EP0407297B1 - By-pass device for a double-flow gas-turbine engine - Google Patents

By-pass device for a double-flow gas-turbine engine Download PDF

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Publication number
EP0407297B1
EP0407297B1 EP90401927A EP90401927A EP0407297B1 EP 0407297 B1 EP0407297 B1 EP 0407297B1 EP 90401927 A EP90401927 A EP 90401927A EP 90401927 A EP90401927 A EP 90401927A EP 0407297 B1 EP0407297 B1 EP 0407297B1
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EP
European Patent Office
Prior art keywords
trap
connecting rod
primary
airflow duct
hatch
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 - Lifetime
Application number
EP90401927A
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German (de)
French (fr)
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EP0407297A1 (en
Inventor
Pierre Antoine Glowacki
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
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Publication of EP0407297A1 publication Critical patent/EP0407297A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction

Definitions

  • the invention relates to a discharge device for a double-flow gas turbine engine, such as a turbojet engine for propelling an aircraft.
  • These discharge members include several hatches distributed along the wall of the air stream and controlled synchronously.
  • the control and synchronism mechanism must quickly control the opening and closing of the doors and keep them closed tightly and is therefore relatively complex.
  • Document FR 2 260 697 also discloses a combined booster and discharge mechanism comprising a set of booster valves formed by two panels, one in the primary flow and the other in the secondary flow, articulated by a rack. , the two panels thus opening in opposite directions simultaneously in their respective streams to fulfill a feeding function.
  • Each panel has a central hatch, the two hatches opening symmetrically towards each other away from their respective veins to fulfill a discharge function.
  • the object of the present invention is to provide the discharge device with a device which makes it possible to maintain the hatches in the closed position so as to prevent their opening and their beating under the pressure of the gases in the primary flow.
  • the discharge device comprises a first pivoting hatch in each passage along the external wall of the primary gas stream and a second pivoting hatch in each passage along the internal wall of the vein secondary gas, the primary vein hatches and the secondary vein hatches being mechanically connected together;
  • this device is characterized in that the mechanical connection is constituted by a connecting rod articulated at one of its ends on a flap of the primary vein and at its other end on a flap of the secondary vein.
  • the connecting rod causes the traps of the secondary vein to pivot towards the inside of the secondary vein.
  • the connecting rod also returns the doors of the secondary vein to the closed position.
  • the pressure prevailing in the secondary vein then exerts on the corresponding flap a force which is transmitted by the connecting rod to the flap of the primary vein and keeps the latter in closed condition by preventing it from being opened under the pressure prevailing in the vein. primary.
  • a dual-flow turbojet engine of axis XX comprises a fan 12 supplying air to a primary air stream 14 and a secondary air stream 16, annular and separated by a bulkhead assembly 18.
  • a low pressure compressor 20 In the primary air stream 14, a low pressure compressor 20, an intermediate chamber 22 and a high pressure compressor 24 are successively installed.
  • a discharge passage 26 is provided in the partition 18 for separation in order to discharge part of the air flow from the intermediate chamber 22 to the flow stream. secondary air 16.
  • this force at least partially compensates for the force exerted in the reverse direction on the first hatch 28 by the pressurized air downstream of the low pressure compressor 20 in the intermediate chamber 22, so that the forces which must be contained in the command 37 are reduced accordingly.
  • We can thus lighten this mechanism and / or improve its functioning.
  • the respective sizes of the two doors 28, 38 can be chosen to will, as well as the position of the articulations 46, 48 of the connecting rod 44 on the back of the two doors relative to their pivot axes 32, 42.
  • the size of the second hatch 38 may be greater than that of the first 28 in order to compensate, at least partially, for the pressure difference between the secondary air stream 16 and the intermediate chamber 22 of the air stream primary 14.
  • the distance between the articulation point 48 of the connecting rod 44 on the second hatch 38 and the axis of rotation 42 of the latter may be less than the distance between the articulation point 46 of the connecting rod 44 on the first hatch 28 and the axis of rotation 32 thereof.
  • this arrangement will make it possible to achieve a differential opening of the two doors and thereby control the flow of air discharged from the primary air stream 14 to the secondary air stream 16.

