FR2681644A1 - Improvements made to fans (blowers) particularly for turbojets with at least one bypass flow - Google Patents

Improvements made to fans (blowers) particularly for turbojets with at least one bypass flow Download PDF

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Publication number
FR2681644A1
FR2681644A1 FR9111628A FR9111628A FR2681644A1 FR 2681644 A1 FR2681644 A1 FR 2681644A1 FR 9111628 A FR9111628 A FR 9111628A FR 9111628 A FR9111628 A FR 9111628A FR 2681644 A1 FR2681644 A1 FR 2681644A1
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FR
France
Prior art keywords
stator
rotor
vane
compensation
vanes
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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
FR9111628A
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French (fr)
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FR2681644B1 (en
Inventor
Fournier Gerard
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Office National dEtudes et de Recherches Aerospatiales ONERA
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Office National dEtudes et de Recherches Aerospatiales ONERA
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Priority to FR9111628A priority Critical patent/FR2681644B1/en
Publication of FR2681644A1 publication Critical patent/FR2681644A1/en
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Publication of FR2681644B1 publication Critical patent/FR2681644B1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Abstract

The blower includes, from upstream to downstream, a rotor with blades 5 and a stator with vanes 6 situated downstream of the bladed rotor. The space E separating the plane of the rotor from the plane of the stator 6 lies between 0.3 C and 2 C (0.3 C < E < 2 C), C denoting the projection onto the axis of the fan of the chord of a rotor blade. The stator 6 includes a number of vanes S lying between R and 1.5 R (R < S < 1.5 R), R denoting the number of blades 5 of the rotor. Non-rotating compensation vaning 7 is located in the vicinity of the fan.

Description

Perfectionnement apporté aux soufflantes notamment pour
turboréacteurs à au moins deux flux
L'invention est relative aux soufflantes, notamment pour turboréacteurs à au moins deux flux et elle s'applique aussi bien aux soufflantes pour turboréacteurs d'avions subsoniques qu'aux soufflantes pour turboréacteurs d'avions supersoniques, dans leurs phases de vol subsonique (atterrissage et décollage). Une telle soufflante est alors généralement disposée en amont d'un ensemble essentiellement constitué par au moins un compresseur, au moins une chambre de combustion, au moins une turbine et au moins une tuyère.Improvement provided to blowers, particularly for
turbojets with at least two streams
The invention relates to blowers, in particular for turbofan engines with at least two flows, and it applies both to blowers for turbojet engines of subsonic aircraft and to blowers for supersonic aircraft turbojets, in their phases of subsonic flight (landing and take-off). Such a fan is then generally disposed upstream of an assembly consisting essentially of at least one compressor, at least one combustion chamber, at least one turbine and at least one nozzle.

Cette soufflante comprend essentiellement un rotor à aubes, entraîné par la turbine du turboréacteur, ce rotor à aubes étant suivi d'un stator à aubes. This fan essentially comprises a blade rotor, driven by the turbine of the turbojet, the paddle rotor being followed by a paddle stator.

Il est bien connu que la soufflante des turboréacteurs de ce type est génératrice d'ondes acoustiques dont on a toujours cherché à diminuer l'intensité. It is well known that the fan of turbojets of this type is generating acoustic waves whose intensity has always been sought.

On est partiellement arrivé à ce but grâce à des dispositions géométriques destinées à utiliser les propriétés de coupure acoustique présentée par les canaux empruntés par l'air dans son trajet en amont et en aval de la soufflante. On était donc conduit à réaliser des soufflantes relativement longues en espaçant au maximum le rotor du stator. This goal has been partially achieved by geometric arrangements for utilizing the acoustic cutoff properties exhibited by air channels in its path upstream and downstream of the blower. It was therefore necessary to make relatively long blowers by maximally spacing the rotor of the stator.

On a aussi contribué à ce but en augmentant le nombre d'aubes du stator, jusqu'à lui faire comporter deux fois plus d'aubes que le rotor. On était donc conduit à réaliser des soufflantes d'un prix de revient élevé. This goal has also been contributed by increasing the number of stator vanes to include twice as many vanes as the rotor. It was therefore necessary to produce blowers of a high cost.

