EP2582985B1 - Compresseur et turbomachine a rendement optimise. - Google Patents

Compresseur et turbomachine a rendement optimise. Download PDF

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Publication number
EP2582985B1
EP2582985B1 EP11735463.9A EP11735463A EP2582985B1 EP 2582985 B1 EP2582985 B1 EP 2582985B1 EP 11735463 A EP11735463 A EP 11735463A EP 2582985 B1 EP2582985 B1 EP 2582985B1
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EP
European Patent Office
Prior art keywords
blades
downstream
upstream
compressor
compressor according
Prior art date
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Application number
EP11735463.9A
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German (de)
English (en)
French (fr)
Other versions
EP2582985A1 (fr
Inventor
Vincent Paul Gabriel Perrot
Agnès PESTEIL
Lieven Baert
Vasiliki Iliopoulou
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F04D29/545—Ducts
    • 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
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow
    • 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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Definitions

  • the invention relates to axial flow compressors of a turbomachine.
  • Such compressors usually include a casing in which a paddle wheel is mounted for relative rotation, the wheel comprising a set of radial blades each having an end, a leading edge, and a trailing edge.
  • the blades are arranged in such a way that their ends pass as close as possible to the internal wall of the casing.
  • the document EP 2 180 195 A2 discloses a compressor comprising an internal shoulder and guide elements, formed on the wall of the casing, and which interact with these vortices.
  • This groove or trench is an axisymmetric groove formed in the wall of the housing.
  • This groove is hollowed out with respect to the aerodynamic reference surface which is the shape which the internal wall of the casing would have in the absence of a groove and which corresponds to the general shape of the gas passage stream.
  • the patent GB10179 gives an example of a compressor comprising such a groove.
  • the groove is formed essentially by three substantially conical surfaces, namely an upstream surface, a middle surface and a downstream surface, extending one after the other from upstream to downstream.
  • the median surface is substantially parallel to the aerodynamic reference surface.
  • the downstream surface joins the aerodynamic reference surface just downstream of the vaning edge of the blades.
  • the advantage of such a bleeding is that it allows, thanks to its surface median extending parallel to the aerodynamic reference surface, to generate only a relatively limited vortex of play. Indeed, the passage between the casing and the blade at the level of the median surface does not take place inside the aerodynamic reference surface, but is offset to the bottom of the groove, and therefore radially at a distance from the normal gas passage stream that delimits the aerodynamic reference surface. Due to this offset, the passage of fluid from the lower surface to the upper surface via the median surface is relatively low and contributes very little to the vortices of play.
  • the fluid passage is highly turbulent and contributes significantly to the game vortices.
  • this compressor comprises makes it possible to improve the efficiency of the compressor, but only to a small extent, and on the other hand does not bring any improvement, or even brings degradation, in terms of pumping margin.
  • the objective of the invention is to provide an axial flow compressor for a turbomachine, comprising a casing, having an internal wall whose general shape defines an aerodynamic reference surface delimiting a gas passage stream; an impeller, mounted for rotation relative to the casing in said vein; the wheel comprising a plurality of radial vanes each comprising an end, a leading edge, and a trailing edge; a circumferential groove being formed in the internal wall of the casing; the shape of said groove being defined essentially by three substantially conical surfaces, namely an upstream surface, a middle surface and a downstream surface, extending one after the other from upstream to downstream; the median surface being substantially parallel to said aerodynamic reference surface; and the downstream surface extending downstream at least to the trailing edge of the blades; compressor in which the efficiency losses due to the play vortices are lower, but the pumping margin at least as large, as in the compressors known previously.
  • the aerodynamic reference surface is a fictitious surface, the shape of which is what one can imagine that the casing would have had, if the groove had not been formed in its wall.
  • the upstream surface extends upstream of the leading edge of the blades, and the junction between the middle and downstream surfaces is located between 30% and 80%, and preferably between 50 and 65%, of the axial length of the blades from the leading edge.
  • the invention consists in a joint arrangement of the casing and of the shape of the tip of the blades, allowing the clearance flow to take place not inside the aerodynamic reference surface, but inside a groove arranged in the wall of the casing.
  • This groove has an innovative triple slope shape.
  • This triple slope is formed by three surfaces, each having a very specific function:
  • the median surface is that which makes it possible to maintain a significant pressure differential between the two sides, intrados and extrados, of each of the blades.
  • the median surface limits the longer part of the blade, it is the surface which is best able to limit the flow passing from the lower surface to the upper surface, because it is offset to the outside aerodynamic reference surface:
