EP1693572B1 - Luftentnahme bei den rotierenden Schaufelspitzen eines Hochdruckverdichters eines Turbinentriebwerks - Google Patents

Luftentnahme bei den rotierenden Schaufelspitzen eines Hochdruckverdichters eines Turbinentriebwerks Download PDF

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Publication number
EP1693572B1
EP1693572B1 EP06100669.8A EP06100669A EP1693572B1 EP 1693572 B1 EP1693572 B1 EP 1693572B1 EP 06100669 A EP06100669 A EP 06100669A EP 1693572 B1 EP1693572 B1 EP 1693572B1
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EP
European Patent Office
Prior art keywords
turbomachine
compressor according
turbomachine compressor
bleed holes
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
EP06100669.8A
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English (en)
French (fr)
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EP1693572A2 (de
EP1693572A3 (de
Inventor
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
Original Assignee
SNECMA SAS
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Publication of EP1693572A3 publication Critical patent/EP1693572A3/de
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Publication of EP1693572B1 publication Critical patent/EP1693572B1/de
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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
    • F04D29/66—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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D27/023—Details or means for fluid extraction
    • 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
    • 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 present invention relates to the specific field of turbomachines and more particularly relates to a device for sampling air in the aerodynamic stream of a high-pressure axial compressor of these turbomachines.
  • turbomachines turbojet engines or turboprop engines
  • turbomachines turbojet engines or turboprop engines
  • this game can significantly modify and degrade the operation of the compressor until the occurrence of a phenomenon of "pumping".
  • patent FR 2 564 533 which, to avoid pumping in an axial compressor, shows a specific shaping of the casing associated with a specific arrangement of an air flow system.
  • the subject of the present invention is a turbomachine compressor which makes it possible to obtain a noticeable improvement over the devices of the prior art from the efficiency and the margin of safety with respect to pumping, also known as pumping margin.
  • a turbomachine compressor comprising a plurality of blades and, spaced in an axial direction relative to a longitudinal central axis of the turbomachine, a plurality of blades, a fixed casing enveloping said plurality of blades.
  • said fixed housing comprises a plurality of sampling holes centered between 5 and 50% of the length of rope of the blade and a diameter less than or equal to 30% of said length of rope of the blade, each of said sampling holes having a double inclination with respect to said longitudinal central axis.
  • the ratio between the overall air flow rate of the compressor and the air flow rate taken is between 0.1 and 5%.
  • said fixed casing further comprises oblique lamellae arranged in line with said plurality of blades on both sides of each sampling hole and oriented at said angle ⁇ .
  • said sampling holes each comprise a first inclination axis having an angle ⁇ with respect to the longitudinal central axis of between 30 and 90 ° and a second axis of inclination perpendicular to the first and having an angle ⁇ relative to the central longitudinal axis between 30 and 90 °.
  • sampling holes may be arranged in staggered rows or formed of axisymmetric slots. These sampling holes can also be non-circular.
  • the figure 1 is a schematic view of a section of a high-pressure axial compressor 10 disposed about a longitudinal central axis (motor axis 12) of a turbomachine and delimited at its outer portion by a housing 14 forming a surface of revolution around this longitudinal central axis.
  • This compressor comprises several successive stages of compression (in an axial direction), each stage comprising distributed over the circumference a plurality of blades (rotor 16) rotatable about the motor axis and a plurality of blades (stator 18).
  • a clearance e exists between the upper end 20 of each moving blade and the fixed casing 14 which surrounds the compressor.
  • This game can be the place of violent turbulence which can deteriorate the configuration of the flow between the different stages and thus lead to a degradation of the performances of the compressor or, in the extreme, to cause a phenomenon known as "pumping" or "stalling". Consisting of an instantaneous fall in the compression ratio and an inversion of the air flow through the compressor which then leaves the upstream compressor.
  • the safety range in operation with respect to pumping is increased by the addition of an air sampling device disposed at the top of the blades, that is to say substantially at the level of from his leading edge 22.
  • This sampling device comprises a plurality of holes 24, preferably cylindrical, made in the fixed casing 14, centered between 5 and 50% of the length of rope of the blade and having a diameter less than or equal to 30% of the rope length of dawn, the rope of dawn being the line segment connecting the leading edge to the trailing edge of a moving blade.
  • the number of sampling holes is determined as a function of the air flow rate to be taken with respect to the overall air flow through the compressor. Typically, an air flow rate of between 0.1 and 5% guarantees operating efficiency of the device according to the different measurements made by the inventors.
  • sampling holes have a double inclination with a first axis projected in the blade vane plane having an angle ⁇ relative to the motor axis of between 30 and 90 ° (see FIG. figure 2 ) and a second axis projected in the meridian plane (perpendicularity to the first) having an angle ⁇ with respect to the motor axis of between 30 and 90 °.
  • this cylindrical configuration of sampling holes and this linear arrangement on a single row can not be limiting.
  • the figure 3 shows for example a provision of these sampling holes in two rows, the holes being staggered in the previously defined limit of 5 to 50% of the rope length of the blade.
  • these sampling holes have a non-circular shape, square or oblong, for example.
  • sampling holes in the form of an axisymmetric slit.
  • the air which conventionally sneaks by the clearance e above the ends 20 of the blades because of the pressure difference existing between the intrados and extrados faces of these blades is in fact Part sucked by the sampling holes 24.
  • the decrease in this parasitic flux between the two faces of the same blade has the immediate effect of increasing the stability and performance of the compressor.
  • the collected air can join, possibly via a system of protective sheets (not shown), existing sampling collectors of the turbomachine for use engine or other, for example avionics.
  • FIG. figure 5 which shows the variation of the compression ratio as a function of the efficiency of the compressor for a compressor of the prior art (curve 30) and for a compressor provided with the device according to the invention (curve 32) and the figure 6 which shows the variation of the compression ratio as a function of the compressor inlet flow rate for a compressor of the prior art (curve 40) and for a compressor provided with the device according to the invention (curve 42).
  • the effectiveness of the device can be further improved by directing the air directly to the sampling holes as illustrated by Figures 7 and 8 which show the addition of oblique lamellae 50 arranged on the fixed housing to the right of the plurality of blades on both sides of each sampling hole 24. These lamellae machined directly into the housing or connected thereto are oriented at the same angle ⁇ with respect to the motor axis 12 as the sampling holes.
  • this configuration can be implanted on a casing 14 comprising a withdrawal at the right of the dawn (called trench 52) as shown in FIG. figure 9 , or else including a groove 54 at the right of the blade (called crankcase treatment) as shown by the Figures 10 and 11 .
  • trench 52 a withdrawal at the right of the dawn
  • crankcase treatment a groove 54 at the right of the blade
  • the device of the invention can also be used at one or more transonic stages of a high pressure compressor or on a low pressure compressor.
  • the present invention can not be limited to the fastening and driving structure of the blades shown in FIG. figure 1 and a structure using so-called staples or hammer is also conceivable.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (9)

