EP0468877B1 - Dispositif de pompage ou de compression polyphasique et son utilisation - Google Patents

Dispositif de pompage ou de compression polyphasique et son utilisation Download PDF

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Publication number
EP0468877B1
EP0468877B1 EP91402038A EP91402038A EP0468877B1 EP 0468877 B1 EP0468877 B1 EP 0468877B1 EP 91402038 A EP91402038 A EP 91402038A EP 91402038 A EP91402038 A EP 91402038A EP 0468877 B1 EP0468877 B1 EP 0468877B1
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EP
European Patent Office
Prior art keywords
vanes
accordance
previous
axis
impeller
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
EP91402038A
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German (de)
English (en)
French (fr)
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EP0468877A1 (fr
Inventor
Marcel Arnaudeau
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IFP Energies Nouvelles IFPEN
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IFP Energies Nouvelles IFPEN
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    • 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
    • F04D29/18—Rotors
    • F04D29/181—Axial flow rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D3/00—Axial-flow pumps
    • F04D3/02—Axial-flow pumps of screw type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D31/00—Pumping liquids and elastic fluids at the same time

Definitions

  • the present invention relates to a device intended for pumping multiphase fluids which, before pumping and under the pressure and temperature conditions considered, consist of the mixture in particular of a liquid and a gas not dissolved in the liquid, this liquid being able to or not be saturated with gas.
  • a multiphasic fluid for example, but not exclusively, a disphasic petroleum effluent composed of a mixture of oil and gas, poses problems that are all the more difficult to solve since, under the thermodynamic conditions of the biphasic fluid before pumping, the value of the volumetric ratio of gas to liquid is greater.
  • volumetric ratio of gas and liquid
  • GLR volumetric ratio
  • the gas phase is separated from the liquid phase before pumping and each of them is treated separately in separate pumping circuits.
  • the implementation of separate circuits is not always possible and in any case complicates pumping operations.
  • the device according to the invention is designated by the name of compression cell, it can also be called compression pumping cell since it is suitable for liquids as well as liquid gas mixtures or gases. We agree in this document to call it compression cell.
  • the present invention relates to a device which uses in particular blades, blades or special fins for increasing the pumping efficiency of disphasic fluids whose volumetric ratios are higher than those of the prior art.
  • the device according to the present invention makes it possible to treat multiphase fluids whatever the GLR with a compression efficiency which can be greater than 40% or 50% in the most unfavorable operating range.
  • a compression cell generally comprises two parts: an impeller and a diffuser.
  • the impeller is of the two elements, the fundamental element.
  • the impeller is normally mounted on a rotating shaft, keyed or shrunk onto this shaft.
  • the diffuser is static and integral with the body of the machine. The series connection of several of these cells constitutes the hydraulic cell of a pump.
  • the shaft is supported at two or more points by bearings integral with the mechanical pivotings included in the pump body.
  • the pump has suction and discharge.
  • the compression cells can be identical or of different dimensions.
  • the compression cells are defined essentially by their geometries.
  • the present invention relates to a device for compressing a multiphase fluid comprising a liquid phase and a gaseous phase, this device comprising a casing, an impeller having an inlet section and an outlet section, said impeller comprising an axysymmetric hub (having an axial symmetry) of axis Ox and a number n of blades rotating around said axis, these blades having a leading edge and a trailing edge.