  • it is at the median surface that the path that the fluid must travel to pass from the lower surface to the upper surface is the longest, or in other words, that the radial detour imposed on the flow is the largest. For this reason, the larger the median surface, the weaker the flow of fluid passing from the lower surface to the upper surface and thus, the better the efficiency of the impeller - ignoring the side effects -.
  • the upstream and downstream surfaces have the function of and are shaped so as to minimize the formation of vortices at the entrance and at the exit of the groove.
  • the upstream surface is formed entirely upstream of the leading edge of the blade. This allows the middle surface to extend as far upstream as possible, that is to say up to the level of the leading edge of the blades.
  • the invention defines an optimized solution consisting in interrupting the median surface between 30% and 80% relative to the chord of the blades, and in arranging the downstream surface with a slight slope allowing the smooth connection of the median surface of the bleeding at the main surface (aerodynamic reference surface) of the casing.
  • the compressor according to the invention has better performance than the traditional compressor. Compared with known compressors, the compressor according to the invention provides better results in terms of efficiency and pumping margin.
  • the break in slope between the middle and downstream surfaces formed between 30% and 80% of the axial length of the blades allows a better interaction of the clearance flow with the main flow. Indeed, the downstream surface has a slight slope, which generates little vortices.
  • the arrangement of the downstream surface in a slight slope does not cause too large a reduction in the size of the middle surface.
  • the median surface is preserved with a significant size (30 to 80% of the axial length of the blade), which makes it possible to maintain a high efficiency as regards the efficiency of the compressor.
  • the adjustments made to the groove and to the blades according to the invention do not bring any specific difficulty for the manufacture of the casing or of the blades.
  • connection or junction surfaces of the connection leave type, are generally provided to connect the upstream surface in pairs. at the middle surface and the middle surface at the downstream surface.
  • junction surfaces are also provided, in general, between the upstream surface and the aerodynamic reference surface upstream of the groove, and between the downstream surface and the aerodynamic reference surface downstream of the groove.
  • the upstream surface extends upstream of the leading edge of the blades over 5 to 25%, and preferably 7 to 20%, of the inter-blade pitch separating in the circumferential direction the ends of two blades consecutive.
  • a relatively large upstream extension (more than 5% of the inter-blade pitch) of the upstream surface is preferable to a straight upstream surface, that is to say in the form of a step.
  • a vortex forms, which propagates and then mixes with the game vortex: which generates significant yield losses.
  • the downstream surface extends downstream of the trailing edge of the blades over 5 to 25%, and preferably 7 to 20%, of the inter-blade pitch separating in the circumferential direction the ends of two consecutive blades .
  • a relatively large extension downstream (more than 5% of the inter-blade pitch) of the downstream surface is preferable to a straight downstream surface, that is to say in the form of a step.
  • the downstream surface is picked up and forms a stair step in the vicinity of the trailing edge of the blade, the fluid stagnates in the corner thus formed by the bleeding and heats up as the blades pass, which creates losses in the play area which are added to those caused by the vortex directly created by walking.
  • the downstream surface in a longitudinal section, forms an angle of less than 15 °, and preferably less than 5 °, with the aerodynamic reference surface.
  • the upstream surface in a longitudinal section, forms an angle of less than 90 °, and preferably less than 30 °, with the aerodynamic reference surface.
  • the blades extend inside or to the aerodynamic reference surface, without protruding inside the groove. It is indeed desirable to limit as much as possible the disturbance of the flow occurring during the crossing of the impeller; also, it is desirable that the path of the fluid remains contained as much as possible in the aerodynamic reference surface, between the blades. It therefore does not seem desirable for the blades to extend inside the casing, thus protruding outside the reference aerodynamic surface. However, an embodiment with longer blades and penetrating inside the groove is however possible.
  • a substantially constant radial clearance extends between the end of the blades and the groove. This play may be equal to the play usually provided between the tips of the blades and the casing in the case of smooth veins, without bleeding.
  • a second objective of the invention is to propose a turbomachine comprising at least one compressor, a turbomachine in which the losses in efficiency due to the play vortices in the compressor are lower, but the pumping margin at least as great, as in the machines comprising previously known compressors.
  • the compressor is a compressor as defined above.
  • the figure 1 represents an axial flow compressor of a turbomachine 10.
  • This comprises a casing 12, in which is mounted an impeller 14.
  • the impeller 14 itself comprises a rotor disk 16, on which are fixed in a known manner oneself of the radial vanes 18, in an axisymmetric manner.
  • the impeller is arranged so that it can rotate along an axis of rotation A inside the casing 12.
