EP3938626B1 - Nebenstromrichter mit integriertem rohr - Google Patents

Nebenstromrichter mit integriertem rohr Download PDF

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Publication number
EP3938626B1
EP3938626B1 EP20725890.6A EP20725890A EP3938626B1 EP 3938626 B1 EP3938626 B1 EP 3938626B1 EP 20725890 A EP20725890 A EP 20725890A EP 3938626 B1 EP3938626 B1 EP 3938626B1
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EP
European Patent Office
Prior art keywords
flow
vane
turbomachine
downstream
section
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Active
Application number
EP20725890.6A
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English (en)
French (fr)
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EP3938626A2 (de
Inventor
Florent Matthieu Jacques NOBELEN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3938626A2 publication Critical patent/EP3938626A2/de
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/125—Fluid guiding means, e.g. vanes related to the tip of a stator vane

Definitions

  • the field of the invention relates to multiple-flow turbomachines, and more specifically the flow rectifiers of a separate multiple-flow turbomachine.
  • a multi-flow turbomachine as shown in figure 1 conventionally comprises a fan 1, a fan casing 2 and a casing 3 extending along a longitudinal axis X.
  • the casing 3 houses the compression, combustion and expansion elements of the turbomachine.
  • the fan casing 2 extends radially outside the fan 1 and the casing 3 so as to delimit the flow entering the fan 1.
  • the fan 1 compresses and accelerates the flow of air entering the fan casing 2, this air flow then circulating in a primary circuit 4 and a secondary circuit 5, the primary circuit 4 being located inside the casing 3 and traversing the various compression, combustion and expansion elements, the secondary circuit 5 being delimited radially internally by the casing 3 and externally by the fan casing 2.
  • the rotation of the fan 1 inducing a gyration in the flow which it accelerates it is known to arrange a flow rectifier 6 in the secondary circuit 5, the rectifier 6 comprising a plurality of vanes 7 configured to modify the direction of circulation of the flow in order to obtain an axial flow downstream of the rectifier 6.
  • the profile of the nacelles 2 is conventionally configured to form a nozzle downstream of the rectifiers and to accelerate and relax the secondary flow so as to generate the thrust, the section of the secondary circuit 5 decreasing downstream (in the case of a convergent nozzle), then can possibly increase again in the case of a convergent-divergent nozzle.
  • each flow is ejected through a nozzle.
  • the nozzle (primary and secondary) transforms potential energy into energy kinetic, that is to say, it converts the pressure of the flow into the velocity of ejection, which will generate the thrust.
  • the secondary flow nozzle surrounds and is conventionally placed upstream of the primary flow nozzle.
  • the primary flow nozzle is delimited by a cone whose tip is directed downstream and by an annular casing having a trailing edge directed downstream.
  • the cone and the casing define a circuit of convergent or convergent-divergent section according to the architectural choices made.
  • the secondary nozzle is delimited by a duct belonging to the fan casing (commonly called OFD or OFS abbreviated to “ Outer Fan Duct / Shroud ”) and to the turbomachine casing (commonly called IFD or IFS abbreviated to “ Inner Fan Duct / Shroud ”) .
  • the two casings define a convergent or convergent-divergent section according to the architecture of the rest of the engine.
  • This decrease in section is conventionally located downstream of the rectifier 6, so as to accelerate the secondary flow when it flows axially, the secondary flow then being ejected around the primary flow.
  • the air inlet must be extremely short, and the fan casing 2 must be as short as possible after the exit of the vanes 7 of the stator 6.
  • the document GB-2 546 422 discloses an assembly according to the preamble of claim 1.
  • An object of the invention is to reduce the pressure drops induced by the fan casing.
  • Another object of the invention is to accelerate the secondary flow.
  • Another object is to limit the load losses induced by the rectifier.
  • Another object of the invention is to increase the bypass ratio of the turbomachine.
  • Another object is to reduce the compression ratio of the fan.
  • the invention proposes an assembly for a turbomachine in accordance with claim 1.
  • the invention proposes a turbomachine comprising such an assembly.
