FR2900692A1 - High pressure compressor blade for turbo-machine of aviation, has suction device with orifices distributed in groups and inclined towards leading edge, and suction channels each communicating with respective group of orifices - Google Patents
High pressure compressor blade for turbo-machine of aviation, has suction device with orifices distributed in groups and inclined towards leading edge, and suction channels each communicating with respective group of orifices Download PDFInfo
- Publication number
- FR2900692A1 FR2900692A1 FR0651634A FR0651634A FR2900692A1 FR 2900692 A1 FR2900692 A1 FR 2900692A1 FR 0651634 A FR0651634 A FR 0651634A FR 0651634 A FR0651634 A FR 0651634A FR 2900692 A1 FR2900692 A1 FR 2900692A1
- Authority
- FR
- France
- Prior art keywords
- orifices
- blade
- groups
- suction
- channels
- 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
Links
- 239000007789 gas Substances 0.000 description 10
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 238000007664 blowing Methods 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- 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
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/306—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the suction side of a rotor blade
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
PALE DE COMPRESSEUR COMPRENANT UN DISPOSITIF D'ASPIRATIONCOMPRESSOR BLADE COMPRISING A SUCTION DEVICE
DESCRIPTIONDESCRIPTION
Cette invention concerne une pale de compresseur comprenant un dispositif d'aspiration, et notamment, mais pas exclusivement, une pale de compresseur à haute pression. La recherche de performances accrues dans les turbomachines a conduit à proposer des pales munies de dispositifs d'aspiration afin d'absorber une partie de la couche limite. Les dispositifs d'aspiration ordinaires comprennent une série d'orifices débouchant sur une portion de la surface de la pale où l'aspiration doit être produite et un canal interne de la pale communiquant aux orifices et, par son autre extrémité, à un autre canal ou à une cavité portée à plus basse pression, si bien qu'une circulation du gaz des orifices à cet autre canal ou à cette cavité s'instaure pour donner l'aspiration. Les orifices d'aspiration sont normalement répartis en une colonne de direction sensiblement radiale s'étendant sur au moins la plus grande partie de la hauteur de la pale, sur une bande de celle-ci où la compression du gaz atteint une valeur déterminée pour laquelle la diminution de la couche limite est décidée. Un exemple est donné dans le brevet GB 1 085 227. De tels dispositifs deviennent cependant insuffisants pour les compresseurs à haute pression des turbomachines aujourd'hui employées dans l'aviation, qui doivent réaliser des taux de compression de l'ordre de 2 avec de grandes vitesses périphériques. L'accroissement de la compression du gaz est plus sensible en bout de pale, de sorte que la pression dans le canal interne à la pale devient plus élevée au point de menacer, avec les conceptions connues, d'une recirculation du gaz, produite si le gaz aspiré dans le canal atteint une pression excédant celle du gaz environnant dans une région plus proche du pied de la pale. Les orifices situés à cette hauteur de la pale seraient alors le siège de soufflage de gaz hors du canal, c'est-à-dire d'une inversion de l'aspiration. C'est pour obvier à ce défaut que l'invention fut conçue, et pour permettre d'appliquer l'aspiration de couche limite à des pales fonctionnant à des caractéristiques de compression et de vitesses élevées. Sous sa forme la plus générale, l'invention est relative à une pale de compression comprenant un dispositif d'aspiration, le dispositif d'aspiration comprenant un réseau d'orifices débouchant sur une bande de surface de la pale s'étendant dans une direction essentiellement radiale de la pale, caractérisée en ce que les orifices sont répartis en groupes et en ce que le dispositif d'aspiration comprend encore une pluralité de canaux d'aspiration internes à la pale dont chacun communique à un groupe respectif des orifices. Le dispositif d'aspiration est ainsi fractionné ; et comme chaque groupe d'orifices débouche sur du gaz de pression peu différente, les risques de recirculation par soufflage hors de certains des orifices sont désormais exclus. Une direction fortement oblique des groupes d'orifices par rapport à la direction essentiellement radiale de la bande d'aspiration est souvent nécessaire, à la fois pour que le nombre total d'orifices soit suffisant pour couvrir toute la bande d'aspiration et pour que les canaux soient bien séparés. On peut donc arriver à une situation où les alignements formés par les groupes