EP0214038B1 - Device for varying the inlet section of a turbine - Google Patents

Device for varying the inlet section of a turbine Download PDF

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Publication number
EP0214038B1
EP0214038B1 EP86401803A EP86401803A EP0214038B1 EP 0214038 B1 EP0214038 B1 EP 0214038B1 EP 86401803 A EP86401803 A EP 86401803A EP 86401803 A EP86401803 A EP 86401803A EP 0214038 B1 EP0214038 B1 EP 0214038B1
Authority
EP
European Patent Office
Prior art keywords
flap
vane
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.)
Expired
Application number
EP86401803A
Other languages
German (de)
French (fr)
Other versions
EP0214038A1 (en
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
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 filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0214038A1 publication Critical patent/EP0214038A1/en
Application granted granted Critical
Publication of EP0214038B1 publication Critical patent/EP0214038B1/en
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
    • 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

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

Description

Le présenté invention a pour objet un dispositif de variation de la section de passage d'un distributeur de turbine.The present invention relates to a device for varying the passage section of a turbine distributor.

Pour obtenir un gain de poussée dans une turbomachine, il est connu d'utiliser une variation de la section de passage des gaz, au niveau de la section la plus faible dénommée col, d'un distributeur de turbine haute pression ou basse pression, comportant un moyen de refroidissement.To obtain a thrust gain in a turbomachine, it is known to use a variation of the gas passage section, at the level of the smallest section called a neck, of a high pressure or low pressure turbine distributor, comprising a means of cooling.

Dans certains dispositifs, la variation de section est obtenue par un moyen aérodynamique. Toutefois ces moyens qui sont en général peu coûteux entraînent des chutes de rendement importantes et des perturbations dans la ventilation des aubes.In some devices, the section variation is obtained by aerodynamic means. However, these means, which are generally inexpensive, lead to significant drops in efficiency and disturbances in the ventilation of the blades.

On connaît également des dispositifs de variation de section comportant des moyens mécaniques.There are also known section variation devices comprising mechanical means.

Suivant l'un de ces procédés, on utilise une variation du calage de toute l'aube ou d'une partie de l'aube. Toutefois, ce procédé présente des difficultés provenant de la maîtrise des fuites et des étanchéités insuffisantes.According to one of these methods, a variation of the setting of the whole blade or part of the blade is used. However, this process presents difficulties stemming from the control of leaks and insufficient sealing.

On connaît également un procédé dans lequel on utilise une variation de hauteur de la veine. Dans ce but, le dispositif comporte entre les aubes fixes un volet unique monobloc articulé qui peut occuper une position escamotée et une position pour laquelle le canal est partiellement obturé.A method is also known in which a variation in the height of the vein is used. For this purpose, 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.

Toutefois, ce procédé a pour principal défaut de créer des ressauts importants dans la veine, au voisinage des talons des aubes mobiles lorsque les volets sont en position de veine réduite.However, 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.

Par ailleurs, US-A-3 992 128 et FR-A-942 182 décrivent des aubes de diffuseur d'un compressur centrifuge comportant deux parties susceptibles de s'écarter l'une de autre de manière à obtenir un réglage de la section de passage. Ces applications n'envisagent pas le refroidissement des aubes et certaines positions prévues entraînent des variations d'incidence qui n'assurent pas une continuité parfaite des écoulements.Furthermore, US-A-3,992,128 and FR-A-942,182 describe diffuser vanes of a centrifugal compressor having two parts which can move apart from each other so as to obtain an adjustment of the cross-section of passage. These applications do not envisage cooling the blades and certain planned positions cause variations in incidence which do not ensure perfect continuity of the flows.

La présente invention a pour objet un dispositif de variation de la section de passage qui ne présente pas les inconvénients mentionnés ci- dessus.The present invention relates to a device for varying the passage section which does not have the drawbacks mentioned above.

Conformément à la présente invention le volet mobile de chaqueause comporte sur sa face interne des nervures disposées parallèlement à la corde du profil, lesdites nervures constituant des organes de raidissement du volet et des ailettes de radiatour thormique.According to the present invention the movable flap of each has on its internal face of the ribs arranged parallel to the chord of the profile, said ribs constituting stiffening members of the flap and fins of heat radiator.