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  • Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

L'invention concerne un dispositif de décharge pour moteur de turbine à gaz à double flux, tel qu'un turboréacteur servant à la propulsion d'un avion.The invention relates to a discharge device for a double-flow gas turbine engine, such as a turbojet engine for propelling an aircraft.

Il est connu, par exemple du document US 3 638 428, de monter dans la paroi de la veine d'air du flux primaire, entre le compresseur basse pression et le compresseur haute pression de ce flux primaire, des organes de décharge d'air ouvrant lorsque cela est nécessaire un passage d'air vers le flux secondaire, ce qui évite les phénomènes de pompage.It is known, for example from document US 3 638 428, to mount air discharge members in the wall of the air stream of the primary flow, between the low pressure compressor and the high pressure compressor of this primary flow opening when necessary an air passage to the secondary flow, which avoids pumping phenomena.

Ces organes de décharge comprennent plusieurs trappes réparties le long de la paroi de la veine d'air et commandées en synchronisme.These discharge members include several hatches distributed along the wall of the air stream and controlled synchronously.

Le mécanisme de commande et de synchronisme doit commander rapidement l'ouverture et la fermeture des trappes et maintenir celles-ci fermées de façon étanche et est de ce fait relativement complexe.The control and synchronism mechanism must quickly control the opening and closing of the doors and keep them closed tightly and is therefore relatively complex.

Il résulte des jeux cumulés de montage des différents composants de ce mécanisme que les trappes les plus éloignées du moyen de commande d'ouverture et de fermeture ne sont pas suffisamment plaquées sur leur siège et ont tendance à s'entrouvrir sous la pression des gaz provenant du compresseur basse pression; le débit de fuite ainsi créé perturbe le fonctionnement du compresseur haute pression. De plus, les trappes ont tendance à battre, ce qui engendre des vibrations et à terme des détériorations.It follows from the cumulative assembly play of the various components of this mechanism that the hatches furthest from the opening and closing control means are not sufficiently pressed against their seat and tend to open up under the pressure of the gases coming from. the low pressure compressor; the leakage flow thus created disturbs the operation of the high pressure compressor. In addition, the hatches tend to beat, which generates vibrations and ultimately deterioration.

On connaît par ailleurs du document FR 2 260 697 un mécanisme combiné de gavage et de décharge comprenant un ensemble de vannes de gavage formées de deux panneaux, l'un dans le flux primaire et l'autre dans le flux secondaire, articulés par une crémaillère, les deux panneaux s'ouvrant ainsi en sens opposés simultanément dans leur veine respective pour remplir une fonction de gavage.Document FR 2 260 697 also discloses a combined booster and discharge mechanism comprising a set of booster valves formed by two panels, one in the primary flow and the other in the secondary flow, articulated by a rack. , the two panels thus opening in opposite directions simultaneously in their respective streams to fulfill a feeding function.

Chaque panneau comporte une trappe centrale, les deux trappes s'ouvrant symétriquement l'une vers l'autre en éloignement de leurs veines respectives pour remplir une fonction de décharge.Each panel has a central hatch, the two hatches opening symmetrically towards each other away from their respective veins to fulfill a discharge function.

Dans ce cas également, les jeux d'asemblage ne permettent pas d'assurer une bonne fermeture des trappes assurant la fonction de décharge, qui sont donc susceptibles de s'entrouvrir et de battre.In this case also, the assembly clearances do not make it possible to ensure proper closing of the hatches ensuring the discharge function, which are therefore liable to open and to beat.

En outre, la pression dans la veine secondaire s'applique également sur les trappes correspondantes et tend à les entrouvrir. Ainsi, l'effort nécessaire sur le moyen de commande doit-il être plus important.In addition, the pressure in the secondary vein also applies to the corresponding hatches and tends to open them. Thus, the effort required on the control means must be greater.

Le but de la présente invention est de munir le dispositif de décharge d'un dispositif qui permette de maintenir les trappes en position fermée de manière à empêcher leur entrebaillement et leurs battements sous la pression des gaz dans le flux primaire.The object of the present invention is to provide the discharge device with a device which makes it possible to maintain the hatches in the closed position so as to prevent their opening and their beating under the pressure of the gases in the primary flow.