La présente invention a pour but de réduire ces inconvénients en proposant une soufflante silencieuse, dont la longueur est diminuée par réduction de l'espace rotorstator, et dont le coût est réduit par diminution du nombre d'aubes du stator. The present invention aims to reduce these disadvantages by providing a silent blower, whose length is reduced by reducing the rotorstator space, and whose cost is reduced by reducing the number of stator blades.

Pour ce faire, le demandeur a développé l'idée consistant, d'une part, à accepter une augmentation de la perturbation de vitesse de l'écoulement dans le plan du rotor et en fonction de sa vitesse de rotation, et, d'autre part, de compenser, voir même d'annuler cette augmentation en agissant sur l'écoulement en amont ou en aval du rotor. To do this, the applicant has developed the idea of, on the one hand, accepting an increase in the speed perturbation of the flow in the plane of the rotor and as a function of its speed of rotation, and, on the other hand, on the other hand, to compensate or even cancel this increase by acting on the flow upstream or downstream of the rotor.

Selon l'invention, la soufflante comporte, d'amont en aval, un rotor à aubes et un stator à aubes, et elle est caractérisée par le fait que - l'espace E séparant le plan du rotor du plan du stator est compris entre 0,3C et 2C (0,3C < E < 2C), C désignant la projection sur l'axe de la soufflante de la corde d'une aube du rotor - le stator comporte un nombre d'aubes S compris entre R et 1,5R (R < S < 1,5R), R désignant le nombre d'aubes du rotor - un aubage de compensation non tournant est disposé au voisinage de la soufflante. According to the invention, the fan comprises, from upstream to downstream, a rotor with vanes and a stator with vanes, and it is characterized in that the space E separating the plane of the rotor from the plane of the stator is between 0.3C and 2C (0.3C <E <2C), C denoting the projection on the axis of the fan of the rope of a rotor blade - the stator comprises a number of blades S between R and 1 , 5R (R <S <1,5R), where R denotes the number of rotor blades - a non-rotating compensation vane is arranged in the vicinity of the fan.

Selon des caractéristiques préférées de l'invention, - l'espace E entre le rotor et le stator est proche de 0,5C (0,4C < E < 0,6 C) - le nombre d'aubes S du stator est un peu supérieur au nombre d'aubes R du rotor (R < S < 1,1 R). According to preferred features of the invention, - the space E between the rotor and the stator is close to 0.5C (0.4C <E <0.6C) - the number of blades S of the stator is a little greater than the number of blades R of the rotor (R <S <1.1 R).

Selon un premier mode de réalisation de l'invention l'aubage de compensation est disposé en amont du rotor de la soufflante.According to a first embodiment of the invention the compensation vane is disposed upstream of the rotor of the fan.

Selon un second mode de réalisation de l'invention (applicable notamment aux configurations de turboréacteurs dans lesquels l'entrée d'air comporte des obstacles engendrant des sillages), l'aubage de compensation est disposé en aval du stator de la soufflante, ou dans le plan du stator ; le stator constitue, dans ce dernier cas, l'aubage de compensation lui-même. According to a second embodiment of the invention (applicable in particular to turbojet configurations in which the air inlet has obstacles generating wakes), the compensation vane is disposed downstream of the stator of the fan, or in the stator plane; the stator constitutes, in the latter case, the compensation vane itself.

L'invention consiste, mises à part les dispositions dont il vient d'être question, en certaines autres dispositions dont il sera plus explicitement question ci-après et qui s'utilisent de préférence en même temps. The invention consists, apart from the provisions just mentioned, in certain other provisions which will be more explicitly discussed below and which are preferably used at the same time.

L'invention pourra, de toutes façons, être bien comprise à l'aide du complément de description qui suit, ainsi que des dessins ci-annexés, lesquels complément et dessins sont relatifs à des modes de réalisation préférés de l'invention et ne comportent, bien entendu, aucun caractère limitatif. The invention may, in any case, be well understood using the additional description which follows, as well as the accompanying drawings, which complement and drawings relate to preferred embodiments of the invention and do not include , of course, no limiting character.

La Fig. 1, de ces dessins, est une coupe axiale schématique d'une soufflante pour turboréacteur établie conformément à un premier mode de réalisation de l'invention. Fig. 1, of these drawings, is a schematic axial section of a turbojet fan according to a first embodiment of the invention.

