EP2368045B1 - Carter de compresseur à cavités optimisées - Google Patents

Carter de compresseur à cavités optimisées Download PDF

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Publication number
EP2368045B1
EP2368045B1 EP09795410.1A EP09795410A EP2368045B1 EP 2368045 B1 EP2368045 B1 EP 2368045B1 EP 09795410 A EP09795410 A EP 09795410A EP 2368045 B1 EP2368045 B1 EP 2368045B1
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EP
European Patent Office
Prior art keywords
cavities
casing
compressor according
cavity
compressor
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
EP09795410.1A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2368045A1 (fr
Inventor
Xavier Jean Agneray
Jérôme Jean BERT
Alexandre Franck Chartoire
Armel Touyeras
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 date
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Publication of EP2368045A1 publication Critical patent/EP2368045A1/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
    • 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
    • F04D29/66—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
    • 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
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

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 document US 5762470 discloses a housing with an annular cavity, placed in communication with the vein through a succession of cuts, specifying the optimal geometry for the cavity and for the cuts; it does not specify what is the relative position for cavities vis-à-vis dawn. It also describes an annular cavity 3, set back from the vein and closed by a grooved grid 3B, the object of which is to allow loss dissipation in the circumferential direction.
  • This configuration has the disadvantage of a risk of parasite reinjection at the blade, via a groove 5 adjacent to the groove in question, which penalizes performance.
  • the present invention aims to overcome these disadvantages by providing a compressor housing with cavities, improved aerodynamic performance.
  • the subject of the invention is a compressor for a turbomachine comprising a housing, at least one compressor stage consisting of a fixed blade wheel and a blade wheel positioned downstream of said wheel.
  • This configuration ensures both a good suction of the air into the cavity and feedback as far upstream as possible from the set of blades. Moreover, the cavities do not communicate between them eliminates any circumferential recirculation, and therefore the risk of a parasitic reinjection at the blade which would come from the adjacent cavity, which would penalize the performance of the compressor. Reinjection is done exclusively as far upstream as possible from the blade set.
  • the upstream end of the cavities makes, in the plane of symmetry of the cavity, an angle ⁇ for the reinjection of the air, equal to 90 plus or minus 5 ° with the portion of the casing situated upstream of said cavity . This avoids recirculation internal to the cavity that would be unfavorable to the efficiency of the compressor.
  • the invention also relates to a turbomachine comprising a compressor having at least one of the characteristics described above.
  • a compressor stage comprising a stator blade, 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 blades have at the casing 4 a length of rope C ax. , measured axially between the outermost point of the leading edge and the outermost point of the trailing edge.
  • the housing 4 is hollowed out with multiple cavities 5 regularly arranged on its circumference, opposite the path of passage of the blades 1. These cavities have, roughly, in section, the shape of a rectangle with rounded corners, extending over a length L2. This cavity 5 is offset upstream of the motor, with respect to the leading edge of the moving blade 1.
  • the length of the cover of the blade 1 by the cavity 5 has a value L1, less than L2.
  • a series of cavities 5 are aligned along the circumference of the casing 4.
  • the axis of these cavities is slightly inclined with respect to the longitudinal direction of the motor.
  • 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 moving blades 1.
  • the distribution of the cavities, as shown in FIG. figure 2 is a uniform arrangement; in a version not shown it can be made irregular to break the aerodynamic excitation on the blades that could be caused by these cavities, including the ends of each of the two half-shells that constitute the housing.
  • the cavity 5 has two parallel sides connecting at their outer end by a half-circumference. It sinks into the casing 4 in an inclined direction, in the direction of rotation of the blades, relative to a perpendicular to the tangent plane to the vein.
  • a maximum inclination is sought but it is limited for reasons of manufacture of the housing; in practice the angle of inclination ⁇ with respect to the tangent plane to the vein is between 45 ° and 60 °.
  • the depth of the cavity 5 is defined by the desired aerodynamic characteristics, again taking into account the manufacturing constraints.
  • the cavity 5 is roughly the shape of a rectangle whose short side, upstream, intersects the housing at an angle ⁇ , measured from the crankcase curve resulting from its cutting by the plane of symmetry of the cavity and which is upstream of the cavity; this angle ⁇ is close to 90 °.
  • the downstream portion of the cavity has a substantially circular shape.
  • the figure 5 shows the case of a casing 4 with a local withdrawal of vein 6 at the blades 1 commonly called “trench". As shown, this shrinkage decreases as it moves downstream of the engine.
  • This type of housing is also likely to receive cavities 5 of the type described above.
  • the local vein withdrawal 6 begins in this case at or downstream of the upstream end of the cavity 5 and ends at or slightly downstream of the trailing edge of the blades 1.
  • the invention relates to an optimization of the geometric characteristics of the cavities 5 and their positioning relative to the blades 1. It allows a very significant improvement of the operability of the compressor (in terms of yield and margin to pumping) thanks to its management of the flow in the clearance between blades and crankcase and its reinjection upstream of the mobile blading wheel 1. This improvement is particularly noticeable in the context of a highly loaded compressor, having blades of three-dimensional shape (forward arrow blades) and reduced inter-stage distances to limit the overall length of the compressor.
  • the downstream shape of the cavity 5, where the fluid is sucked is optimized for better guidance of the fluid upstream, and its upstream shape is optimized to ensure reinjection into the vein as close as possible to the radial direction. Its length is optimized to ensure the reinjection of the fluid as far upstream as possible from the blade.
  • the effectiveness of the present invention therefore comes from the combination of a limited axial overlap of the blade and a reinjection upstream of the blade at an optimized angle.
  • the assembly improves the efficiency of the compressor under steady-state operating conditions as well as under a strong aerodynamic stress intermediate between the nominal operating line and the stability limit (or pumping line) of the compressor. This is due to the fact that the local losses of efficiency induced by the shift L1 are compensated by the gain brought by the control of the recirculation of the air.
  • cavities associated with an abradable deposit can be directly machined directly into the housing or implanted via a coating technology by a specific insert, fixed to the housing.
  • this technology is applicable to any type of compressor, whether axial or centrifugal, and that it is intended for a turbojet engine or a turboprop.

