EP2859239B1 - Carter de compresseur a cavités au calage optimisé - Google Patents

Carter de compresseur a cavités au calage optimisé Download PDF

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Publication number
EP2859239B1
EP2859239B1 EP13742668.0A EP13742668A EP2859239B1 EP 2859239 B1 EP2859239 B1 EP 2859239B1 EP 13742668 A EP13742668 A EP 13742668A EP 2859239 B1 EP2859239 B1 EP 2859239B1
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EP
European Patent Office
Prior art keywords
cavities
casing
downstream
upstream
blade
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.)
Active
Application number
EP13742668.0A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2859239A2 (fr
Inventor
Thierry Jean-Jacques Obrecht
Céline GHILARDI
Vincent Perrot
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP2859239A2 publication Critical patent/EP2859239A2/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • 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
    • F04D19/00—Axial-flow 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—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
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage

Definitions

  • the field of the present invention is that of propulsion and more particularly that of axial or axial-centrifugal compressors for propulsion assembly (turbojet or turboprop, referred to as turbomachines in the following description) and more specifically to high-pressure compressors heavily loaded.
  • the aeronautical turbomachines are mainly constituted by one or more compressors, in which the air sucked into the air intake is compressed, by a combustion chamber in which the injected fuel is burned, then by a turbine in which the burnt gases are relaxed to drive the compressor or compressors and finally by an ejection device.
  • Aeronautical compressors consist of blades, or blades, which are rotated inside a housing that seals the air stream with the outside of the engine. It is known that the clearance between the ends of the compressor blades and the casing forming the inner wall of the air flow line degrades the efficiency of the engine of the turbomachine.
  • this game can significantly modify and degrade the operation of the compressor until the occurrence of a phenomenon of "pumping", which results from the stalling of the airflow from the surface of the blades.
  • the control of the air circulation at the end of the blades is thus a major challenge to obtain both a good aerodynamic efficiency of the compressor and a sufficient margin against the pumping phenomenon.
  • the present invention therefore aims to provide a compressor housing with cavities, aerodynamic performance further improved.
  • the subject of the invention is a compressor for a turbomachine comprising a casing, at least one compressor stage consisting of a fixed blade wheel and a blade wheel positioned downstream of said wheel.
  • fixed vanes, and recessed cavities non-communicating with each other, in the thickness of said casing from its internal face and arranged parallel to each other on a circumference of said casing opposite the path of passage of the blades, said cavities having an elongated shape in a main direction of orientation and closing respectively upstream and downstream by an upstream face and a downstream face whose intersections with the housing respectively form an upstream boundary and a downstream boundary, said cavities being offset relative to the blades to overflow upstream of the blade wheel by covering their upstream end, characterized in that the front The downstream of these cavities is oriented parallel to the rope at the head of the moving blade.
  • the orientation direction of said cavities is perpendicular to that of the rope of the blades.
  • the substantially parallelepipedal shape of the cavity makes it possible to make full use of the thrust effect indicated above.
  • the cavities are evenly distributed around the circumference of the casing.
  • the cavities are distributed unevenly over the circumference of the housing.
  • the invention also relates to a turbomachine comprising a compressor as described above.
  • a compressor stage comprising a stator vane, or fixed blade 2, positioned upstream of a rotor blade, or mobile blade 1, attached to a disk 3 (or directly integral with this disk according to a technology called monoblock blisk).
  • the vanes are held in place by attachment to a compressor casing 4, which surrounds the blades 1 leaving a predefined clearance with them.
  • the casing 4 is dug, from its internal face, multiple cavities 5, not communicating with each other, which are regularly arranged on its circumference, vis-à-vis the path of passage of the blades 1.
  • These cavities have, roughly, the shape of a rectangular parallelepiped which sinks radially into the housing and which has in section along an axial plane, the shape of a rectangle with rounded corners.
  • Their shape, in section in a plane tangential to the circumference of the housing is, in turn, substantially that of an elongated rectangle extending along two long sides and comprising, upstream and downstream, two small sides forming so-called upstream 7 and downstream borders 6. These two boundaries are classically straight line segments.
  • the cavities are offset upstream of the motor, with respect to the leading edge of the moving blade 1.
  • the length of which the upstream 7 of the cavity exceeds with respect to the leading edge 11 of the blades, is however, limited by the space between the blade wheel 1 and the blade wheel 2. With these cavities, the parasitic air is sucked to a certain percentage of the rope of the dawn and reinjected into the vein upstream of dawn.
  • This configuration allows the recycling of air passing in the game between the blade 1 and the casing 4; this game can indeed be the place of violent turbulence which would disturb the configuration of the flow between the different stages and therefore which could lead to a deterioration of the performances of the compressor or, in the extreme, cause a phenomenon called "pumping" or of "stall".