A cet effet, le dispositif de décharge conforme à l'invention comprend une première trappe pivotante dans chaque passage le long de la paroi externe de la veine de gaz primaire et une seconde trappe pivotante dans chaque passage le long de la paroi interne de la veine de gaz secondaire, les trappes de la veine primaire et les trappes de la veine secondaire étant mécaniquement reliées entre elles; ce dispositif est caractérisé en ce que la liaison mécanique est constituée par une bielle de liaison articulée à une de ses extrémités sur une trappe de la veine primaire et à son autre extrémité sur une trappe de la veine secondaire.To this end, the discharge device according to the invention comprises a first pivoting hatch in each passage along the external wall of the primary gas stream and a second pivoting hatch in each passage along the internal wall of the vein secondary gas, the primary vein hatches and the secondary vein hatches being mechanically connected together; this device is characterized in that the mechanical connection is constituted by a connecting rod articulated at one of its ends on a flap of the primary vein and at its other end on a flap of the secondary vein.

Ainsi, lorsque les trappes de la veine primaire pivotent vers l'extérieur de la veine, la bielle de liaison provoque le pivotement des trappes de la veine secondaire vers l'intérieur de la veine secondaire.Thus, when the traps of the primary vein pivot towards the outside of the vein, the connecting rod causes the traps of the secondary vein to pivot towards the inside of the secondary vein.

Par conséquent, lorsque le mécanisme de commande ramène les trappes de la veine primaire en position fermée, la bielle ramène également les trappes de la veine secondaire en position fermée. La pression régnant dans la veine secondaire exerce alors sur la trappe correspondante une force qui est transmise par la bielle à la trappe de la veine primaire et maintient cette dernière en condition fermée en l'empêchant de s'entrouvrir sous la pression régnant dans la veine primaire.Consequently, when the control mechanism returns the doors of the primary vein to the closed position, the connecting rod also returns the doors of the secondary vein to the closed position. The pressure prevailing in the secondary vein then exerts on the corresponding flap a force which is transmitted by the connecting rod to the flap of the primary vein and keeps the latter in closed condition by preventing it from being opened under the pressure prevailing in the vein. primary.

D'autres détails et avantages de l'invention apparaîtront clairement à la lecture de la description qui va suivre, en se référant aux dessins annexés, dans lesquels :

  • la figure 1 est une vue en coupe longitudinale partielle d'un turboréacteur double flux équipé d'un dispositif conforme à l'invention, et
  • la figure 2 est une vue en coupe agrandie du dispositif lui-même.
Other details and advantages of the invention will appear clearly on reading the description which follows, with reference to the appended drawings, in which:
  • FIG. 1 is a view in partial longitudinal section of a turbofan engine equipped with a device according to the invention, and
  • Figure 2 is an enlarged sectional view of the device itself.

Comme illustré à la figure 1, un turboréacteur 10 double flux d'axe X-X comporte une soufflante 12 fournissant de l'air à une veine d'air primaire 14 et une veine d'air secondaire 16, annulaires et séparées par un ensemble formant cloison 18.As illustrated in FIG. 1, a dual-flow turbojet engine of axis XX comprises a fan 12 supplying air to a primary air stream 14 and a secondary air stream 16, annular and separated by a bulkhead assembly 18.

Dans la veine d'air primaire 14, sont implantés successivement un compresseur basse pression 20, une chambre intermédiaire 22 et un compresseur haute pression 24.In the primary air stream 14, a low pressure compressor 20, an intermediate chamber 22 and a high pressure compressor 24 are successively installed.

Afin d'éviter dans certaines conditions de fonctionnement le pompage du compresseur basse pression 20, un passage de décharge 26 est ménagé dans la cloison 18 de séparation afin de décharger une partie du débit d'air depuis la chambre intermédiaire 22 vers la veine d'air secondaire 16.In order to avoid under certain operating conditions the pumping of the low pressure compressor 20, a discharge passage 26 is provided in the partition 18 for separation in order to discharge part of the air flow from the intermediate chamber 22 to the flow stream. secondary air 16.