La Fig. 2, est une coupe axiale schématique d'une soufflante pour turboréacteur d'avion supersonique établie conformément à un second mode de réalisation de l'invention. Fig. 2 is a diagrammatic axial section of a supersonic aircraft turbojet engine fan according to a second embodiment of the invention.

Les figs. 3, 4 et 5 sont des vues développées montrant respectivement trois dispositions possibles concernant la répartition des aubes du stator de la soufflante selon le mode de réalisation de la figure 2. The figs. 3, 4 and 5 are developed views respectively showing three possible arrangements concerning the distribution of the blades of the stator of the fan according to the embodiment of FIG. 2.

Comme montré sur les figures 1 et 2, la soufflante 1 pour turboréacteur à double flux est disposée en amont d'un ensemble 2 comprenant un compresseur, une chambre de combustion, une turbine et une tuyère (non représentés). As shown in Figures 1 and 2, the fan 1 for turbofan engine is disposed upstream of an assembly 2 comprising a compressor, a combustion chamber, a turbine and a nozzle (not shown).

La soufflante 1 est entourée d'un carénage 3 et comporte un moyeu axial tournant 4. The fan 1 is surrounded by a shroud 3 and comprises a rotating axial hub 4.

La soufflante 1, est constituée par un rotor à aubes 5, entraîné par la turbine du turboréacteur, et un stator à aubes 6 situé en aval du rotor à aubes 5. The fan 1 is constituted by a vane rotor 5, driven by the turbojet turbine, and a vane stator 6 located downstream of the vane rotor 5.

L'espace E séparant le plan du rotor 5 du plan du stator 6 est compris entre 0,3 C et 2 C (0,3C < E < 2C), et de préférence entre 0,4 C et 0,6 C (0,4C < E < 0,6C), C désignant la projection sur l'axe de la soufflante de la corde d'une aube du rotor 5. The space E separating the plane of the rotor 5 from the plane of the stator 6 is between 0.3 C and 2 C (0.3C <E <2C), and preferably between 0.4 C and 0.6 C (0 , 4C <E <0.6C), C designating the projection on the axis of the fan of the rope of a blade of the rotor 5.

Le stator 6 comporte un nombre d'aubes S compris entre R et 1,5R (R < S < 1,5 R), et de préférence entre R et 1,1 R (R < S < 1,1 R), R désignant le nombre d'aubes du rotor 5. The stator 6 comprises a number of blades S between R and 1.5 R (R <S <1.5 R), and preferably between R and 1.1 R (R <S <1.1 R), R designating the number of blades of the rotor 5.

Dans le mode de réalisation représenté sur la Fig. In the embodiment shown in FIG.

1, un aubage de compensation non tournant 7 est disposé au voisinage de la soufflante 1, en amont de son rotor 5. 1, a non-rotating compensation vane 7 is disposed in the vicinity of the fan 1, upstream of its rotor 5.

Cet aubage de compensation 7 peut comporter des aubes orientables. Les pièces constituant l'aubage peuvent être des profils aérodynamiques, des tiges ou des câbles tendus. This compensation vane 7 may comprise steerable vanes. The parts constituting the blading may be aerodynamic profiles, rods or tensioned cables.

Cet aubage de compensation 7 peut être monté sur un mécanisme (non représenté) permettant son déplacement angulaire. This compensation vane 7 can be mounted on a mechanism (not shown) allowing its angular displacement.

Dans le mode de réalisation représenté sur la figure 2, qui correspond à des configurations de turboréacteurs pour avions supersoniques dans lesquels les entrées d'air comportent un plan séparateur 8, engendrant des sillages, l'aubage de compensation 7 est disposé en aval du stator 6. In the embodiment shown in FIG. 2, which corresponds to jet engine configurations for supersonic aircraft in which the air inlets comprise a separator plane 8, generating wakes, the compensation vane 7 is disposed downstream of the stator. 6.

En variante la compensation est obtenue directement au moyen des aubes du stator 6 convenablement disposées pour compenser le déficit de vitesse moyenne dans le plan du rotor.As a variant, the compensation is obtained directly by means of stator vanes 6 suitably arranged to compensate for the average speed deficit in the plane of the rotor.