  • Said fluid enters said impeller through the inlet section and exits therefrom through the outlet section, said axis being oriented in the direction of progression of said fluid, the number of rotating fins being equal to or greater than 2.
  • the value d can be equal to:
  • the blades may have upper edges which are part of a cylinder of revolution having the axis of symmetry as the axis Ox.
  • the portion of the channel may correspond to the entire length of the channel.
  • the entry angles of the blades are for the intrados angles between 4 ° and 24 ° and preferably between 4 ° and 12 °, and for the extrados angles between 2 ° and 23 ° and preferably between 2 ° and 11 ° .
  • the hollow of the blades defined as: B s M - B e M may be between 0 ° and 30 ° and preferably between 6 ° and 12 °, B s M being the mean angle of exit of the blade and B e M the mean angle of entry of the blade.
  • the average thickness of the blade is between 3 and 5 mm outside the areas near the leading and trailing edges.
  • the number of blades may be between 3 and 8, and preferably between 4 and 6, limits included.
  • the blades may have a lower outlet angle of between 4 ° and 54 ° and preferably between 10 ° and 24 °, and for the upper surface angle 2 ° to 58 ° and preferably 8 ° to 23 °.
  • the average profile or skeleton of said blades defined by the intersection of a blade of zero thickness and a cylindrical surface relative to said axis may be such that the angle formed by this profile with said axis decreases monotonously from the edge leading towards the trailing edge and the curve representing the value of the curvature along the profile of the blade as a function of the curvilinear abscissa at a slope whose value increases from the leading edge towards the trailing edge of the blade.
  • Said curve may have an inflection point.
  • the device according to the invention may include a paddle diffuser.
  • This diffuser may include between 8 and 30 blades and preferably between 15 and 25 blades.
  • the axial length of the impeller relative to its outside diameter may be between 0.10 and 0.40 and preferably between 0.15 and 0.20.
  • the diffuser hub may have a shape of revolution around the axis Ox, and the line considered in an axial plane generating this shape of revolution may have at least one inflection point.
  • This line may have tangents parallel to said axis at the two ends of this line corresponding to the inlet and outlet of the diffuser.
  • the present invention also relates to the use of at least one device described above, in the constitution of a multiphase pump as well as the use of such a multiphase pump to perform pumping operations of multiphase effluent. tanker.
  • fluid will mean either a gaseous or exclusively liquid monophasic fluid in which a gas is completely dissolved, or a multiphasic fluid comprising in particular a liquid phase and a gaseous phase as well as possibly solid particles, for example sand or viscous particles such as hydrate agglomerates.
  • the liquid phase can obviously consist of liquids of different natures, similarly, the gas phase can consist of several gases of different natures.
  • FIG. 1 shows schematically and in axial section a particular, non-limiting embodiment of a pumping assembly using the device according to the invention. This assembly is intended for pumping a multiphase petroleum effluent.
  • FIG. 1 In the example of FIG. 1 between the inlet 2 and outlet 3 orifices of the pumping device and inside the casing 1, is placed at least one compression cell according to the invention.
  • This cell is adapted to increase the total energy of the fluid.
  • three impellers referenced 17 to 19 are visible. This number is not limiting and depends on the increase in pressure which it is desired to obtain.
  • a diffuser or rectifier such as diffusers 24 to 26, is placed at the outlet of each impeller, this diffuser being secured to housing 1, for example, by means of fixing screws 27 (symbolized by dashed lines on the figure).
  • Each pair of impeller and diffuser (17, 24; 19, 26) constitutes with a portion of the housing a compression cell.
  • Reference 14 designates a deflector.