Ce passage est commandé par une pluralité d'ensembles de trappes, chaque ensemble comprenant deux trappes :

  • une première trappe 28 dans la paroi extérieure 30 de la veine d'air primaire, pivotant autour d'un axe 32 sensiblement perpendiculaire à l'axe du turboréacteur ainsi qu'à la direction d'écoulement de l'air, cet axe 32 étant situé le long de la bordure amont de la trappe 28, c'est-à-dire la bordure proche du compresseur basse pression 20. Un levier 34 solidaire de la première trappe 28 fait saillie vers l'intérieur de la cloison 18 et est engagé par une tige 36 d'un mécanisme de commande 37 destiné à commander en synchronisme le pivotement de toutes les trappes 28 analogues sur le pourtour de la paroi extérieure 30 de la veine d'air primaire 14, la trappe 28 pivotant ainsi vers l'intérieur de la cloison 18, donc vers l'extérieur de la veine primaire en établissant une communication entre cette dernière et le passage de décharge 26 traversant la cloison;
  • une seconde trappe 38, dans la paroi intérieure 40 de la veine d'air secondaire 16, pivotant également autour d'un axe 42 perpendiculaire à l'axe du tambour situé le long de la bordure amont de cette seconde tappe 38,
  • et une bielle de liaison 44 entre la première et la seconde trappe 28, 38, articulée à ses deux extrémités 46, 48 sur le dos des deux trappes respectivement.
This passage is controlled by a plurality of sets of hatches, each set comprising two hatches:
  • a first hatch 28 in the outer wall 30 of the primary air stream, pivoting about an axis 32 substantially perpendicular to the axis of the turbojet engine as well as to the direction of air flow, this axis 32 being located along the upstream edge of the hatch 28, that is to say the edge close to the low pressure compressor 20. A lever 34 secured to the first hatch 28 projects towards the inside of the partition 18 and is engaged by a rod 36 of a control mechanism 37 intended to control in synchronism the pivoting of all the similar hatches 28 around the periphery of the outer wall 30 of the primary air stream 14, the hatch 28 thus pivoting inwards of the partition 18, therefore towards the outside of the primary vein by establishing a communication between the latter and the discharge passage 26 passing through the partition;
  • a second hatch 38, in the inner wall 40 of the secondary air stream 16, also pivoting about an axis 42 perpendicular to the axis of the drum located along the upstream edge of this second valve 38,
  • and a connecting rod 44 between the first and the second hatch 28, 38, articulated at its two ends 46, 48 on the back of the two hatches respectively.

Ainsi, comme illustré en détail à la figure 2, lorsque la tige 36 du mécanisme de commande provoque le pivotement de la première trappe 28 en éloignement de la veine d'air 14, la trappe 28 repousse la bielle 44 et celle-ci provoque à son tour le pivotement de la seconde trappe 38 vers l'intérieur de la veine d'air secondaire 16 ouvrant ainsi le passage de décharge 26 vers la veine secondaire.Thus, as illustrated in detail in FIG. 2, when the rod 36 of the control mechanism causes the first flap 28 to pivot away from the air stream 14, the flap 28 pushes the connecting rod 44 and the latter causes in turn the pivoting of the second hatch 38 towards the inside of the secondary air stream 16 thus opening the discharge passage 26 towards the secondary stream.

Inversement, lorsque le mécanisme de commande fait pivoter la première trappe 28 en retour vers la paroi extérieure 30 de la veine primaire 14, la bielle 44 fait également pivoter la seconde trappe 38 en retour vers la paroi intérieure 40 de la veine secondaire 16, c'est-à-dire la position illustrée à la figure 1.Conversely, when the control mechanism pivots the first flap 28 back to the outer wall 30 of the primary vein 14, the connecting rod 44 also swivels the second flap 38 back to the inner wall 40 of the secondary vein 16, c that is to say the position illustrated in FIG. 1.

Dans cette situation, la pression d'air régnant dans la veine secondaire 16 exerce sur la seconde trappe 38 une force, dirigée vers l'intérieur de la cloison 18, qui est transmise par la bielle 44 à la première trappe 28, ce qui aide à maintenir cette dernière correctement fermée et évite son entrebaillement et ses battements, même lorsque la trappe 28 en question se trouve être la plus éloignée de l'organe d'entrée du mécanisme de commande 37 et que les jeux des composants du mécanisme se cumulent au point de ne pouvoir permettre un maintien précis de cette trappe.In this situation, the air pressure prevailing in the secondary vein 16 exerts on the second hatch 38 a force, directed towards the inside of the partition 18, which is transmitted by the connecting rod 44 to the first hatch 28, which helps keeping the latter properly closed and avoiding its opening and its beating, even when the hatch 28 in question is found to be the furthest from the input member of the control mechanism 37 and that the clearances of the components of the mechanism accumulate at the point of not being able to allow a precise maintenance of this hatch.