  • the turbomachine extends along an axis X of the turbomachine, and the terms axial, radial and tangential refer to the axis X of the turbomachine.
  • An axial direction follows axis X of the turbomachine, a radial direction is perpendicular to axis X of the turbomachine, and a tangential direction is orthogonal to a radial direction and an axial direction.
  • the turbomachine is a dual-flow turbomachine further comprising a fan 1, housed in the fan casing 2, and rotatable about a longitudinal axis X, an inner shroud 31 configured to delimit a primary stream 4 of a primary gas flow from the turbomachine, the shroud 32 and the fan casing 2 delimiting a so-called secondary flow path for an air flow propelled by the fan 1.
  • the shroud 32 is located in the upstream extension of the casing 3 of the turbomachine.
  • the shroud 32 can be part of the casing 3, and thus form the upstream portion of the casing 3.
  • the shroud 32 and the inner shroud 31 may form a single piece and form the leading edge of the casing 3.
  • the inlet section 14a, the ejection section 14b and the outlet section 14c extending respectively from the radially inner limit to the radially outer limit of the blades 7.
  • the inlet section 14a thus corresponds to a radial section of the flow channel 13 which coincides with the leading edge 9 of the second blade 7b, and the ejection section 14b corresponds to a radial section extending downstream of the input section 14a.
  • the ejection section 14b has a surface smaller than a surface of the inlet section 14a and smaller than a surface of the outlet section 14c.
  • the flow channel 13 has a radial section 14 which is defined as a virtual plane extending from the extrados wall 10a of the first blade 7a to the intrados wall 11b of the second blade 7b while being normal to an average direction of the flow at a central streamline F and extending substantially radially relative to the longitudinal axis X.
  • central streamline is meant the streamline located equidistant from the first blade 7a and the second blade 7b.
  • the radial section 14 of the flow channel 13 has a surface which gradually decreases between the inlet section 14a and the ejection section 14b.
  • the radial section 14 has a width L defined as a distance between the upper surface 10a of the first blade 7a and the lower surface 11b of the second blade 7b for a constant distance from the axis X, and in which the width of the radial section 14 is decreasing according to the circulation of the flow in the flow channel 13 between the inlet section 14a and the ejection section 14b.
  • the extrados wall 10a of the first blade 7a and the intrados wall 11b of the second blade 7b are increasingly close to each other, for a given distance from the X axis, as the as the flow travels from upstream to downstream in the flow channel 13.
  • a radial section 14 has a shape comparable to an angular portion of a disc and has a dimension in a transverse direction and a dimension in a radial direction.
  • the radial section 14 is delimited by the first vane 7a and the second vane 7b.
  • the distance separating the first blade 7a and the second blade 7b, the width L, is a function of the distance from the axis X of the turbomachine at which the width L considered. Indeed the distance between the first blade 7a and the second blade 7b increases with the distance to the X axis.
  • the width of a radial section 14 is a function of the radius or of a distance from the axis X of the turbomachine, and increases as a function of the distance from the axis X of the turbomachine.
  • the radial section 14 is delimited radially internally by the outer shroud 32 and extends over the entire height of a blade 7.
  • the radial section 14 has a radially inner limit and a radially outer limit each substantially forming an arc of a circle.
  • the width L decreases, and optionally the dimension in the radial direction also decreases.
  • the decrease in the flow section 14 causes relaxation and therefore an acceleration of the secondary flow.
  • the lower surface 11a of the first blade 7a and the upper surface 10b of the second blade 7b are therefore configured so that the width L of a radial section 14, for a given distance from the axis X of the turbomachine, decreases as the flow moves downstream.
  • the width L of the radial section 14 will be less than the width of the inlet section 14a.
  • This width L can optionally be the length of a straight segment joining at mid-height the first blade 7b and the second blade 7a.
  • the length of the straight segment joining the first vane 7b and the second vane 7a at mid-height gradually decreases between the inlet section 14a and the ejection section 14b.