d'orifices ne sont pas en prolongement mais superposés les uns sur les autres. Quoi qu'il en soit, leur extension dans la direction essentiellement radiale de la pale sera souvent identique ou à peu près, afin de ne pas franchir le différentiel de pression au-delà duquel les recirculations sont à craindre. La bande d'aspiration s'étendra souvent entre 40% et 60% de la longueur de corde de la pale, mesurée entre le bord d'attaque et le bord de fuite. This invention relates to a compressor blade comprising a suction device, and in particular, but not exclusively, a high-pressure compressor blade. The search for increased performance in turbomachines has led to the provision of blades with suction devices to absorb a portion of the boundary layer. The ordinary suction devices comprise a series of orifices opening onto a portion of the surface of the blade where the suction must be produced and an internal channel of the blade communicating with the orifices and, at its other end, to another channel. or a cavity carried at lower pressure, so that a flow of gas from the orifices to this other channel or cavity is established to give suction. The suction ports are normally distributed in a substantially radial column of direction extending over at least the greater part of the height of the blade, on a strip thereof where the compression of the gas reaches a predetermined value for which the reduction of the boundary layer is decided. An example is given in patent GB 1 085 227. Such devices however become insufficient for the high-pressure compressors of turbomachines nowadays used in aviation, which must achieve compression ratios of the order of 2 with high peripheral speeds. The increase in the compression of the gas is more sensitive at the end of the blade, so that the pressure in the internal channel of the blade becomes higher, to the point of threatening, with the known designs, a recirculation of the gas, produced if the gas sucked into the channel reaches a pressure exceeding that of the surrounding gas in a region closer to the foot of the blade. The orifices located at this height of the blade would then be the seat of gas blowing out of the channel, that is to say a reversal of the suction. It is to obviate this defect that the invention was conceived, and to make it possible to apply the boundary-layer suction to blades operating with compression characteristics and high speeds. In its most general form, the invention relates to a compression blade comprising a suction device, the suction device comprising an array of orifices opening onto a surface strip of the blade extending in one direction. essentially radial of the blade, characterized in that the orifices are distributed in groups and in that the suction device further comprises a plurality of suction channels internal to the blade, each of which communicates with a respective group of orifices. The suction device is thus fractionated; and as each group of orifices opens on a little different pressure gas, the risks of recirculation by blowing out some of the orifices are now excluded. A strongly oblique direction of the groups of orifices relative to the substantially radial direction of the suction strip is often necessary, both so that the total number of orifices is sufficient to cover the entire suction strip and for the channels are well separated. We can therefore arrive at a situation where the alignments formed by the groups of orifices are not in extension but superimposed on each other. Whatever the case may be, their extension in the essentially radial direction of the blade will often be identical or nearly so as not to cross the pressure differential beyond which recirculations are to be feared. The suction strip will often extend between 40% and 60% of the rope length of the blade, measured between the leading edge and the trailing edge.
Selon une autre caractéristique optionnelle mais avantageuse, les canaux pourront avoir une section s'évasant à partir d'une extrémité distale à l'endroit des groupes d'orifices afin de réduire encore les risques de recirculation. According to another optional but advantageous feature, the channels may have a section flaring from a distal end at the location of the groups of orifices to further reduce the risk of recirculation.
L'invention sera maintenant décrite plus en détail au moyen des figures annexées suivantes : - la figure 1 est une vue générale de la pale, - la figure 2 est une vue de détail, - la figure 3 une coupe transversale. The invention will now be described in more detail by means of the following appended figures: FIG. 1 is a general view of the blade, FIG. 2 is a detail view, FIG. 3 is a cross section.