  • FIG. 2 schematically represents, seen in perspective, a nonlimiting example of embodiment of an impeller element or stage essentially comprising a hub 28 integral with the shaft 6 which, during the operation of the device, is driven in rotation in the direction indicated by the arrow r '.
  • Two blades 29 and 30 have been shown in Figure 2, but this number is by no means limiting. In general, a number of blades is chosen to facilitate the static and dynamic balancing of the rotor.
  • the height of the blades is such that the shape which they define during their rotation is complementary to the bore of the casing 1 which, in the example illustrated, is cylindrical.
  • blades can be attached and fixed by welding to the hub 28, but it is preferable to produce the assembly, hub and blades, by molding or milling.
  • the impeller and the rectifier are of the helicoaxial type.
  • the hatched part of Figure 3 corresponds to the axisymmetric hub.
  • Figure 4 defines the blades of the impeller.
  • the number of blades n is preferably always greater than or equal to 2.
  • the number can be between 3 and 8 and preferably between 4 and 6 in particular for impellers whose outside diameter of the blades varies between 100 and 400 mm.
  • the simplest representation to describe the blade is to define its geometric layout on the developed surface of the cylindrical envelope with the outside radius r, r can be between R3 and R2. This surface is represented in the plan (fig. 4).
  • the two right tracks 41, C1C2 and right 42 C'1C'2 are parallel and distant from the called (above) length of the impeller.
  • the blades are integral with the hub. They are geometrically defined as follows.
  • Each blade has two faces, a lower face 31 and an upper face 32, a leading edge or point C1 (or at point C2), a trailing edge at point C'1 (or at point C'2), and a thickness defined as the distance between the lower surface and the upper surface.
  • the lower surface exit angle B s I and the upper surface exit angle B s E are defined in the same way with respect to the points C'1 and C'2 and the trace 42 of the exit face.
  • chord angle B c is the chord angle C1C'1 or C2C'2, straight lines joining the points C les and C'1 on the one hand (or C2 and C'2) and the trace or the exit face. These different angles are defined from a direction parallel to the right 41 or 42.
  • the rope coincides with the profile of the lower surface in the vicinity of the trailing edge.
  • the length of the cord C1C'1 is then equal to the value l / sinB c , l and B c as defined above.
  • n be the number of blades
  • the shape of the actual blade is defined by the traces of the lower surface and the upper surface in this plane of FIG. 4.
  • the curve of the lower surface connecting C1 to C'1 can be defined by a second degree equation as a function of the curvilinear abscissa of the blade counted from C1; this curve is tangent to the trace of the angle B e I or point C1 and to the trace of the angle B s I at the point C'1.
  • the upper surface curve connecting C1 to C'1 can be defined by a fourth degree equation as a function of the curvilinear abscissa of the blade, counted from C1, this curve has a tangent making an angle B e E to neighborhood of C1 and B s E in the neighborhood of C'1.
  • the blade skeleton or average fiber of the blade can be represented by a fourth degree equation.
  • the radii of curvature ⁇ m of the blades are also defined as a function of the curvilinear abscissa. Thus are defined the curvatures 1 / ⁇ m and particularly the curvature of medium fiber.
  • the thickness of the blades is small (practically between three and five millimeters, for certain particular industrial applications the blades can be of greater thickness) in the case where the thickness of the blade is not constant or cannot be considered as such one can use in the formulas which follow either the actual thickness of the blade as a function of the abscissa or use a fixed value for the thickness of the blade, this thickness may be equal to the average thickness of the blade.
  • the blades are generally thinner on the leading edges and on the trailing edges.