  • the ejection section 14b has the minimum area for a radial section 14.
  • the width L of a radial section 14 decreases as it moves from upstream to downstream as far as a median plane 15, the median plane 15 therefore including the ejection section 14b.
  • the median plane 15 is normal to the axis X of the turbomachine, and delimits the flow channel 13 into two parts, an upstream or intake portion 16 and a downstream or ejection portion. 17.
  • the transverse dimension of the radial section 14 is less than the transverse dimension of the inlet section 14a and greater than the transverse dimension of the ejection section 14b.
  • the flow channel 13 is convergent, the radial section 14 having a decreasing surface from upstream to downstream.
  • Inlet portion 16 of flow channel 13 is configured to do the work of changing flow direction and flow acceleration.
  • the flow channel 13 therefore has an inlet section 14a defining a plane normal (or orthogonal) to the flow direction of the flow diverted by the fan, this plane therefore not being normal to the axis X of the turbomachine, and an ejection section 14b defining a plane normal to the axis X of the turbomachine. This makes it possible to eject a flow circulating in a direction substantially parallel to the axis of the turbomachine.
  • the intake portion 16 straightens the flow while relaxing it and accelerating it until ejection at the level of the median plane 15.
  • the ejection portion 17 is configured to minimize the aerodynamic drag of the rectifier 6.
  • the angle of incidence of the profile with respect to the flow is low so as to avoid the separation of the air flow, while having the shortest possible length to minimize viscous friction.
  • Part of the ejection portion 17 is located downstream of the trailing edge 8 of the fan casing 2. Thus, this makes it possible to slow down the flow in the ejection portion 17 down to flight speed.
  • the profile of the blades 7 is configured to minimize the drag of each blade 7, the blades 7 therefore extending axially to their trailing edge 12.
  • the section of the flow channel 13 therefore increases downstream in the ejection portion 17.
  • the blades 7 have a line of camber 71 which may comprise a point of inflection, the line of camber or mean line being defined in that it extends from the leading edge 9 to the trailing edge 12 and that it is halfway between the extrados 10 and the intrados 11.
  • the line of camber 71 has an inclination with respect to the axis X of the turbomachine corresponding to the gyration of the flow at the leading edge 9, and is substantially parallel to the motor axis from the median plane 15 to the trailing edge 12.
  • the median plane 15, and therefore the ejection section 14b coincides with the trailing edge 8 of the fan casing.
  • the ejection portion 17 is therefore not streamlined.
  • the length of the fan casing 2 can be reduced to a minimum without penalizing the operation of the intake portion 16 which is streamlined by the fan casing 2, nor the operation of the ejection portion 17 whose sole role is to reduce drag.
  • a portion of the blades 7, in particular the trailing edge 12, is then located downstream of the trailing edge 8 of the fan casing 2, and is therefore not streamlined.
  • the fan casing 2 can extend axially beyond the median plane 15.
  • the trailing edge 8 of the fan casing 2 is located downstream of the median plane 15 and upstream of the trailing edges blades 12, at the level of a fairing plane 18.
  • This configuration makes it possible to form a converging then diverging profile in the streamlined part of the flow channels 13 (that is to say covered by the fan casing 2). This improves performance depending on the flight envelope.
  • each pair of adjacent vanes 7 of the straightener 6 defines a flow channel 13 configured to straighten and accelerate the flow simultaneously, the vanes of the straightener 6 thus defining a plurality of flow channels 13 distributed circumferentially.
  • the pressure losses are reduced by the reduction in the length of the fan casing 2 and the profile of the blades 7, more particularly the trailing edge 12 and the profile of the ejection portion 17 make it possible to reduce the drag and thus to limit separations and pressure drops.
  • Conventional nozzles form a converging channel which accelerates the flow without deflecting it.
  • the profile of the blades 7 ending in a trailing edge makes it possible to avoid flow separation at the outlet of the assembly.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Baugruppe für eine Strömungsmaschine, die sich entlang einer Achse (X) erstreckt und umfasst:
    - einen Mantel (32), der so ausgelegt ist, dass er einen Gebläsepfad (5) eines Gasstroms der Strömungsmaschine begrenzt,
    - ein Gebläsegehäuse (2), das den Mantel (32) radial umgibt und zusammen mit dem Mantel (32) den Gebläsepfad (5) begrenzt, und
    - einen Gleichrichter (6), der eine Vielzahl von Schaufeln (7) umfasst, die so ausgelegt sind, dass sie einen in dem Gebläsepfad (5) zirkulierenden Nebenstrom gleichrichten, wobei die Vielzahl von Schaufeln (7) eine erste Schaufel (7a) und eine an die erste Schaufel (7a) angrenzende zweite Schaufel (7b) umfasst, die zwischen sich einen Strömungskanal (13) begrenzen, der so ausgelegt ist, dass er den Strom gleichrichtet,
    dadurch gekennzeichnet, dass
    der Strömungskanal (13) konvergent und so ausgelegt ist, dass er den Strom mittels eines Eingangsquerschnitts (14a), der in einer nicht zur Achse der Strömungsmaschine senkrechten Ebene umfasst ist, und eines Ausgangsquerschnitts, der in einer zur Achse (X) der Strömungsmaschine senkrechten Ebene (14b) umfasst ist, beschleunigt, wobei die erste Schaufel (7a) und die zweite Schaufel (7b) jeweils einen unverkleideten stromabwärtigen Teil aufweisen, der eine Abströmkante bildet.
  2. Baugruppe für eine Strömungsmaschine nach Anspruch 1, wobei der Strömungskanal (13) von stromaufwärts nach stromabwärts einen Einlassabschnitt (16), der sich von stromaufwärts nach stromabwärts verjüngt, und einen Auslassabschnitt (17) umfasst, der sich von stromaufwärts nach stromabwärts erweitert.
  3. Baugruppe für eine Strömungsmaschine nach einem der Ansprüche 1 oder 2, wobei die erste Schaufel (7a) eine erste Fläche aufweist, die zweite Schaufel (7b) eine der ersten Fläche zugewandte zweite Fläche aufweist, die erste Fläche sich von stromaufwärts nach stromabwärts der zweiten Fläche annähert.
  4. Baugruppe für eine Strömungsmaschine nach Anspruch 1 bis 3, wobei sich das Gebläsegehäuse (2) um eine Längsachse (X) erstreckt und ein stromabwärtiges Ende umfasst, das eine Abströmkante (8) bildet, und wobei sich der Auslassabschnitt (17) stromabwärts der Abströmkante (8) des Gebläsegehäuses (2) erstreckt.
  5. Baugruppe für eine Strömungsmaschine nach einem der Ansprüche 1 bis 4, wobei eine Wölbungslinie jeder Schaufel (7) einen Wendepunkt aufweist.
  6. Baugruppe nach einem der Ansprüche 1 bis 5, wobei jede Schaufel (7) eine Anströmkante (9), eine der Anströmkante (9) gegenüberliegende Abströmkante (12), und innere (11) und äußere Bogenwände (10) umfasst, die die Anströmkante (9) mit der Abströmkante (12) verbinden, und der Strömungskanal (13) von stromaufwärts nach stromabwärts in der Strömungsrichtung der Fluide aufweist
    - einen Eingangsquerschnitt (14a), der sich von der ersten Schaufel (7a) zur zweiten Schaufel (7b) erstreckt, wobei er zu einer mittleren Richtung der Strömung normal und zur Anströmkante (9) einer der Schaufeln (7) tangential verläuft und eine erste Querschnittsfläche aufweist,
    - einen Auslassquerschnitt (14b), der sich von der ersten Schaufel (7a) zur zweiten Schaufel (7b) erstreckt, wobei er zu einer mittleren Richtung der Strömung normal verläuft und eine zweite Querschnittsfläche aufweist, und
    - einen Ausgangsquerschnitt (14c), der sich von der ersten Schaufel (7a) zur zweiten Schaufel (7b) erstreckt, wobei er zu einer mittleren Richtung der Strömung normal und zur Abströmkante (12) mindestens einer der Schaufeln (7) tangential verläuft und eine dritte Querschnittsfläche aufweist, und wobei die erste Querschnittsfläche größer ist als die zweite Querschnittsfläche, wobei die zweite Querschnittsfläche kleiner ist als die dritte Querschnittsfläche.
  7. Baugruppe nach einem der Ansprüche 1 bis 6, wobei der Strömungskanal (13) einen Eingangsquerschnitt (14a), der eine zur Strömungsrichtung des vom Gebläse abgelenkten Stroms normale, zur Achse (X) der Strömungsmaschine nicht parallele Ebene definiert, und einen Auslassquerschnitt (14b) aufweist, der eine zur Achse (X) der Strömungsmaschine normale Ebene definiert.
  8. Baugruppe nach einem der Ansprüche 1 bis 7, wobei sich das Gebläsegehäuse (2) axial über die Mittelebene (15) hinaus fortsetzt, wobei die Abströmkante (8) des Gebläsegehäuses (2) stromabwärts der Mittelebene (15) und stromaufwärts der Abströmkanten (12) der Schaufeln, im Bereich einer Wölbungsebene (18) liegt.
  9. Strömungsmaschine, die eine Baugruppe für eine Strömungsmaschine nach einem der Ansprüche 1 bis 8 umfasst.
EP20725890.6A 2019-03-15 2020-03-12 Nebenstromrichter mit integriertem rohr Active EP3938626B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1902662A FR3093756B1 (fr) 2019-03-15 2019-03-15 redresseur de flux secondaire a Tuyère intégréE
PCT/FR2020/050524 WO2020188197A2 (fr) 2019-03-15 2020-03-12 Redresseur de flux secondaire a tuyere integree