La figure 1 montre une réalisation possible où une pale 1 de compresseur, fixée à un rotor 2 par un pied 3, comprend un dispositif d'aspiration conforme à l'invention. Le compresseur est représenté très partiellement et seulement où le rotor se joint à la pale, puisqu'il n'est pas différent de compresseurs connus. Des orifices 4 débouchent à la surface de la pale 1 le nombre de trous est fonction de la largeur de la zone (40 à 60%), de l'angle d'inclinaison des canaux et de la distance entre 2 trous consécutifs et du taux d'aspiration sur une région 5 d'aspiration s'étendant en bande essentiellement radiale, c'est-à-dire perpendiculaire à l'axe X du rotor 2, mais qui peut cependant présenter une certaine inclinaison, d'après l'inclinaison de la pale 1 en direction longitudinale ou d'autres critères. La région 5 sera souvent limitée par des lignes fictives tracées à proportions uniformes de distance des bords d'attaque 6 et de fuite 7 de la pale 1 ; dans bien des exemples concrets, elle sera fréquemment limitée par deux lignes 8 et 9 situées à 40% et 60% de la longueur de corde entre le bord d'attaque 6 et le bord de fuite 7. Les orifices 4 sont répartis par groupes 10 alignés et qui s'étendent sur des distances radiales 11 modérées, limitées à 10% ou 20% de la hauteur totale de la pale 1 dans certains cas plausibles mais qui dépendent de la vitesse périphérique de la pale 1. D'après la nécessité de couvrir toute la région 5 par les orifices 4, les groupes 10 présentent souvent une inclinaison marquée dans la direction longitudinale de l'axe X. FIG. 1 shows a possible embodiment in which a compressor blade 1, fixed to a rotor 2 by a stand 3, comprises a suction device according to the invention. The compressor is shown very partially and only where the rotor joins the blade, since it is no different from known compressors. Orifices 4 open on the surface of the blade 1 the number of holes is a function of the width of the zone (40 to 60%), the angle of inclination of the channels and the distance between 2 consecutive holes and the rate on a suction region extending in an essentially radial strip, that is to say perpendicular to the X axis of the rotor 2, but which may however have a certain inclination, according to the inclination of the blade 1 in the longitudinal direction or other criteria. The region 5 will often be limited by dummy lines drawn at uniform proportions of distance from the leading edges 6 and leakage 7 of the blade 1; in many concrete examples, it will be frequently limited by two lines 8 and 9 situated at 40% and 60% of the rope length between the leading edge 6 and the trailing edge 7. The orifices 4 are distributed in groups 10 aligned and extending over moderate radial distances 11, limited to 10% or 20% of the total height of the blade 1 in certain plausible cases but depending on the peripheral speed of the blade 1. covering the entire region 5 through the orifices 4, the groups 10 often have a marked inclination in the longitudinal direction of the X axis.
Le nombre d'orifices 4 dans chaque groupe 10 dépend de la largeur de la région 5, de l'angle d'inclinaison des canaux 12, du taux d'aspiration et de la distance entre deux orifices 4 consécutifs. The number of orifices 4 in each group 10 depends on the width of the region 5, the angle of inclination of the channels 12, the suction rate and the distance between two consecutive orifices 4.