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)
EP09795410.1A 2008-12-23 2009-12-16 Carter de compresseur à cavités optimisées Active EP2368045B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0858990A FR2940374B1 (fr) 2008-12-23 2008-12-23 Carter de compresseur a cavites optimisees.
PCT/EP2009/067326 WO2010072638A1 (fr) 2008-12-23 2009-12-16 Carter de compresseur a cavites optimisees

Publications (2)

Publication Number Publication Date
EP2368045A1 EP2368045A1 (fr) 2011-09-28
EP2368045B1 true EP2368045B1 (fr) 2017-12-13

Family

ID=40823269

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09795410.1A Active EP2368045B1 (fr) 2008-12-23 2009-12-16 Carter de compresseur à cavités optimisées

Country Status (9)

Country Link
US (1) US8845269B2 (zh)
EP (1) EP2368045B1 (zh)
JP (1) JP5686743B2 (zh)
CN (1) CN102265039B (zh)
BR (1) BRPI0923622B1 (zh)
CA (1) CA2747989C (zh)
FR (1) FR2940374B1 (zh)
RU (1) RU2514459C2 (zh)
WO (1) WO2010072638A1 (zh)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3913231A1 (fr) 2020-05-22 2021-11-24 Safran Aero Boosters Piège à débris

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CN102022351B (zh) * 2010-12-08 2012-06-27 北京航空航天大学 一种拓宽高负荷轴流压气机稳定工作范围的方法
FR2969230B1 (fr) 2010-12-15 2014-11-21 Snecma Aube de compresseur a loi d'empilage amelioree
US8678740B2 (en) * 2011-02-07 2014-03-25 United Technologies Corporation Turbomachine flow path having circumferentially varying outer periphery
FR2988146B1 (fr) 2012-03-15 2014-04-11 Snecma Carter pour roue a aubes de turbomachine ameliore et turbomachine equipee dudit carter
FR2989744B1 (fr) 2012-04-19 2014-06-13 Snecma Carter de compresseur a cavites au calage optimise
FR2989742B1 (fr) * 2012-04-19 2014-05-09 Snecma Carter de compresseur a cavites a forme amont optimisee
JP6010348B2 (ja) * 2012-06-01 2016-10-19 三菱日立パワーシステムズ株式会社 軸流圧縮機及びこれを備えたガスタービン
US20140093355A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Extended indentation for a fastener within an air flow
WO2014158236A1 (en) * 2013-03-12 2014-10-02 United Technologies Corporation Cantilever stator with vortex initiation feature
DE102013219818B3 (de) * 2013-09-30 2015-02-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. Axialverdichter
JP2016118165A (ja) * 2014-12-22 2016-06-30 株式会社Ihi 軸流機械およびジェットエンジン
US9926806B2 (en) 2015-01-16 2018-03-27 United Technologies Corporation Turbomachine flow path having circumferentially varying outer periphery
CN106286394B (zh) * 2016-10-14 2018-08-10 中国科学院工程热物理研究所 一种压气机连通式收缩缝机匣处理方法及装置
EP3543541A4 (en) * 2016-11-18 2020-07-08 Mitsubishi Heavy Industries, Ltd. COMPRESSOR, AND METHOD FOR PRODUCING BLADE THEREOF
WO2020231798A1 (en) 2019-05-14 2020-11-19 Carrier Corporation Centrifugal compressor including diffuser pressure equalization feature
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US20230151825A1 (en) * 2021-11-17 2023-05-18 Pratt & Whitney Canada Corp. Compressor shroud with swept grooves
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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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3913231A1 (fr) 2020-05-22 2021-11-24 Safran Aero Boosters Piège à débris
BE1028337A1 (fr) 2020-05-22 2021-12-17 Safran Aero Boosters Piège à débris

Also Published As

Publication number Publication date
US8845269B2 (en) 2014-09-30
BRPI0923622A2 (pt) 2020-08-11
US20120003085A1 (en) 2012-01-05
WO2010072638A1 (fr) 2010-07-01
EP2368045A1 (fr) 2011-09-28
RU2514459C2 (ru) 2014-04-27
RU2011130927A (ru) 2013-01-27
BRPI0923622B1 (pt) 2021-01-05
JP2012513561A (ja) 2012-06-14
CA2747989A1 (fr) 2010-07-01
FR2940374B1 (fr) 2015-02-20
JP5686743B2 (ja) 2015-03-18
FR2940374A1 (fr) 2010-06-25
CN102265039B (zh) 2015-03-04
CA2747989C (fr) 2016-08-09
CN102265039A (zh) 2011-11-30

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