  • the hollow of the blades is defined as the difference of the mean angles (or of the mean fiber) of outlet B s M and inlet B e M, more precisely B s E and B s I being defined at the outlet we have B s M ⁇ (B s E + B s I) / 2 1st order
  • the dip defined as the difference B s M - B e M is one of the characteristics of these impellers.
  • the orthoradial distance between the blades is defined as the distance between a point on a lower surface and a point on the upper surface of the previous blade measured in an orthoradial plane perpendicular to the Ox axis ( Figure 4) (ie perpendicular to the plane in Figure 4).
  • Figure 4 orthoradial plane perpendicular to the Ox axis
  • distance 2 ⁇ r / n - e / sinB vs
  • a helicalaxial pump is defined like all pumps or all compressors by its volumetric flow or nominal flow.
  • the input and output sections of the impeller may in particular be determined from the speed triangles by applying inter alia Euler's laws in relation to the desired nominal operating conditions.
  • the orthoradial section defines the hydraulic channel.
  • the section is defined with respect to x current point on Ox, it can also be defined according to the curvilinear abscissa of the chord of the blade profile.
  • n could be considered not as the number of blades but as a parameter linked to the relative input section of each of the channels.
  • the orthoradial section of at least one passage evolves in the manner indicated by the formula giving S (x).
  • the deviations from this formula can be less than 5% or preferably less than 3%, and this between two orthoradial planes of abscissa x1, x2 (cf. Figure 7).
  • the cross section of a channel given by the above formula is respected as well as possible, in particular taking into account manufacturing tolerances.
  • the distance x1, x2 of the axis Ox for which the formula giving the variation of the orthoradial section is verified under the conditions of precision already indicated above, is equal to at least 80% of the length of the impeller and preferably greater 90%.
  • the ratio between the length of the impeller and its outside diameter can be between 10% and 40% and preferably between 15% and 25%.
  • the fluid is driven at a speed having at least one axial component and one circumferential component.
  • a rectifier makes it possible to increase the static pressure by eliminating or at least reducing the circumferential component of the flow speed of the fluid.
  • This rectifier could be of any known type, with characteristics adapted to those of the impeller stage, as indicated below with reference to FIGS. 8 and 9.
  • Figure 8 shows, in section, an assembly comprising an impeller (shown in broken lines) and a rectifier (shown in solid lines).
  • FIG. 9 schematically represents the developed trace of the intersection of a fin of the rectifier with a cylindrical surface of radius r.
  • the rectifier consists of a sleeve 34 which carries at least two fins 35.
  • a ring 36 fixed on the fins 35 allows the rectifier and the casing 1 to be secured, for example by means of screws shown diagrammatically at 27.
  • the outside diameter of the sleeve 34 decreases progressively from the inlet to the outlet over a first portion M'N 'which can represent at least 30% of the total length of the rectifier measured parallel to the axis and which, for its part, is equal to minus 30% of the mean diameter Dm of the blades at the inlet of the rectifier.
  • M'N ' can represent at least 30% of the total length of the rectifier measured parallel to the axis and which, for its part, is equal to minus 30% of the mean diameter Dm of the blades at the inlet of the rectifier.
  • the fins 35 have an appropriate profile which allows the straightening of the flow of the fluid. At the inlet of the rectifier, this profile is substantially tangent to the flow while at the end of the first portion M'N ', the profile of the fins is substantially tangent to a plane passing through the axis of the device, l tilt angle varying gradually over this first portion.
  • the first portion M'N 'of the fins is given a constant radius of curvature.
  • the remaining portion N'P 'of the fin is arranged axially and on this part, the hub is cylindrical.