La pale 1 est creusée de canaux 12 distincts, sensiblement parallèles et dont chacun dessert un groupe 10 des orifices 4. Chacun des canaux 12 comprend une portion distale 13 dont l'extrémité communique aux orifices 4 du groupe 10 concerné et qui est à l'inclinaison de ce groupe et une portion proximale 14 de raccordement à une cavité 19 incluse dans le rotor 2 et en dépression par rapport à l'environnement de la pale 1. La réalisation représentée des canaux 13 comprend un coude entre les deux portées. Une forme rectiligne ou pourvue de peu de changement de direction est préférée quand elle est possible. Les canaux 12 restent favorablement distincts les uns des autres dans toute la pale 1, jusqu'à la cavité 19, afin de diminuer les risques de mise en surpression et de recirculation. Un écartement suffisant des canaux 12 permet de les creuser plus facilement dans la pale 1 et peut être obtenu plus facilement, du moins aux portions distales 13, si elles et les groupes 10 d'orifices 4 sont inclinés plus fortement de la direction radiale. La division du dispositif d'aspiration et le petit nombre d'orifices 4 desservis par chaque canal 12 qui en est le corollaire explique que le gaz entrant dans les orifices 4 d'un même groupe 10 soit à une pression sensiblement uniforme et que les risques de surpression dans les canaux et de recirculation des gaz par soufflage soient éliminés. La figure 2 illustre que la portion distale 13 des canaux 12 présente avantageusement, à partir d'une extrémité 16, une première partie 17 dont la section droite s'évase, puis une deuxième partie 18 dont la section droite se contracte progressivement au contraire vers la portion proximale 14. La première partie 17 est placée à l'endroit des orifices 4 desservis par le canal 12, et la deuxième partie 18 est placée après cet endroit, et ne communique pas à l'extérieur de la pale 1. Cette disposition facilite l'entrée d'air par chacun des orifices 4 et s'oppose ainsi à la recirculation dans le canal 12 grâce à l'augmentation progressive de section qui diminue la pression statique dans la première partie 17, puis permet la formation d'une pression statique plus élevée en aval de l'écoulement, dans la deuxième partie 18 et après elle, grâce à la diminution de section, une fois que l'écoulement régulier a été formé. Enfin, la figure 3 montre que les orifices d'aspiration 4 sont avantageusement inclinés vers le bord d'attaque 6, de l'intérieur vers l'extérieur de la pale 1, afin de faciliter l'aspiration. The blade 1 is hollowed out with distinct, substantially parallel channels 12, each of which serves a group 10 of the orifices 4. Each of the channels 12 comprises a distal portion 13 whose end communicates with the orifices 4 of the group 10 concerned and which is at the inclination of this group and a proximal portion 14 of connection to a cavity 19 included in the rotor 2 and in depression relative to the environment of the blade 1. The embodiment shown channels 13 comprises a bend between the two ranges. A rectilinear shape or provided with little change of direction is preferred when it is possible. The channels 12 remain favorably distinct from each other throughout the blade 1, to the cavity 19, to reduce the risk of overpressure and recirculation. A sufficient spacing of the channels 12 makes it possible to dig them more easily in the blade 1 and can be obtained more easily, at least at the distal portions 13, if they and the groups 10 of orifices 4 are inclined more strongly in the radial direction. The division of the suction device and the small number of orifices 4 served by each channel 12 which is the corollary explains that the gas entering the orifices 4 of the same group 10 is at a substantially uniform pressure and that the risks overpressure in the channels and recirculation of the gases by blowing are eliminated. FIG. 2 illustrates that the distal portion 13 of the channels 12 advantageously has, from one end 16, a first portion 17 whose cross-section flares out, then a second portion 18 whose cross-section progressively contracts, on the contrary, towards the proximal portion 14. The first part 17 is placed at the place of the orifices 4 served by the channel 12, and the second part 18 is placed after this place, and does not communicate outside the blade 1. This provision facilitates the entry of air through each of the orifices 4 and thus opposes recirculation in the channel 12 through the gradual increase in section which decreases the static pressure in the first part 17, then allows the formation of a higher static pressure downstream of the flow, in the second part 18 and after it, due to the section decrease, once the regular flow has been formed. Finally, Figure 3 shows that the suction ports 4 are advantageously inclined towards the leading edge 6, from the inside to the outside of the blade 1, to facilitate suction.