Le dispositif suivant l'invention permet d'obtenir une variation de la section de passage des gaz avec un minimum de pertes aérodynamiques entre le fonctionnement dit "nominal" et le fonctionnement à d'autres contitions dites "hors adaptation", la variation étant continue entre les différents points de fonctionnement.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 "out of adaptation" contitions, the variation being continuous between the different operating points.

D'autre caractéristiques et avantages de l'invention ressortiront de la description qui va suivre d'un mode de réalisation et en se référant aux dessins annexés sur lesquels:

  • La figure 1 est une vue en coupe partielle suivant la ligne 1 - de la figure 2 d'une aube de diatributeur de turbine munie du dispositif suivant l'invention.
  • La figure 2 est une vue en coupe suivant la ligne II - Il de la figure 1.
  • La figure 3 est une vue suivant la flèche III de la figure 4 de la partie arrière d'une aube.
  • La figure 4 est une vue suivant la flèche IV de la figure 3 de la partie arrière de l'aube sur sa face intrados.
  • La figure 5 est une vue en coupe suivant la ligne Y - Y de la figure 4.
Other characteristics and advantages of the invention will emerge from the description which follows of an embodiment and with reference to the appended drawings in which:
  • Figure 1 is a partial sectional view along line 1 - of Figure 2 of a turbine distributor blade provided with the device according to the invention.
  • Figure 2 is a sectional view along line II - II of Figure 1.
  • Figure 3 is a view along arrow III of Figure 4 of the rear part of a blade.
  • Figure 4 is a view along arrow IV of Figure 3 of the rear part of the blade on its lower surface.
  • FIG. 5 is a sectional view along the line Y - Y of FIG. 4.

A la figure 1, on a représenté une aube d'un diatributeur de turbine qui est pourvue, du côté intrados et sur la moitié de la corde du profil du côté du bord de fuite, d'un volet mobile 2 monté pivotant sur ladite aube autour d'un axe 3 disposé radialement.In Figure 1, there is shown a blade 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 disposed radially.

Le volet 2 en position de repos est aligné sur l'intrados de l'aube, c'est-à-dire que la face 2a suit la définition de l'intrados du profil, optimisé pour minimiser des pertes. L'autre face du volet 2 comporte des nervures 4 disposées parallèlement à la corde du profil qui augmentent sa résistance mécanique en assurant une plus grande rigidité du volet, et qui jouent le rôle d'ailettes de radiateur assurant une accélération des échanges thermiques avec l'air de refroidissement baignant ces ailettes.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.

La hauteur de l'ailette 2 occupe la totalité de la hauteur de la pale à cet endroit, excepté la partie située près des plates-formes qui comporte un rayon de raccordement. L'aube 1 sur laquelle vient s'adapter le volet mobile 2 comporte une face 5 sur l'extrados, où le profil est optimisé.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.

Sur l'autre face 6, l'aube présente des nervures 7 décalées par rapport aux nervures 4 du volet, de telle sorte qu'en position "nominale" les deux séries de nervures se chevauchent. Le pas et l'épaisseur des nervures 4 et 7 sont tels qu'ils ménagent un espace 8 entre la queue de l'aube et le volet pour faire passer l'air de refroidissement. Sur le volet 2 et sur l'aube 1, à l'emplacement de l'axe 3, les nervures 4 et 7 sont réalisées de manière à constituer une charnière à piano.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. On the shutter 2 and on the blade 1, at the location of the axis 3, the ribs 4 and 7 are produced so as to constitute a piano hinge.

L'air de refroidissement qui circule dans la cavité principale 9 de l'aube s'écoule par des trous 10 et 11 vers l'arrière. L'un des trous 10 assurant le refroidissement de la charnière avec son axe 3 et vers l'espace 8 en direction du bord de fuite, une partie de l'air, après avoir refroidi au passage les nervures 4, 7 côté intrados, s'échappe par les trous 13 prévus dans le volet 2 (Fig. 1,2,3,4) et par la fente 12 située au bord de fuite.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.