  • the straight input section of a rectifier S e is chosen to be greater than the output section S s of the impeller stage precede the rectifier so that the ratio S e / S s can have a value between 1 and 1 , 2 and, preferably, between 1.1 and 1.15, while the ratio S s / S e between the straight sections between the outlet and the inlet of the rectifier is greater than 1 and, preferably, between 2 and 3.
  • each fin of the rectifier could be obtained by machining portions of intersecting planes.
  • the sleeve may be formed by a form of revolution obtained by the rotation of a flat line 36 M ', T', N ', P' around the axis Ox of the compression cell, this line comprising at least two parts.
  • a first part M'T ' corresponds to an arc of a circle, the center of which is on the same side as the axis Ox relative to this line.
  • a second part T 'and N' also corresponds to an arc of a circle preferably of the same radius as the first arc M'T 'but whose center is located on the other side of said line relative to the center of the circle of the first arc M'T'.
  • the two arcs of circle M'T 'and T'N' are connected to each other in T 'with preferably tangents parallel to this point where, in this case T' is an inflection point of the curve M'T ' NOT'.
  • the orthogonal projection on the axis Ox of the arc M'T 'could be equal to the corresponding length either of the arc T'N' or of the curve T'P '.
  • the tangents to the line M'T'N'P 'in M' and P ' may be parallel to the axis Ox, possibly comprising a third straight N'P' part parallel to the axis Ox.
  • the line M'T'N'P 'described above was in an axial plane of the compression cell.
  • the length of the impeller and the diffuser may be equal.
  • FIG. 7 two curves are shown, they correspond to the variation of the orthoradial section of a channel of the impeller as a function of the abscissa on the axis Ox.
  • the origin of this axis corresponds to the input face of the impeller, this face comprising the part of the leading edge furthest forward relative to the flow of gases.
  • This part of this curve 37 extends to the abscissa l corresponding to the length of the impeller, the abscissas x1 and x2 define the zone x1, x2 within which the formulation given previously for the variation of the orthoradial section S (x) is respected under the conditions of precision already indicated previously in this text.
  • x1 could be equal to l-x2
  • the length x1 may correspond to the length for which the thickness of the blade has reached 80 or 90% of the average thickness. Generally this length may correspond to 3% of the length of the curvilinear abscissa.
  • x2 can be determined as being the beginning of the zone x2, l where the thickness of the blade deviates by more than 10% or 20% from the average thickness.
  • the tangent 38 to the curve 37 in S e can be horizontal.
  • Curve 43 corresponds to the evolution of the orthoradial section of a diffuser channel multiplied by n r / n i where n R corresponds to the number of blades or fins of the diffuser and n I the number of blades or fins of the impeller .
  • the curve 43 is a continuous curve between the abscissa l and l3 and has no singular point. This curve has an inflection point 44.
  • the abscissa of this inflection point can be substantially equal to (l + l3) / 2.
  • the tangent 45 at the inlet of the diffuser corresponding to the abscissa l to the clearance between impeller and diffuser near is the horizontal (L.a.d. parallel to the axis Ox). It is the same at the exit of the diffsueur the tangent 46 is parallel to the axis Ox.
  • the length l3-l corresponds to the axial length of the diffuser.
  • outlet section S s of the impeller channel will be strictly equal to the inlet section in the diffuser.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Reduction Or Emphasis Of Bandwidth Of Signals (AREA)
EP91402038A 1990-07-27 1991-07-23 Dispositif de pompage ou de compression polyphasique et son utilisation Expired - Lifetime EP0468877B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9009607A FR2665224B1 (fr) 1990-07-27 1990-07-27 Dispositif de pompage ou de compression polyphasique et son utilisation.
FR9009607 1990-07-27