En outre, cette force compense au moins partiellement la force exercée en direction inverse sur la première trappe 28 par l'air sous pression en aval du compresseur basse pression 20 dans la chambre intermédiaire 22, de sorte que les efforts que doit contenir le mécanisme de commande 37 sont réduits d'autant. On peut ainsi alléger ce mécanisme et/ou améliorer son fonctionnement.In addition, this force at least partially compensates for the force exerted in the reverse direction on the first hatch 28 by the pressurized air downstream of the low pressure compressor 20 in the intermediate chamber 22, so that the forces which must be contained in the command 37 are reduced accordingly. We can thus lighten this mechanism and / or improve its functioning.

Comme il apparaîtra clairement à l'homme de métier, les tailles respectives des deux trappes 28, 38 peuvent être choisies à volonté, de même que la position des articulations 46, 48 de la bielle 44 sur le dos des deux trappes par rapport à leurs axes de pivotement 32, 42.As will be clear to those skilled in the art, the respective sizes of the two doors 28, 38 can be chosen to will, as well as the position of the articulations 46, 48 of the connecting rod 44 on the back of the two doors relative to their pivot axes 32, 42.

Notamment, la taille de la seconde trappe 38 pourra être supérieure à celle de la première 28 afin de compenser, au moins partiellement, l'écart de pression entre la veine d'air secondaire 16 et la chambre intermédiaire 22 de la veine d'air primaire 14.In particular, the size of the second hatch 38 may be greater than that of the first 28 in order to compensate, at least partially, for the pressure difference between the secondary air stream 16 and the intermediate chamber 22 of the air stream primary 14.

Par ailleurs, la distance entre le point d'articulation 48 de la bielle 44 sur la seconde trappe 38 et l'axe de rotation 42 de celle-ci pourra être inférieure à la distance entre le point d'articulation 46 de la bielle 44 sur la première trappe 28 et l'axe de rotation 32 de celle-ci.Furthermore, the distance between the articulation point 48 of the connecting rod 44 on the second hatch 38 and the axis of rotation 42 of the latter may be less than the distance between the articulation point 46 of the connecting rod 44 on the first hatch 28 and the axis of rotation 32 thereof.

Outre un meilleur équilibrage des forces antagonistes que les trappes 28, 38 exercent sur la bielle 44, cette disposition permettra de réaliser une ouverture différentielle des deux trappes et de ce fait de contrôler le débit d'air déchargé depuis la veine d'air primaire 14 vers la veine d'air secondaire 16.In addition to better balancing of the opposing forces that the doors 28, 38 exert on the connecting rod 44, this arrangement will make it possible to achieve a differential opening of the two doors and thereby control the flow of air discharged from the primary air stream 14 to the secondary air stream 16.

Claims (4)

  1. Discharge device for bypass gas turbine engine (10) comprising a primary airflow duct (14) and a secondary airflow duct (16) separated by a dividing wall (18), the discharge device comprising a plurality of discharge passages (26) passing through the said dividing wall (18) from the said primary airflow duct to the said secondary airflow duct , a first hinged trap (28) in each passage (26) along the length of the outer wall (30) of the primary airflow duct (14) and a second hinged trap (38) in each passage along the length of the inner wall (40) of the secondary airflow duct (16), the first and second traps (28, 38) being mechanically interlinked, characterised in that the mechanical linkage comprises a connecting rod (44) articulated at one of its ends (44) to the first trap (28) and at its other end (48) to the second trap (38).
  2. Device in accordance with Claim 1, characterised in that the first and second traps (28, 38) are fitted to pivot about axes (32, 42) situated along their upstream edges.
  3. Device in accordance with either of Claims 1 and 2, characterised in that the first trap (28) and the second trap (38) are of different sizes.
  4. Device in accordance with any of Claims 1 to 3, characterised in that the distance separating the pivot point (46) of the connecting rod (44) on the first trap (28) and the hinge axis (32) of this latter is different from the distance separating the pivot point (48) of the connecting rod (44) on the second trap and the hinge axis (42) of this latter.
EP90401927A 1989-07-05 1990-07-04 By-pass device for a double-flow gas-turbine engine Expired - Lifetime EP0407297B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8909027A FR2649445B1 (en) 1989-07-05 1989-07-05 DISCHARGE DEVICE FOR A DOUBLE-FLOW GAS TURBINE ENGINE
FR8909027 1989-07-05