Par ailleurs, l'un des trous 11 assure également le refroidissement de la charnière et de l'intrados l'air s'échappant de celle-ci suivant la flèche F.Furthermore, one of the holes 11 also provides the cooling of the hinge and the lower surface the air escaping from it according to arrow F.

Cette disposition permet de refroidir non seulement la charnière mais toute la région du bord de fuite côté intrados, comme côté extrados.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.

Dans la position "nominale" ou de repos, le volet 2 s'appuie sur l'aube 1 par l'intermédiaire des nervures 4 qui présentent des surfaces de contact rectifiées.In the "nominal" or rest position, the shutter 2 rests on the blade 1 by means of the ribs 4 which have rectified contact surfaces.

Lorsqu'on veut restreindre la section de passage du distributeur, les volets 2 sont écartés de la partie arrière de l'aube ainsi qu'il est représenté, en trait interrompu, à la figure 3.When it is desired to restrict the passage section of the distributor, the flaps 2 are separated from the rear part of the blade as shown, in broken lines, in FIG. 3.

Dans ce but, le volet 2 comporte un taquet 14 (Fig. 3,4, 5) qui est en appui contre l'une des extrémités d'un levier 15 monté de façon articulée autour d'un axe 16 fixé sur l'aube 1, ledit levier étant situé au-dessus de la plate-forme du distributeur.For this purpose, the flap 2 comprises a cleat 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.

A son autre extrémité le levier 15 comporte un trou 17 dans lequel est engagé un organe solidaire d'un anneau, non représenté au dessin, et qui assure la liaison et l'entraînement de tous les leviers de toutes les aubes.At its other end, 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.

L'anneau de commande est actionné par un ou plusieurs vérins hydrauliques régulés.The control ring is actuated by one or more regulated hydraulic cylinders.

Claims (7)

1. Device for varying the flow cross-section in the guide vane array of a turbine, in which each vane (1) includes, on the concave side, a movable flap (2) mounted to pivot on the said vane around an axis (3) arranged radially, the said flap (2), in rest position, being aligned with the concave side of the vane (1), providing continuity of its profile, characterized in that the movable flap (2) includes, on its internal face, ribs (4) arranged parallel to the chord of the profile, the said ribs (4) constituting stiffening members for the flap and thermal cooling fins.
2. Device according to Claim 1, characterized in that the movable flap (2) extends over substantially one half of the chord of the profile of the vane (1).
3. Device according to Claim 1, characterized in that the ribs (4) provided on the internal face of the movable flap (2) mesh with corresponding ribs (7) provided on the body (1) of the vane.
4. Device according to Claim 1, characterized in that a space (8) is formed in the interior of the vane (1), between the internal face of the flap (2) and the internal face of the convex side, the said space (8) opening to the exterior through a slot situated at the trailing edge, and being traversed by the cooling air.
5. Device according to Claim 4, characterized in that the flap (2) includes at least one row of holes (13) through which the cooling air is discharged on the concave side.
6. Device according to Claim 1, characterized in that cooling holes (10, 11) are provided between the main cavity (9) of the vane and the hinge on which the flap is pivoted on the vane (1).
7. Device according to Claim 1, characterized in that each flap (2) includes a lug (14) against which is engaged a lever (15) mounted in a pivoted manner on the platform of the guide vane array, the said levers (15) corresponding to all the vanes being connected together and operated by an external ring actuated by at least one ram.
EP86401803A 1985-08-14 1986-08-13 Device for varying the inlet section of a turbine Expired EP0214038B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8512366A FR2586268B1 (en) 1985-08-14 1985-08-14 DEVICE FOR VARIATION OF THE PASSAGE SECTION OF A TURBINE DISTRIBUTOR
FR8512366 1985-08-14

Publications (2)

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

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EP86401803A Expired EP0214038B1 (en) 1985-08-14 1986-08-13 Device for varying the inlet section of a turbine

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US (1) US4705452A (en)
EP (1) EP0214038B1 (en)
DE (1) DE3662292D1 (en)
FR (1) FR2586268B1 (en)