  • the casing 12 has an internal wall 20 whose general shape defines a reference aerodynamic surface 22 ( fig. 3 ) delimiting a gas passage vein.
  • This aerodynamic reference surface is a surface of revolution, which has a generally substantially conical shape, and in this case cylindrical.
  • Each blade 18 has ( fig. 3 ) a leading edge 26, a trailing edge 28, and a radially outer end 24 which extends axially over a distance L from upstream to downstream.
  • a slight clearance B is provided (clearance which in certain cases can be modified as a result of friction occurring during the first hours of engine operation) between the end 24 of the blade 18 and the internal wall 20 of the casing 12.
  • the ends of the blades are spaced two by two by a distance D, in the circumferential direction, known as inter-blade pitch.
  • a circumferential groove 32 is formed in the internal wall 20 of the casing 12.
  • This groove is formed by three substantially conical surfaces, namely an upstream surface 32A, a middle surface 32B and a downstream surface 32C. These three surfaces extend one after the other from upstream to downstream (from left to right on the figure 3 ).
  • the upstream surface is of increasing diameter, the middle surface of substantially constant diameter, the downstream surface of decreasing diameter.
  • the end 24 of the blade 18 is arranged so as to maintain a substantially constant clearance B with the groove.
  • the end 24 of the blade has upstream, opposite the median surface 32B, an upstream part 24B which merges locally with the aerodynamic reference surface 22. More downstream, the end 24 of the blade has opposite downstream surface 32C (more precisely, an upstream portion of the downstream surface), a downstream part 24C.
  • the downstream part 24C is formed (like the upstream part 24B) so as to maintain a constant clearance between the end 24 of the blade and the groove 32. Also, the part 24C of the blade is trimmed or slightly shortened radially with respect to the upstream part 24B.
  • the upstream surface 32A extends upstream of the leading edge of the blades, over a distance DA which is equal to approximately 10% of the inter-blade pitch.
  • the angle ⁇ 1 formed by the upstream surface 32A, in an axial section, with the aerodynamic reference surface 22, is approximately 15 °.
  • the median surface 32B is a surface substantially parallel to the aerodynamic reference surface 22 (or “offset” (“offset”) relative to the latter).
  • offset offset
  • the section curve of the surface 24B is parallel to the section curve of the reference aerodynamic surface 22.
  • the median surface 32B extends from the leading edge of the blade 18, to a plane P situated at 50% of the distance L, relative to the leading edge 26 of the blade 18.
  • the downstream surface 32C extends downstream of the middle surface 32B at least up to the level of the trailing edge 28, and preferably beyond, to a distance DC downstream of the trailing edge 28. In the case represented in figure 3 , the downstream surface 32C extends to a distance DC equal to around 10% of the inter-blade pitch D. Also, the angle ⁇ 2 that forms the downstream surface 32C, in an axial section, with the aerodynamic reference surface 22, is worth approximately 1 °.
  • the figures 4 and 5 present comparative results from 3D numerical simulations carried out from the resolution of the Navier-Stokes equations.
  • the figure 4 presents the results of flow simulations in a compressor with a groove of known shape, and the figure 5 , the result in a compressor according to the invention.
  • the general direction A2 of the axis A of the compressor is shown on the figures 4 and 5 .
  • the general direction of fluid flow through the compressor is also indicated by an arrow.
  • the compressor partially shown in the figure 4 comprises a groove 132 formed with an upstream surface 132A, a middle surface 132B and a surface 132C.
  • the upstream 132A and downstream 132C surfaces form real stair steps arranged across the flow of fluid in the vein.
  • each of figures 4 and 5 presents a set of partial parallel cuts C1-C9.
  • Each of the sections C1-C9 schematically represents the flow in a plane.
  • the different cutting planes are parallel and extend in the direction A2 of the axis of rotation of the impeller 14 and substantially in the radial direction of the blades 18A-18C.
  • the left side of the figures 4 and 5 firstly illustrates the first effect of the invention, in the vicinity of the leading edge (26A, 26B) of the blades (18A, 18B).
  • the figure 4 shows the presence of a vortex 40 formed immediately downstream of the upstream surface. With the invention ( fig. 5 ), this vortex 40 is almost eliminated.
  • the shape of the groove 32 makes it possible to reduce the formation of vortices at the level of the upstream surface of the grooves. Indeed, we see that the vortex 40 formed on the upstream in the traditional compressor, hardly forms in the compressor according to the invention and does not magnify the main game vortex.
  • the figures show a vortex 44 more specifically linked to the shape of the trench on the downstream part of the blade. Again, especially in sections C8, C9 and in sections C3 and C4, we can see with the invention a reduction in the size of the vortex 44 in the vicinity of dawn.
  • the vortex generated in the vicinity of the downstream surface is less on the compressor according to the invention than on the traditional compressor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP11735463.9A 2010-06-17 2011-06-09 Compresseur et turbomachine a rendement optimise. Active EP2582985B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1054826A FR2961564B1 (fr) 2010-06-17 2010-06-17 Compresseur et turbomachine a rendement optimise
PCT/FR2011/051307 WO2011157927A1 (fr) 2010-06-17 2011-06-09 Compresseur et turbomachine a rendement optimise.