On peut alors envisager les dispositions suivantes concernant le stator 6 et qui permettent de compenser ce déficit de vitesse - la répartition axiale des aubes du stator 6 peut être irrégulière ; par exemple un certain nombre d'aubes du stator 6 peuvent se situer plus en aval que les autres (Fig. We can then consider the following provisions relating to the stator 6 and which compensate for this speed deficit - the axial distribution of the stator vanes 6 may be irregular; for example a number of stator vanes 6 may be further downstream than the others (Fig.

3) - la répartition circonférentielle des aubes du stator 6 peut être irrégulière : par exemple un certain nombre d'aubes du stator 6 peuvent être supprimées (Fig. 4) - les caractéristiques géométriques, notamment épaisseur et/ou corde, de certaines des aubes du stator 6 sont différentes des caractéristiques des autres aubes du stator 6 (Fig. 5).3) - the circumferential distribution of the vanes of the stator 6 may be irregular: for example a number of vanes of the stator 6 may be omitted (FIG 4) - the geometrical characteristics, in particular thickness and / or cord, of some of the vanes the stator 6 are different from the characteristics of the other vanes of the stator 6 (FIG 5).

Bien entendu, comme dans le mode de réalisation représentée sur la figure 1, les aubes de l'aubage de compensation peuvent être orientables et l'aubage de compensation peut être monté sur un mécanisme permettant son déplacement angulaire. Of course, as in the embodiment shown in Figure 1, the vanes of the compensation vane can be rotatable and the compensation vane can be mounted on a mechanism for its angular displacement.

Claims (12)

REVENDICATIONS 1 - Soufflante, notamment pour turboréacteur à au moins deux flux, comportant, d'amont en aval, un rotor à aubes (5) et un stator à aubes (6) situés en aval du rotor à aubes (5), caractérisée par le fait que - l'espace E séparant le plan du rotor (5) du plan du stator (6) est compris entre 0,3 C et 2 C (0,3 C < E < 2C), C désignant la projection sur l'axe de la soufflante de la corde d'une aube de rotor. 1 - Blower, in particular for turbojet engine with at least two flows, comprising, from upstream to downstream, a blade rotor (5) and a paddle stator (6) situated downstream of the paddle rotor (5), characterized by the fact that - the space E separating the plane of the rotor (5) from the plane of the stator (6) is between 0.3 C and 2 C (0.3 C <E <2C), C designating the projection on the axis of the fan of the rope of a rotor blade. R et 1,5 R (R < S < 1,5R), R désignant le nombre d'aubes du rotor (5), - un aubage de compensation non tournant (7) est disposé au voisinage de la soufflante.R and 1.5 R (R <S <1.5R), where R denotes the number of vanes of the rotor (5), - a non-rotating compensation vane (7) is arranged in the vicinity of the fan. - le stator (6) comporte un nombre d'aubes S compris entrethe stator (6) comprises a number of blades S between 2 - Soufflante selon la revendication 1 caractérisée par le fait que l'espace E entre le rotor (5) et le stator (6) est proche de 0,5 C (0,4 C < E < 0,6 C). 2 - blower according to claim 1 characterized in that the space E between the rotor (5) and the stator (6) is close to 0.5 C (0.4 C <E <0.6 C). 3 - Soufflante selon la revendication 1 ou 2 caractérisée par le fait que le nombre d'aubes S du stator (6) est un peu supérieur au nombre d'aubes R du rotor (5) (R < S < 1,lu).  3 - blower according to claim 1 or 2 characterized in that the number of blades S of the stator (6) is slightly greater than the number of blades R of the rotor (5) (R <S <1, lu). 4 - Soufflante selon l'une quelconque des revendications 1 à 3 caractérisée par le fait que l'aubage de compensation (7) est disposé en amont du rotor (5). 4 - blower according to any one of claims 1 to 3 characterized in that the compensation vane (7) is disposed upstream of the rotor (5). 5 - Scufflante selon l'une quelconque des revendications 1 à 3, caractérisée par le fait que l'aubage de compensation (7) est disposé en aval du stator (6). 5 - Scufflante according to any one of claims 1 to 3, characterized in that the compensation vane (7) is disposed downstream of the stator (6). 6 - Soufflante selon l'une quelconque des revendications 1 à 3, caractérisée par le fait que le stator (6) constitue l'aubage de compensation (7). 6 - blower according to any one of claims 1 to 3, characterized in that the stator (6) constitutes the compensation vane (7). 7- Soufflante selon la revendication 6, caractérisée par le fait que la répartition axiale des aubes du stator (6) est irrégulière. 7- Blower according to claim 6, characterized in that the axial distribution of the vanes of the stator (6) is irregular. 8 - Soufflante selon la revendication 6 ou 7 caractérisée par le fait que la répartition circonférentielle des aubes du stator (6) est irrégulière.  8 - Blower according to claim 6 or 7 characterized in that the circumferential distribution of the vanes of the stator (6) is irregular. 9 - Soufflante selon l'une quelconque des revendications 6 à 8, caractérisée par le fait que les caractéristiques géométriques de certaines des aubes du stator (6) sont différentes des caractéristiques des autres aubes du stator (6). 9 - blower according to any one of claims 6 to 8, characterized in that the geometric characteristics of some of the stator vanes (6) are different from the characteristics of the other blades of the stator (6). 10 - Soufflante selon l'une quelconque des revendications 1 à 9, caractérisée par le fait que l'aubage de compensation (7) comporte des aubes orientables. 10 - blower according to any one of claims 1 to 9, characterized in that the compensation vane (7) comprises orientable vanes. 11 - Soufflante selon l'une quelconque des revendications 1 à 10 caractérisée par le fait que l'aubage de compensation (7) est monté sur un mécanisme permettant son déplacement angulaire. 11 - Blower according to any one of claims 1 to 10 characterized in that the compensation vane (7) is mounted on a mechanism for its angular displacement. 12 - Soufflante selon l'une quelconque des revendications 1 à 4 caractérisée par le fait que l'aubage de compensation (7) est constitué de simples tiges ou de câbles.  12 - blower according to any one of claims 1 to 4 characterized in that the compensation vane (7) consists of simple rods or cables.
FR9111628A 1991-09-20 1991-09-20 IMPROVEMENT FOR BLOWERS, PARTICULARLY FOR TURBOREACTORS WITH AT LEAST TWO FLOWS. Expired - Fee Related FR2681644B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR9111628A FR2681644B1 (en) 1991-09-20 1991-09-20 IMPROVEMENT FOR BLOWERS, PARTICULARLY FOR TURBOREACTORS WITH AT LEAST TWO FLOWS.

