EP2859240A2 - Verdichtergehäuse mit hohlräumen mit einer optimierten aufwärtsströmungsform - Google Patents

Verdichtergehäuse mit hohlräumen mit einer optimierten aufwärtsströmungsform

Info

Publication number
EP2859240A2
EP2859240A2 EP13742669.8A EP13742669A EP2859240A2 EP 2859240 A2 EP2859240 A2 EP 2859240A2 EP 13742669 A EP13742669 A EP 13742669A EP 2859240 A2 EP2859240 A2 EP 2859240A2
Authority
EP
European Patent Office
Prior art keywords
cavities
upstream
compressor
downstream
housing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13742669.8A
Other languages
English (en)
French (fr)
Other versions
EP2859240B1 (de
Inventor
Thierry Jean-Jacques Obrecht
Olivier Stéphane DOMERCQ
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
Original Assignee
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2859240A2 publication Critical patent/EP2859240A2/de
Application granted granted Critical
Publication of EP2859240B1 publication Critical patent/EP2859240B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • 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
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal 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
    • 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
    • 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
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids

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 improvement brought by this realization comes only from an optimization of the axial position of the cavities and the search for optimization on other parameters of these cavities must be pursued to try to further improve the aerodynamic efficiency and / or the pumping margin of existing compressors.
  • the present invention therefore aims to provide a compressor housing with cavities, aerodynamic performance further improved.
  • the subject of the invention is a casing for a turbomachine compressor comprising recessed cavities, non-communicating with one another, in the thickness of said casing from its internal face and arranged parallel to each other on a circumference said housing, said cavities having an elongate shape in a main direction of orientation between two side walls and closing respectively upstream and downstream by an upstream face and a downstream face whose intersections with the inner face of the carter respectively form an upstream boundary and a downstream boundary, characterized in that the upstream boundary of these cavities has the form of a corrugated line having at least two alternations along its length between said side walls.
  • corrugated line promotes the mixing of the re-injected air with the main air and thus improves the efficiency and / or the pumping margin of the stage of the compressor using said casing.
  • said side walls converge towards each other while moving from downstream to upstream.
  • This configuration makes it possible to accelerate the air flowing between the dawn and the casing and to improve its reinjection into the vein, which again results in an improvement in the yield and / or the pumping margin of the floor concerned.
  • the wavy line is a broken line in zigzag, consisting of segments forming between them alternately projecting angles and re-entrant angles.
  • the upstream face of said cavities is constituted by a succession of teeth extending, radially, between the upstream boundary and the bottom of the cavity and, axially, alternately upstream and downstream of said cavity.
  • the downstream face has a convex shape. This facilitates the suction of air downstream of the cavity.
  • the cavities are evenly distributed around the circumference of the casing.
  • the cavities are unequally distributed around the circumference of the housing.
  • the invention also relates to a compressor for a turbomachine comprising a housing as described above and a turbomachine comprising such a compressor.
  • Figure 1 is a schematic sectional view of a compressor stage whose housing has a recirculating cavity of the air flowing between the blade and the housing;
  • Figure 2 is a schematic view, from above, of a rotor blade and a housing according to the prior art;
  • Figure 3 is a schematic view, from above, of a rotor blade and a housing according to one embodiment of the invention
  • FIG. 4 is a schematic view of the cutting of a cavity in a housing according to the invention.
  • Figure 5 is a perspective view of the cavities cut in a housing according to the invention.
  • FIG. 1 there is shown a compressor stage comprising a stator vane, or fixed vane 2, positioned upstream of a rotor vane, or mobile vane 1, attached to a disk 3 (or directly attached to this disk according to a so-called blisk technology monobloc).
  • 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 hollowed out, from its internal face, of multiple cavities 5, not communicating with one another, which are regularly arranged on its circumference, opposite 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 casing 4 is, in turn, substantially that of an elongated rectangle extending along two long sides and comprising, upstream and downstream, two short sides forming so-called upstream 7 and downstream borders 6. It should be noted that in the prior art, these two boundaries are classically straight line segments.
  • the cavities 5 are offset upstream of the motor, with respect to the leading edge 11 of the moving blade 1.
  • the length from which the upstream 7 of the cavity 5 protrudes with respect to the leading edge of the blades, is however, limited by the space between the blade wheel 1 and the blade wheel 2. Because of the implantation of these cavities, the parasitic air is sucked to a certain percentage of the rope of the dawn moving 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 degradation of the performances of the compressor or, at the extreme, to 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 we see the circumferential position of a series of cavities 5 aligned along the casing 4, respectively according to the prior art and according to the invention.
  • the number of cavities is much greater than the number of blades 1 constituting the mobile wheel of the compressor stage. This number is in practice between 2 and 4 times the number of 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, particularly at the ends of each of the two half-shells that constitute the housing.
  • the cut formed by the cavities 5 at their intersection with the inner face of the casing 4 has a substantially rectangular shape with the two large sides substantially parallel.
  • the cavities are cut in a trapezoidal shape, with two small sides upstream and downstream that are substantially parallel and two long sides that are convergent upstream, so that the downstream boundary 6 has a greater length than that of the upstream boundary 7.
  • FIG. 4 shows in detail the shape of the cutout of a cavity 5 in a casing 4, according to the invention, at the inner face of the casing 4. While the small downstream side, that is to say the frontier downstream 6, is, as in the prior art, rectilinear, the short upstream side, that is to say the upstream border 7, is not but it has a herringbone shape that develop from side and other of the circumferential line connecting the upstream boundaries of the different cavities 5.
  • FIG. 5 shows in perspective and in recess, the shape of the cavities 5 and their relative position with respect to a wheel of moving blades 1, in the case of a casing 4 according to the invention.
  • the front face of the parallelepiped forming the cavity 5 is corrugated in a herringbone shape which extends all along the front face of the cavity, starting in the bottom of the cavity and ending with a zigzag line at the bottom. of the internal face of the casing 4 and the upstream frontier 7.
  • 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
  • the third the volume of the cavity that determines the amount of air removed and reinjected, thus the efficiency of the crankcase treatment.
  • it should also take into account a point that directly influences the efficiency of the crankcase treatment and which concerns the quality of the reinjection of the air upstream of the moving wheel.
  • the reinjection speed must be as high as possible to obtain the most improvement in the pumping margin, and, on the other hand, the air reintroduced into the vein must mix best possible with the main flow, otherwise there is a risk of generating yield losses.
  • the invention proposes, firstly, to have cavities 5 whose width is variable and which tapers laterally from downstream to upstream. Keeping a large width in the cavity downstream is important to suck air recirculation in good conditions and avoid the appearance of a whirlpool play; and the decrease of the upstream cavity makes it possible to increase the speed of the air which will be reinjected into the vein. Then the arrangement of rafters allows to improve the mixture of air reinjected with the main air, in the same way that rafters on the nozzle of a turbomachine allow