Publications (2)

Publication Number Publication Date
EP0407297A1 EP0407297A1 (en) 1991-01-09
EP0407297B1 true EP0407297B1 (en) 1993-03-31

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EP90401927A Expired - Lifetime EP0407297B1 (en) 1989-07-05 1990-07-04 By-pass device for a double-flow gas-turbine engine

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US (1) US5119625A (en)
EP (1) EP0407297B1 (en)
DE (1) DE69001214T2 (en)
FR (1) FR2649445B1 (en)

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GB2259328B (en) * 1991-09-03 1995-07-19 Gen Electric Gas turbine engine variable bleed pivotal flow splitter
CA2133793A1 (en) * 1994-10-06 1996-04-07 William E. Carscallen Inter compressor duct variable geometry annular diffuser/bleed valve
FR2823532B1 (en) 2001-04-12 2003-07-18 Snecma Moteurs DISCHARGE SYSTEM FOR A TURBO-JET OR TURBO-PROPELLER WITH SIMPLIFIED CONTROL
FR2831608B1 (en) 2001-10-31 2004-01-02 Snecma Moteurs UNLOADING DEVICE IN A DOUBLE-FLOW REACTOR TURBO
FR2920134B1 (en) * 2007-08-20 2010-02-26 Aircelle Sa NACELLE EQUIPPED WITH AT LEAST ONE OVERPRESSURE TRAPPER
US20120070271A1 (en) 2010-09-21 2012-03-22 Urban Justin R Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events
US8935926B2 (en) 2010-10-28 2015-01-20 United Technologies Corporation Centrifugal compressor with bleed flow splitter for a gas turbine engine
EP2900959B1 (en) * 2012-09-26 2019-05-01 United Technologies Corporation Bleed duct for laminar fan duct flow
US9518513B2 (en) 2012-10-12 2016-12-13 General Electric Company Gas turbine engine two degree of freedom variable bleed valve for ice extraction
US9982598B2 (en) * 2012-10-22 2018-05-29 General Electric Company Gas turbine engine variable bleed valve for ice extraction
DE102013215371A1 (en) 2013-08-05 2015-02-05 Rolls-Royce Deutschland Ltd & Co Kg Apparatus and method for blowing off compressor air in an engine
DE102014221049A1 (en) * 2014-10-16 2016-04-21 Rolls-Royce Deutschland Ltd & Co Kg Arrangement and method for blowing off compressor air in an engine
GB201419756D0 (en) 2014-11-06 2014-12-24 Rolls Royce Plc Bleed valve
FR3057620B1 (en) * 2016-10-18 2020-07-31 Safran Aircraft Engines PROPULSION ASSEMBLY INCLUDING A GAS GENERATOR SUPPLY DUCT IN AN INTER-VEIN CRANKCASE
US10830179B2 (en) 2017-03-01 2020-11-10 General Electric Company Variable bleed valve door assembly and system for gas turbine engines
US10830438B2 (en) * 2017-10-12 2020-11-10 Raytheon Technologies Corporation Modulated combustor bypass
FR3107086B1 (en) * 2020-02-10 2023-04-14 Safran Aircraft Engines Relief valve with gate and vane actuated in a coordinated way

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US3638428A (en) * 1970-05-04 1972-02-01 Gen Electric Bypass valve mechanism
FR2260697B1 (en) * 1974-02-11 1976-06-25 Snecma
US4010608A (en) * 1975-06-16 1977-03-08 General Electric Company Split fan work gas turbine engine
DE2740904A1 (en) * 1977-09-10 1979-03-22 Motoren Turbinen Union DEVICE FOR OPERATING SHUT-OFF ELEMENTS IN GAS TURBINE ENGINES, IN PARTICULAR GAS TURBINE JET

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Publication number Publication date
FR2649445A1 (en) 1991-01-11
DE69001214D1 (en) 1993-05-06
FR2649445B1 (en) 1991-10-04
US5119625A (en) 1992-06-09
EP0407297A1 (en) 1991-01-09
DE69001214T2 (en) 1993-09-23

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