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Application Number Priority Date Filing Date Title
FR9111628A FR2681644B1 (en) 1991-09-20 1991-09-20 IMPROVEMENT FOR BLOWERS, PARTICULARLY FOR TURBOREACTORS WITH AT LEAST TWO FLOWS.

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FR2681644A1 true FR2681644A1 (en) 1993-03-26
FR2681644B1 FR2681644B1 (en) 1995-02-24

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EP1624195A1 (en) * 2004-08-04 2006-02-08 Hitachi, Ltd. Axial pump
GB2471845A (en) * 2009-07-14 2011-01-19 Rolls Royce Plc Fan outlet guide vane arrangement in a turbofan gas turbine engine
ITTO20110728A1 (en) * 2011-08-04 2013-02-05 Avio Spa STATIC PALLETED SEGMENT OF A GAS TURBINE FOR AERONAUTICAL MOTORS
WO2014143426A1 (en) * 2013-03-14 2014-09-18 Elliott Company Vane arrangement having alternating vanes with different trailing edge profile
WO2015015160A1 (en) * 2013-07-29 2015-02-05 Wells John Charles Gas turbine engine inlet
US9091174B2 (en) 2011-05-13 2015-07-28 Rolls-Royce Plc Method of reducing asymmetric fluid flow effects in a passage
CN104822903A (en) * 2012-06-14 2015-08-05 Ge亚飞欧有限责任公司 Aerofoil array for a gas turbine with anti fluttering means
EP3026221A1 (en) * 2014-11-25 2016-06-01 United Technologies Corporation Vane assembly, gas turbine engine, and associated method of reducing blade vibration
FR3092868A1 (en) * 2019-02-19 2020-08-21 Safran Aircraft Engines Turbomachine stator wheel comprising blades with different chords
FR3130319A1 (en) * 2021-12-13 2023-06-16 Safran Aircraft Engines Unducted turbomachine comprising stator vanes having different chords
FR3130320A1 (en) * 2021-12-13 2023-06-16 Safran Aircraft Engines Unducted turbomachine comprising stator vanes having different chords

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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