Publications (2)

Publication Number Publication Date
EP2582985A1 EP2582985A1 (fr) 2013-04-24
EP2582985B1 true EP2582985B1 (fr) 2020-07-15

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EP11735463.9A Active EP2582985B1 (fr) 2010-06-17 2011-06-09 Compresseur et turbomachine a rendement optimise.

Country Status (9)

Country Link
US (1) US9488179B2 (ru)
EP (1) EP2582985B1 (ru)
JP (1) JP5882311B2 (ru)
CN (1) CN102947598B (ru)
BR (1) BR112012030350B1 (ru)
CA (1) CA2801221C (ru)
FR (1) FR2961564B1 (ru)
RU (1) RU2568355C2 (ru)
WO (1) WO2011157927A1 (ru)

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Publication number Publication date
BR112012030350B1 (pt) 2020-11-17
FR2961564B1 (fr) 2016-03-04
WO2011157927A1 (fr) 2011-12-22
RU2013102076A (ru) 2014-07-27
US20130156559A1 (en) 2013-06-20
BR112012030350A2 (pt) 2016-08-09
CN102947598B (zh) 2016-05-04
EP2582985A1 (fr) 2013-04-24
CA2801221C (fr) 2018-09-04
CA2801221A1 (fr) 2011-12-22
CN102947598A (zh) 2013-02-27
JP5882311B2 (ja) 2016-03-09
RU2568355C2 (ru) 2015-11-20
JP2013529740A (ja) 2013-07-22
FR2961564A1 (fr) 2011-12-23
US9488179B2 (en) 2016-11-08

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