  • a phenomenon is characterized by an instantaneous drop in the compression ratio and a transient inversion of the air flow through the compressor, which then leaves the upstream of the compressor.
  • FIG. 2 and 3 the circumferential position of a series of cavities 5 aligned along the casing 4 is seen.
  • the number of cavities is much greater than the number of vanes 1 constituting the mobile wheel of the compressor stage. This number is in practice between 2 and 4 times the number of moving blades 1.
  • the circumferential distribution of the cavities as shown in the figures is a uniform arrangement; it has, moreover, already been proposed to make this provision irregular to break the aerodynamic excitation on the blades that could be caused by these cavities, especially at the ends of each of the two half-shells that constitute the housing.
  • the axis of these cavities is slightly inclined relative to the longitudinal direction of the motor, defined as being the axis of rotation of the moving wheel 1 and illustrated by an arrow in the figure.
  • the cavities 5 are positioned with the main orientation of their long sides which is significantly more tangential than on the figure 2 , and which is characterized by a wedge angle perpendicular to the rope of the blades 1.
  • the rope of a blade is defined as being the line joining its leading edge to its trailing edge.
  • the cavity has, in the example shown, a substantially parallelepiped shape, the downstream boundary 6 of the cavity 5 is aligned with this rope of the blades.
  • the Figures 5 and 6 show in perspective, and recessed, the relative position of the cavities 5 with respect to a blade wheel 1, respectively in the prior art and according to the invention.
  • the invention is characterized by an orientation of the main direction of the cavity 5 which is perpendicular to that of the rope of the blades 1 to take into account the case where the cavity 5 would have not the shape of a rectangular parallelepiped with rounded shapes, as shown in the figures, the main characteristic of the invention is defined primarily as a parallelism between the downstream border 6 of the cavity 5 and the rope of the blade 1.
  • the downstream border of a cavity when it is not rectilinear, is defined, as for it, as the line segment connecting the extreme downstream points of the long sides forming the intersection of the cavity with the inner wall of the casing 4 .
  • the first concerns the axial position of the downstream cavity, which defines the location air suction, the second, the axial position of the upstream cavity that defines the place of reinjection of air and the third, the volume of the cavity that determines the amount of air removed and reinjected, thus the efficiency of the crankcase treatment.
  • the invention first sought to reduce the axial extension of the cavities and for this analyzed the influence of the wedging thereof on the performance of the compressor.
  • the reduction of the axial trace of the cavity by a The increase in wedging brings the recess of the cavity and the reinjection point closer together with the leading edge 11 at the same time, but it is done here while preserving the volume of the cavity, which makes it possible to maintain the efficiency associated with crankcase treatment by cavity implantation.
  • the invention then focused on determining the optimum angle of inclination for the wedging of the cavities. Indeed, an excessive angle tends to bring too close the place of the levy of the leading edge of the dawn, so to perform at a place where the pressure difference between intrados and extrados is not yet large This would not prevent the game whirlpool from developing a little further downstream. Similarly, the reinjection of the air would be too close to the leading edge, and the mixture between the main upstream air and the air reinjected (tangentially) would not yet be established at the leading edge of the dawn, which would be detrimental from the point of view of the stability of the flow. Finally, a too inclined cavity would lead to an air reinjection angle too large, that is to say at an axial speed of the reinjected air too low, affecting its effectiveness.
  • EP-2025945-A2 , EP-1134427-A1 , EP2151582-A2 , US-4086022-A and DE-3147713-A1 thus describe cavities whose calibration angle is not optimum.
  • the optimum angle of wedging of the cavity is that which makes it possible to have the downstream boundary 6 of the cavity 5 aligned with the wedging of the moving blade 1.
  • the explanation of this optimum can be given by the fact that, during the passage of the dawn above the cavity, the blade "pushes" the flow of air into the cavity.
  • the fact of having a downstream border aligned with the setting of the blade makes it possible to have this thrusting effect which happens at the same time over the entire downstream zone of the cavity. This causes a more effective thrust at the optimum moment, when the dawn passes at the level of the downstream of the cavity, and this thrust effect causes the decrease of the game whirlpool associated with the passage of the blade.
  • the invention results, on the one hand, by an optimization of the axial position of the beginning and the end of the cavity relative to the leading edge of the blade, associated with the maintenance of a sufficient volume of the cavity to ensure the effectiveness of the crankcase treatment, and, secondly, by reducing the axial size of the cavities, which has the effect of limiting the thickness of the crankcase necessary for the integration of those -this.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13742668.0A 2012-04-19 2013-04-15 Carter de compresseur a cavités au calage optimisé Active EP2859239B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1201159A FR2989744B1 (fr) 2012-04-19 2012-04-19 Carter de compresseur a cavites au calage optimise
PCT/FR2013/050828 WO2013156725A2 (fr) 2012-04-19 2013-04-15 Carter de compresseur a cavités au calage optimisé