  1. Turbomaschinenverdichter, umfassend wenigstens eine Vielzahl von Laufschaufeln (16) und, in einer axialen Richtung gegenüber einer Längsmittelachse der Turbomaschine (12) beabstandet, eine Vielzahl von Leitschaufeln (18), ein festes Gehäuse (14), das die Vielzahl von Laufschaufeln umhüllt, dadurch gekennzeichnet, dass das feste Gehäuse eine Vielzahl von Entnahmelöchern (24) umfasst, die zwischen 5 und 50 % der Sehnenlänge der Schaufel angeordnet sind und einen Durchmesser kleiner oder gleich 30 % der Sehnenlänge der Schaufel aufweisen, wobei ein jedes der Entnahmelöcher eine zweifache Neigung gegenüber der Längsmittelachse aufweist.
  2. Turbomaschinenverdichter nach Anspruch 1, dadurch gekennzeichnet, dass die Entnahmelöcher jeweils eine erste Neigungsachse, die einen Winkel ϕ gegenüber der Längsmittelachse zwischen 30 und 90°aufweist, sowie eine zweite Neigungsachse, die zu der ersten senkrecht ist und einen Winkel θ gegenüber der Längsmittelachse zwischen 30 und 90°aufweist, umfassen.
  3. Turbomaschinenverdichter nach Anspruch 1 oder Anspruch 2, dadurch gekennzeichnet, dass das Verhältnis zwischen der Gesamtluftmenge der Turbomaschine und der entnommenen Luftmenge im Bereich zwischen 0,1 und 5 % liegt.
  4. Turbomaschinenverdichter nach Anspruch 1 oder Anspruch 2, dadurch gekennzeichnet, dass das feste Gehäuse ferner Schräglamellen (50) umfasst, die gegenüber der Vielzahl von Laufschaufeln auf beiden Seiten eines jeden Entnahmelochs angeordnet und in dem Winkel ϕ ausgerichtet sind.
  5. Turbomaschinenverdichter nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass das feste Gehäuse ferner eine Riefelung (54), die um jedes Entnahmeloch herum angeordnet ist, umfasst.
  6. Turbomaschinenverdichter nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Entnahmelöcher versetzt angeordnet sind.
  7. Turbomaschinenverdichter nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Entnahmelöcher unrund sind.
  8. Turbomaschinenverdichter nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Entnahmelöcher von achsensymmetrischen Schlitzen gebildet sind.
  9. Turbomaschine, die einen Hochdruckaxialverdichter nach einem der Ansprüche 1 bis 8 umfasst.
EP06100669.8A 2005-02-16 2006-01-20 Luftentnahme bei den rotierenden Schaufelspitzen eines Hochdruckverdichters eines Turbinentriebwerks Active EP1693572B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0501567A FR2882112B1 (fr) 2005-02-16 2005-02-16 Prelevement en tete des roues mobiles de compresseur haute pression de turboreacteur