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13742669.8A 2012-04-19 2013-04-15 Verdichtergehäuse mit hohlräumen mit einer optimierten aufwärtsströmungsform Active EP2859240B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1201160A FR2989742B1 (fr) 2012-04-19 2012-04-19 Carter de compresseur a cavites a forme amont optimisee
PCT/FR2013/050829 WO2013156726A2 (fr) 2012-04-19 2013-04-15 Carter de compresseur á cavités a forme amont optimisée

Publications (2)

Publication Number Publication Date
EP2859240A2 true EP2859240A2 (de) 2015-04-15
EP2859240B1 EP2859240B1 (de) 2016-11-09

Family

ID=48906434

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13742669.8A Active EP2859240B1 (de) 2012-04-19 2013-04-15 Verdichtergehäuse mit hohlräumen mit einer optimierten aufwärtsströmungsform

Country Status (8)

Country Link
US (1) US9638213B2 (de)
EP (1) EP2859240B1 (de)
CN (1) CN104220758B (de)
BR (1) BR112014025385B1 (de)
CA (1) CA2868456C (de)
FR (1) FR2989742B1 (de)
RU (1) RU2626874C2 (de)
WO (1) WO2013156726A2 (de)

Families Citing this family (7)

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Publication number Priority date Publication date Assignee Title
CN110094364B (zh) * 2018-01-31 2020-05-22 中国航发商用航空发动机有限责任公司 一种转子叶片及轴流压气机
RU2694454C1 (ru) * 2018-11-13 2019-07-15 Федеральное государственное казенное военное образовательное учреждение высшего образования "Военный учебно-научный центр Военно-воздушных сил "Военно-воздушная академия имени профессора Н.Е. Жуковского и Ю.А. Гагарина" (г. Воронеж) Министерства обороны Российской Федерации Осевой компрессор
US10914318B2 (en) 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion
FR3140406A1 (fr) 2022-10-04 2024-04-05 Safran Traitement de carter non axisymétrique à ouverture pilotée
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
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

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Also Published As

Publication number Publication date
US20150078889A1 (en) 2015-03-19
US9638213B2 (en) 2017-05-02
RU2014141066A (ru) 2016-06-10
RU2626874C2 (ru) 2017-08-02
FR2989742B1 (fr) 2014-05-09
CN104220758B (zh) 2016-04-13
BR112014025385A2 (pt) 2018-04-10
CA2868456A1 (fr) 2013-10-24
CN104220758A (zh) 2014-12-17
WO2013156726A3 (fr) 2014-01-09
WO2013156726A2 (fr) 2013-10-24
FR2989742A1 (fr) 2013-10-25
BR112014025385B1 (pt) 2022-02-01
CA2868456C (fr) 2020-01-14
EP2859240B1 (de) 2016-11-09

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