Publications (2)

Publication Number Publication Date
EP2859239A2 EP2859239A2 (fr) 2015-04-15
EP2859239B1 true EP2859239B1 (fr) 2016-11-16

Family

ID=48906433

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13742668.0A Active EP2859239B1 (fr) 2012-04-19 2013-04-15 Carter de compresseur a cavités au calage optimisé

Country Status (9)

Country Link
US (1) US10024336B2 (pt)
EP (1) EP2859239B1 (pt)
JP (1) JP6618799B2 (pt)
CN (1) CN104220759B (pt)
BR (1) BR112014025631B1 (pt)
CA (1) CA2868226C (pt)
FR (1) FR2989744B1 (pt)
RU (1) RU2616695C2 (pt)
WO (1) WO2013156725A2 (pt)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2971547B1 (en) * 2013-03-12 2020-01-01 United Technologies Corporation Cantilever stator with vortex initiation feature
JP6624846B2 (ja) * 2015-08-19 2019-12-25 株式会社荏原製作所 ターボ機械
US9589652B1 (en) 2015-09-24 2017-03-07 Cypress Semiconductor Corporation Asymmetric pass field-effect transistor for non-volatile memory
CN105840551B (zh) * 2016-04-15 2018-06-12 上海交通大学 多工况点高负荷压气机叶片的气动实现方法
FR3122450B1 (fr) 2021-04-28 2023-05-12 Safran Ensemble de turbomachine comprenant un carter et un support de traitement aerodynamique en tete d’aubes et turbomachine correspondante
US11965528B1 (en) 2023-08-16 2024-04-23 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with circumferential movable closure for a fan of a gas turbine engine
US11970985B1 (en) 2023-08-16 2024-04-30 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine
US12018621B1 (en) 2023-08-16 2024-06-25 Rolls-Royce North American Technologies Inc. Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1518293A (en) * 1975-09-25 1978-07-19 Rolls Royce Axial flow compressors particularly for gas turbine engines
JPS6318799Y2 (pt) 1980-12-02 1988-05-26
GB2245312B (en) * 1984-06-19 1992-03-25 Rolls Royce Plc Axial flow compressor surge margin improvement
US4781530A (en) * 1986-07-28 1988-11-01 Cummins Engine Company, Inc. Compressor range improvement means
US5059093A (en) * 1990-06-07 1991-10-22 United Technologies Corporation Compressor bleed port
RU2109174C1 (ru) * 1996-01-05 1998-04-20 Акционерное общество "Авиадвигатель" Устройство для регулирования перепуска воздуха из компрессора газотурбинного двигателя самолета
DE69909120T2 (de) * 1998-11-13 2003-12-24 Pratt & Whitney Canada Gehäusekonfiguration für einen verdichter
US6290458B1 (en) * 1999-09-20 2001-09-18 Hitachi, Ltd. Turbo machines
DE60014025T2 (de) * 2000-03-17 2006-02-16 Hitachi, Ltd. Turbomaschinen
RU2215908C2 (ru) * 2001-12-06 2003-11-10 Открытое акционерное общество "Авиадвигатель" Устройство для регулирования перепуска воздуха из компрессора газотурбинного двигателя самолета
CN100395432C (zh) * 2002-02-28 2008-06-18 Mtu飞机发动机有限公司 用于涡轮压缩机的循环结构
GB2418956B (en) * 2003-11-25 2006-07-05 Rolls Royce Plc A compressor having casing treatment slots
DE102007037924A1 (de) 2007-08-10 2009-02-12 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Ringkanalwandausnehmung
DE102008037154A1 (de) 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine
FR2940374B1 (fr) 2008-12-23 2015-02-20 Snecma Carter de compresseur a cavites optimisees.

Also Published As

Publication number Publication date
US10024336B2 (en) 2018-07-17
JP6618799B2 (ja) 2019-12-11
CA2868226C (fr) 2020-01-14
WO2013156725A3 (fr) 2014-01-09
US20150078890A1 (en) 2015-03-19
JP2015514906A (ja) 2015-05-21
FR2989744B1 (fr) 2014-06-13
FR2989744A1 (fr) 2013-10-25
CN104220759B (zh) 2016-08-24
CA2868226A1 (fr) 2013-10-24
EP2859239A2 (fr) 2015-04-15
BR112014025631B1 (pt) 2021-06-01
RU2616695C2 (ru) 2017-04-18
RU2014141506A (ru) 2016-06-10
CN104220759A (zh) 2014-12-17
WO2013156725A2 (fr) 2013-10-24

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