Families Citing this family (40)

* 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
GB2262314A (en) * 1991-12-10 1993-06-16 Rolls Royce Plc Air cooled gas turbine engine aerofoil.
ES2063636B1 (en) * 1992-04-23 1997-05-01 Turbo Propulsores Ind SET OF STATOR BLADES FOR GAS TURBINE ENGINES.
FR2707338B1 (en) * 1993-07-07 1995-08-11 Snecma Variable camber turbomachine blade.
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 (en) * 2008-09-29 2010-04-01 Mtu Aero Engines Gmbh Axial flow machine with asymmetric compressor inlet guide
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
WO2014133612A1 (en) 2013-02-26 2014-09-04 Bloxham Matthew J Gas turbine engine variable geometry flow component
EP2905425B1 (en) 2014-02-06 2019-07-10 United Technologies Corporation Variable vane and seal arrangement
US10030669B2 (en) * 2014-06-26 2018-07-24 General Electric Company Apparatus for transferring energy between a rotating element and fluid
DE102014213633A1 (en) * 2014-07-14 2016-01-14 Siemens Aktiengesellschaft Adjustable nozzle ring
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
US10711702B2 (en) 2015-08-18 2020-07-14 General Electric Company Mixed flow turbocore
US10578028B2 (en) 2015-08-18 2020-03-03 General Electric Company Compressor bleed auxiliary turbine
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
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
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
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
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
US10718221B2 (en) 2015-08-27 2020-07-21 Rolls Royce North American Technologies Inc. Morphing vane
US9976514B2 (en) 2015-08-27 2018-05-22 Rolls-Royce North American Technologies, Inc. Propulsive force vectoring
EP3954882B1 (en) * 2016-03-30 2023-05-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Variable geometry turbocharger
US10480326B2 (en) * 2017-09-11 2019-11-19 United Technologies Corporation Vane for variable area turbine
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
US10934883B2 (en) * 2018-09-12 2021-03-02 Raytheon Technologies Cover for airfoil assembly for a gas turbine engine
US11686211B2 (en) 2021-08-25 2023-06-27 Rolls-Royce Corporation Variable outlet guide vanes
US11879343B2 (en) 2021-08-25 2024-01-23 Rolls-Royce Corporation Systems for controlling variable outlet guide vanes
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

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE733286C (en) * 1935-09-14 1943-03-24 Schuechtermann & Kremer Baum A Pit fan
DE659211C (en) * 1936-08-25 1938-04-28 Brandenburgische Motorenwerke Method for maintaining the same pressure in the delivery line of a loading fan for aircraft engines
FR942182A (en) * 1945-12-28 1949-02-01 Rolls Royce Improvements to centrifugal superchargers for internal combustion engines
US2866313A (en) * 1950-04-14 1958-12-30 Power Jets Res & Dev Ltd Means for cooling turbine-blades by liquid jets
GB774501A (en) * 1953-10-15 1957-05-08 Power Jets Res & Dev Ltd A stator guide vane construction for elastic fluid turbines
NL198161A (en) * 1955-06-17
US2856758A (en) * 1955-10-31 1958-10-21 Douglas Aircraft Co Inc Variable nozzle cooling turbine
US3442493A (en) * 1965-10-22 1969-05-06 Gen Electric Articulated airfoil vanes
DE1601613A1 (en) * 1967-08-03 1970-12-17 Motoren Turbinen Union Turbine blades, in particular turbine guide blades for gas turbine engines
US3563669A (en) * 1969-07-10 1971-02-16 Gen Motors Corp Variable area nozzle
JPS507108A (en) * 1973-04-09 1975-01-24
US3992128A (en) * 1975-06-09 1976-11-16 General Motors Corporation Variable diffuser
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

Also Published As

Publication number Publication date
FR2586268B1 (en) 1989-06-09
EP0214038A1 (en) 1987-03-11
FR2586268A1 (en) 1987-02-20
US4705452A (en) 1987-11-10
DE3662292D1 (en) 1989-04-13

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