Publications (2)

Publication Number Publication Date
EP0468877A1 EP0468877A1 (fr) 1992-01-29
EP0468877B1 true EP0468877B1 (fr) 1994-05-11

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EP91402038A Expired - Lifetime EP0468877B1 (fr) 1990-07-27 1991-07-23 Dispositif de pompage ou de compression polyphasique et son utilisation

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EP (1) EP0468877B1 (pt)
JP (1) JP3393653B2 (pt)
BR (1) BR9103220A (pt)
CA (1) CA2047975C (pt)
DE (1) DE69101953T2 (pt)
DK (1) DK0468877T3 (pt)
FR (1) FR2665224B1 (pt)
NO (1) NO300469B1 (pt)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2699986B1 (fr) * 1992-12-29 1995-02-24 Inst Francais Du Petrole Dispositif et méthode permettant de transférer dans une seule conduite un effluent de type polyphasique.
FR2724424B1 (fr) 1994-09-14 1996-12-13 Inst Francais Du Petrole Systeme de pompage polyphasique a boucle de regulation
FR2743113B1 (fr) * 1995-12-28 1998-01-23 Inst Francais Du Petrole Dispositif de pompage ou de compression d'un fluide polyphasique a aubage en tandem
FR2748533B1 (fr) * 1996-05-07 1999-07-23 Inst Francais Du Petrole Systeme de pompage polyphasique et centrifuge
FR2748532B1 (fr) * 1996-05-07 1999-07-16 Inst Francais Du Petrole Systeme de pompage polyphasique et centrifuge
FR2774136B1 (fr) 1998-01-28 2000-02-25 Inst Francais Du Petrole Dispositif de compression-pompage monoarbre associe a un separateur
EP1073847B1 (en) 1998-04-24 2003-03-26 Ebara Corporation Mixed flow pump
FR2782755B1 (fr) 1998-09-02 2000-09-29 Inst Francais Du Petrole Turmomachine polyphasique a melange de phases ameliore et methode associee
FR2783884B1 (fr) 1998-09-24 2000-10-27 Inst Francais Du Petrole Systeme de compression-pompage comportant une section de compression en fonctionnement alterne et son procede
FR2787837B1 (fr) * 1998-12-28 2001-02-02 Inst Francais Du Petrole Impulseur diphasique avec canal incurve dans le plan meridien
FR2787836B1 (fr) * 1998-12-28 2001-02-02 Inst Francais Du Petrole Impulseur diphasique helico-radio-axial avec carenage incurve
FR2792678B1 (fr) 1999-04-23 2001-06-15 Inst Francais Du Petrole Procede de recuperation assistee d'hydrocarbures par injection combinee d'une phase aqueuse et de gaz au moins partiellement miscible a l'eau
FR2858668B1 (fr) 2003-08-04 2005-09-23 Inst Francais Du Petrole Utilisation d'une turbine diphasique dans un procede d'hydrotraitement
FR2891609B1 (fr) 2005-10-04 2007-11-23 Inst Francais Du Petrole Procede d'oxy-combustion permettant la capture de la totalite du dioxyde de carbone produit.
CA3133286C (en) * 2014-02-24 2023-11-07 Baker Hughes Esp, Inc. Downhole wet gas compressor processor
EP3312432B1 (en) 2016-10-19 2021-06-23 IFP Energies nouvelles Diffuser for a fluid compression device, comprising at least one vane with opening
CN108005950B (zh) * 2018-01-30 2024-04-09 清华大学 叶片式油气混输泵的叶轮及其设计方法
CN110578706A (zh) * 2019-09-17 2019-12-17 兰州理工大学 一种螺旋轴流式油气混输泵的超分离型叶轮
FR3102685B1 (fr) 2019-11-06 2021-10-29 Ifp Energies Now Procédé d’oligomérisation d’oléfines dans un réacteur d’oligomérisation
FR3117127A1 (fr) 2020-12-07 2022-06-10 IFP Energies Nouvelles Procédé d’hydrotraitement d’un flux liquide comprenant des hydrocarbures avec un flux gazeux comprenant de l’hydrogène
KR102539808B1 (ko) * 2021-07-08 2023-06-07 한국과학기술연구원 친수 톱니 임펠러형 오일 이송 장치
FR3126423A1 (fr) 2021-08-26 2023-03-03 IFP Energies Nouvelles Procédé d’hydroconversion de charges hydrocarbonées
FR3137164B1 (fr) 2022-06-24 2024-07-19 Ifp Energies Now Système et procédé de compression de dioxyde de carbone avec compression polyphasique et pompe supercritique

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1518502A (en) * 1923-07-25 1924-12-09 Gill Propeller Company Ltd Screw propeller or the like
GB1561454A (en) * 1976-12-20 1980-02-20 Inst Francais Du Petrole Devices for pumping a fluid comprising at least a liquid

Also Published As

Publication number Publication date
NO912904D0 (no) 1991-07-25
DE69101953T2 (de) 1994-10-13
JP3393653B2 (ja) 2003-04-07
NO300469B1 (no) 1997-06-02
EP0468877A1 (fr) 1992-01-29
JPH074371A (ja) 1995-01-10
NO912904L (no) 1992-01-28
FR2665224B1 (fr) 1992-11-13
DE69101953D1 (de) 1994-06-16
BR9103220A (pt) 1992-02-18
CA2047975A1 (fr) 1992-01-28
DK0468877T3 (da) 1994-07-11
CA2047975C (fr) 2002-07-09
FR2665224A1 (fr) 1992-01-31

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