Publications (3)

Publication Number Publication Date
EP1693572A2 EP1693572A2 (de) 2006-08-23
EP1693572A3 EP1693572A3 (de) 2011-05-18
EP1693572B1 true EP1693572B1 (de) 2015-11-04

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EP06100669.8A Active EP1693572B1 (de) 2005-02-16 2006-01-20 Luftentnahme bei den rotierenden Schaufelspitzen eines Hochdruckverdichters eines Turbinentriebwerks

Country Status (7)

Country Link
US (1) US7549838B2 (de)
EP (1) EP1693572B1 (de)
JP (1) JP5004476B2 (de)
CN (1) CN1840864B (de)
CA (1) CA2536132C (de)
FR (1) FR2882112B1 (de)
RU (1) RU2395010C2 (de)

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EP2058524A1 (de) 2007-11-12 2009-05-13 Siemens Aktiengesellschaft Kompressor mit veränderlichen Leitschaufeln mit Zapfluftsystem
FR2958694B1 (fr) * 2010-04-07 2014-04-18 Snecma Compresseur de moteur, en particulier de turboreacteur d'aeronef, muni d'un systeme de prelevement d'air
FR2970302B1 (fr) * 2011-01-11 2015-07-17 Snecma Turboreacteur a double flux
JP5591142B2 (ja) * 2011-02-16 2014-09-17 三菱重工業株式会社 回転機械の抽気構造
EP2532898A1 (de) * 2011-06-08 2012-12-12 Siemens Aktiengesellschaft Axialturboverdichter
CN102312860B (zh) * 2011-09-01 2013-04-24 西北工业大学 一种吸力面抽吸的压气机静子叶片
CN103133057A (zh) * 2011-11-25 2013-06-05 中国航空工业集团公司沈阳发动机设计研究所 一种t型槽结构吸附式空心静子叶片
US9399951B2 (en) * 2012-04-17 2016-07-26 General Electric Company Modular louver system
RU2623323C2 (ru) * 2012-09-06 2017-06-23 Сименс Акциенгезелльшафт Турбомашина и способ ее работы
CN103994101B (zh) * 2013-02-19 2016-04-20 中国科学院工程热物理研究所 基于多级轴流压气机轮毂端壁自循环抽吸喷气装置及方法
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EP2868898A1 (de) 2013-10-30 2015-05-06 Siemens Aktiengesellschaft Verbesserter Teillastbetrieb einer Gasturbine mit einstellbarem Bypass-Strömungskanal
GB201702383D0 (en) * 2017-02-14 2017-03-29 Rolls Royce Plc Gas turbine engine fan blade with axial lean
CN108119406B (zh) * 2018-01-11 2020-11-27 南京航空航天大学 轴流压气机周向大间隔小通孔机匣
JP7041033B2 (ja) * 2018-09-26 2022-03-23 本田技研工業株式会社 軸流圧縮機
JP7228402B2 (ja) * 2019-02-18 2023-02-24 株式会社オティックス ターボチャージャ用コンプレッサハウジング及びその製造方法
CN110083869B (zh) * 2019-03-27 2021-02-26 南京航空航天大学 一种评估模式变换对涡喷/涡扇变循环发动机稳定裕度影响的计算方法
CN111734679A (zh) * 2020-07-02 2020-10-02 中国航发常州兰翔机械有限责任公司 一种带放气孔的航空发动机压气机内机匣及其加工方法
CN114183403B (zh) * 2022-02-14 2022-05-06 成都中科翼能科技有限公司 一种斜孔式处理机匣及压气机

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Also Published As

Publication number Publication date
EP1693572A2 (de) 2006-08-23
JP2006226285A (ja) 2006-08-31
RU2395010C2 (ru) 2010-07-20
CN1840864A (zh) 2006-10-04
RU2006104789A (ru) 2007-09-27
JP5004476B2 (ja) 2012-08-22
CN1840864B (zh) 2010-05-26
CA2536132A1 (fr) 2006-08-16
US20060182623A1 (en) 2006-08-17
EP1693572A3 (de) 2011-05-18
US7549838B2 (en) 2009-06-23
CA2536132C (fr) 2013-06-18
FR2882112B1 (fr) 2007-05-11
FR2882112A1 (fr) 2006-08-18

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