Published As

Publication number Publication date
FR2586268B1 (fr) 1989-06-09
FR2586268A1 (fr) 1987-02-20
DE3662292D1 (en) 1989-04-13
US4705452A (en) 1987-11-10
EP0214038B1 (de) 1989-03-08

Similar Documents

Publication Publication Date Title
EP0214038B1 (de) Einrichtung um den Einlassquerschnitt einer Turbine zu verändern
EP1726783B1 (de) Hohle Laufschaufel für die Turbine eines Gasturbinentriebwerks, mit einem Hohlraum
CA2652679C (fr) Aubes pour roue a aubes de turbomachine avec rainure pour le refroidissement
EP1188903A1 (de) Bearbeiteter Gehäusemantel für Turbomaschinen
CA2478746C (fr) Aube creuse de rotor pour la turbine d'un moteur a turbine a gaz
EP3134620B1 (de) Turbinenschaufel einer turbomaschine mit einem kühlkreislauf mit verbesserter homogenität
EP0633392A1 (de) Turbomaschinenschaufel mit variabler Wölbung
CA2620782C (fr) Dispositif de decharge pour un turboreacteur, et turboreacteur le comportant
EP3377731B1 (de) Schaufel mit kühlsystem, zugehörige leitschaufelanordnung und zugehörige turbomaschine
FR2956454A1 (fr) Aube a angle de calage variable pour la prevention du decollement.
EP2050930B1 (de) Gekühlte Turbomaschinenschaufel
WO2019069011A1 (fr) Conduit de décharge d'un moyeu de carter intermédiaire pour turboréacteur d'aéronef comportant des canaux de refroidissement
FR3067387A1 (fr) Ecope d'alimentation en air pour l'alimentation d'un systeme de refroidissement et de controle des jeux d'une turbine
EP3317495A1 (de) Hinterkantenturbinenschaufel mit ebenen bereichen
FR3093136A1 (fr) Carter d’entree pour une turbomachine d’aeronef
EP4007842B1 (de) Mit kühlkreislauf versehene schaufel
WO2020201642A1 (fr) Aube de stator a calage variable pour une turbomachine d'aeronef
FR3114610A1 (fr) Aube d’entrée d'air pour une turbomachine d’aéronef
EP3344879B1 (de) Auslegung des hinterkanten-skelettlinienwinkels der streben, die den nebenstrom einer turbomaschine mit bypass-strömung durchqueren
WO2023242523A1 (fr) Aube a structure composite presentant une orientation de sortie de couche amelioree
WO2023242522A1 (fr) Aube a structure composite presentant une orientation de sortie de couche amelioree
FR3136810A1 (fr) Aube a structure composite presentant une orientation de sortie de couche amelioree
FR3108065A1 (fr) Systeme de ventilation pour moteur
FR3142776A1 (fr) Ensemble statorique de turbomachine
WO2021023927A1 (fr) Aube mobile pour une roue d'une turbomachine

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

17P Request for examination filed

Effective date: 19860828

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19880120

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
REF Corresponds to:

Ref document number: 3662292

Country of ref document: DE

Date of ref document: 19890413

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

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

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

Ref country code: FR

Payment date: 20040719

Year of fee payment: 19

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

Ref country code: DE

Payment date: 20040723

Year of fee payment: 19

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

Ref country code: GB

Payment date: 20040728

Year of fee payment: 19

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

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20050813

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

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060301

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20050813

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

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060428

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20060428