Claims (6)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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FR0651634A FR2900692B1 (en) | 2006-05-05 | 2006-05-05 | COMPRESSOR BLADE COMPRISING A SUCTION DEVICE |
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FR0651634A FR2900692B1 (en) | 2006-05-05 | 2006-05-05 | COMPRESSOR BLADE COMPRISING A SUCTION DEVICE |
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FR2900692A1 true FR2900692A1 (en) | 2007-11-09 |
FR2900692B1 FR2900692B1 (en) | 2012-03-09 |
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FR0651634A Active FR2900692B1 (en) | 2006-05-05 | 2006-05-05 | COMPRESSOR BLADE COMPRISING A SUCTION DEVICE |
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Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2927673A1 (en) * | 2008-02-14 | 2009-08-21 | Snecma Sa | Fan blade for turbine engine of airplane, has two vents exclusively transporting less percentages of air, which enters into turbine engine along main axis and runs along blade during normal operation, from inlet orifices to outlet orifices |
FR2927674A1 (en) * | 2008-02-14 | 2009-08-21 | Snecma Sa | Fan blade for turbine engine of airplane, has two vents exclusively transporting less percentages of air, which enters into turbine engine along main axis and runs along blade during normal operation, from inlet orifices to outlet orifices |
WO2021016146A1 (en) * | 2019-07-22 | 2021-01-28 | Carrier Corporation | Centrifugal or mixed-flow compressor including aspirated diffuser |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1085227A (en) * | 1963-07-26 | 1967-09-27 | Rolls Royce | Improvements in or relating to gas turbine engines |
DE1938132A1 (en) * | 1969-07-26 | 1971-01-28 | Daimler Benz Ag | Guide vanes of axial compressors |
US5480284A (en) * | 1993-12-20 | 1996-01-02 | General Electric Company | Self bleeding rotor blade |
WO2001055559A1 (en) * | 2000-01-27 | 2001-08-02 | Siemens Aktiengesellschaft | Porous turbine blades and turbine equipped with blades of this type |
WO2003071113A1 (en) * | 2002-02-19 | 2003-08-28 | Alstom Technology Ltd | Turboblower and method for operating such a turboblower |
EP1643136A1 (en) * | 2004-09-30 | 2006-04-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Method for circulating air in a turbocompressor |
-
2006
- 2006-05-05 FR FR0651634A patent/FR2900692B1/en active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1085227A (en) * | 1963-07-26 | 1967-09-27 | Rolls Royce | Improvements in or relating to gas turbine engines |
DE1938132A1 (en) * | 1969-07-26 | 1971-01-28 | Daimler Benz Ag | Guide vanes of axial compressors |
US5480284A (en) * | 1993-12-20 | 1996-01-02 | General Electric Company | Self bleeding rotor blade |
WO2001055559A1 (en) * | 2000-01-27 | 2001-08-02 | Siemens Aktiengesellschaft | Porous turbine blades and turbine equipped with blades of this type |
WO2003071113A1 (en) * | 2002-02-19 | 2003-08-28 | Alstom Technology Ltd | Turboblower and method for operating such a turboblower |
EP1643136A1 (en) * | 2004-09-30 | 2006-04-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Method for circulating air in a turbocompressor |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2927673A1 (en) * | 2008-02-14 | 2009-08-21 | Snecma Sa | Fan blade for turbine engine of airplane, has two vents exclusively transporting less percentages of air, which enters into turbine engine along main axis and runs along blade during normal operation, from inlet orifices to outlet orifices |
FR2927674A1 (en) * | 2008-02-14 | 2009-08-21 | Snecma Sa | Fan blade for turbine engine of airplane, has two vents exclusively transporting less percentages of air, which enters into turbine engine along main axis and runs along blade during normal operation, from inlet orifices to outlet orifices |
WO2021016146A1 (en) * | 2019-07-22 | 2021-01-28 | Carrier Corporation | Centrifugal or mixed-flow compressor including aspirated diffuser |
CN112955661A (en) * | 2019-07-22 | 2021-06-11 | 开利公司 | Centrifugal or mixed flow compressor comprising a suction diffuser |
Also Published As
Publication number | Publication date |
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FR2900692B1 (en) | 2012-03-09 |
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