Publications (2)

Publication Number Publication Date
EP3938626A2 EP3938626A2 (de) 2022-01-19
EP3938626B1 true EP3938626B1 (de) 2022-11-16

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EP20725890.6A Active EP3938626B1 (de) 2019-03-15 2020-03-12 Nebenstromrichter mit integriertem rohr

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US (1) US11434773B2 (de)
EP (1) EP3938626B1 (de)
CN (1) CN114286886B (de)
CA (1) CA3130189A1 (de)
FR (1) FR3093756B1 (de)
WO (1) WO2020188197A2 (de)

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US6502383B1 (en) * 2000-08-31 2003-01-07 General Electric Company Stub airfoil exhaust nozzle
JP4590227B2 (ja) * 2004-08-04 2010-12-01 株式会社日立製作所 軸流ポンプ及び斜流ポンプ
US7730715B2 (en) * 2006-05-15 2010-06-08 United Technologies Corporation Fan frame
US8016561B2 (en) * 2006-07-11 2011-09-13 General Electric Company Gas turbine engine fan assembly and method for assembling to same
US20080159856A1 (en) * 2006-12-29 2008-07-03 Thomas Ory Moniz Guide vane and method of fabricating the same
US9957918B2 (en) * 2007-08-28 2018-05-01 United Technologies Corporation Gas turbine engine front architecture
FR2961565B1 (fr) * 2010-06-18 2012-09-07 Snecma Couplage aerodynamique entre deux rangees annulaires d'aubes fixes dans une turbomachine
FR3032495B1 (fr) * 2015-02-09 2017-01-13 Snecma Ensemble de redressement a performances aerodynamiques optimisees
FR3032480B1 (fr) * 2015-02-09 2018-07-27 Safran Aircraft Engines Ensemble de redressement d'air a performances aerodynamiques ameliorees
FR3046811B1 (fr) * 2016-01-15 2018-02-16 Snecma Aube directrice de sortie pour turbomachine d'aeronef, presentant une fonction amelioree de refroidissement de lubrifiant
US10570917B2 (en) * 2016-08-01 2020-02-25 United Technologies Corporation Fan blade with composite cover
US10815824B2 (en) * 2017-04-04 2020-10-27 General Electric Method and system for rotor overspeed protection
GB2568109B (en) * 2017-11-07 2021-06-09 Gkn Aerospace Sweden Ab Splitter vane

Also Published As

Publication number Publication date
FR3093756A1 (fr) 2020-09-18
CN114286886B (zh) 2024-05-10
WO2020188197A2 (fr) 2020-09-24
WO2020188197A3 (fr) 2020-11-26
CN114286886A (zh) 2022-04-05
FR3093756B1 (fr) 2021-02-19
US20220186624A1 (en) 2022-06-16
CA3130189A1 (fr) 2020-09-24
US11434773B2 (en) 2022-09-06
EP3938626A2 (de) 2022-01-19

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