EP1329639B1 - Zentripetale Abblasvorrichtung - Google Patents

Zentripetale Abblasvorrichtung Download PDF

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Publication number
EP1329639B1
EP1329639B1 EP03290061A EP03290061A EP1329639B1 EP 1329639 B1 EP1329639 B1 EP 1329639B1 EP 03290061 A EP03290061 A EP 03290061A EP 03290061 A EP03290061 A EP 03290061A EP 1329639 B1 EP1329639 B1 EP 1329639B1
Authority
EP
European Patent Office
Prior art keywords
compressor
air
holes
groove
interstice
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.)
Expired - Lifetime
Application number
EP03290061A
Other languages
English (en)
French (fr)
Other versions
EP1329639A1 (de
Inventor
Antoine Robert Alain Brunet
Patrick Pasquis
Alexandre Jean-Claude Auguste Roy
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 date
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Publication of EP1329639A1 publication Critical patent/EP1329639A1/de
Application granted granted Critical
Publication of EP1329639B1 publication Critical patent/EP1329639B1/de
Anticipated expiration legal-status Critical
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine

Definitions

  • the invention relates to an axial turbomachine compressor equipped with a device for the centripetal sampling of air in the vein of the compressor, this sampling air being intended for the cooling of the turbine, said compressor comprising two blades of mobile blades which extend radially outwardly at the periphery of two consecutive disks joined together by an outer shell provided with bores and a stationary straightening rotor ring disposed in the vein between said two rotor blade rings, said bores serving as inputs for air auditing said sampling device and opening into an annular groove provided under the gap separating the inner platforms of the straightening vanes, the rim of the upstream disk, said groove communicating with said vein by said gap.
  • centripetal air sampling device disposed inside the high-pressure rotor, is to bring a flow of air taken from a compressor stage to the turbine stages to be cooled. It is important that the cooling air arriving in the blades of the high pressure turbine, subjected to high temperatures, has a sufficient pressure to allow the formation of a protective air film around the blades of the turbine, and a temperature as low as possible.
  • the sampling device may comprise sampling channels provided in the upstream disk, as is disclosed by FR 2,609,500 and FR 2,614,654 , or sampling tubes arranged in the annular cavity separating the two disks, as is disclosed by US 5,475,313 .
  • the object of the invention is to provide easy to implement and inexpensive means that can significantly reduce the temperature of the air delivered to the high pressure turbine and reduce pressure losses, all things being equal. elsewhere.
  • the document UK 712,051 describes a sampling system where air guide vanes are arranged downstream of the ring of straightening vanes being fixed between two annular walls.
  • the invention relates to a turbomachine axial compressor equipped with a centripetal air sampling device in the vein of said compressor, this air being intended for the cooling of the turbine, said compressor comprising two blades of mobile blades which extend radially. outwardly at the periphery of two consecutive disks assembled by an outer shell provided with bores and a ring of stationary straightening vanes disposed in the vein between said two rotor blades, said bores serving as air inlets to said sampling device and opening into an annular groove provided under the gap between the inner platforms of the straightening vanes of the rim of the upstream disk, said groove communicating with said vein through said interstice, characterized in that said annular groove in which open said holes are located between the most upstream blade crown and the crown of rectifying blades and in that fixed guiding means imparting to the flow of air flowing in said groove a centripetal swirling motion in the direction of rotation of the compressor are arranged at least partly under said inner platforms of the straightening vanes and are integral with these, to
  • the relative total temperature of the air in the bores is substantially lowered compared to the same temperature in a conventional compressor, which improves the cooling of the turbine blades for the same flow, and increases their service life.
  • the pressure losses are also reduced, which improves the flow of air taken compared to the state of the art for identical bores and sampling devices and increases the rate of overpressure in the vanes of the turbine.
  • Said guide means are arranged at least partly under the inner platforms of the straightening vanes.
  • the means for guiding the air in the groove comprise a plurality of blade profiles evenly distributed around the axis of rotation of the compressor.
  • leading edges of the blading profiles extend at least partly in the gap.
  • the angle of attack of the profiles is determined according to the tangential velocity and the local radial velocity of the air passing through the gap.
  • the blade profiles increase the coefficient of air entrainment in the groove, which allows for the same total air temperature, to decrease the relative total temperature.
  • the improvement of the drive coefficient thanks to the proposed blade profiles is about 30% compared to the state of the art, which corresponds to a decrease in the relative total temperature of approximately 40 ° C. This makes it possible to multiply the life of the blades of the turbine by two, for the same flow taken.
  • the figure 1 shows a compressor 1 of an X axis turbomachine according to the state of the art equipped with a centripetal sampling device 2.
  • This compressor 1 comprises an upstream disk 3 having at its periphery a first ring of moving blades 4 disposed in the vein 5, a downstream disc 6 having at its periphery a second ring of moving blades 7 axially offset in the vein 5, and a ring of stationary straightening vanes 8 arranged in the vein 5 between the first and the second ring of moving blades.
  • the upstream disk 3 and the downstream disk 6 are interconnected by an outer shell 9 provided with a sealing labyrinth 10 cooperating with the inner face of the inner platforms 11 of the straightening vanes 8.
  • a groove 12 is provided under interstice 13 which separates the rim of the upstream disk 3, inner platforms 11.
  • Holes 14 formed in the outer shell 9 open into the groove 12. These holes 14 allow the introduction of a sampling air flow rate in the centripetal sampling device 2 which in the example shown on the figure 1 comprises radial channels 15 formed in the wall of the upstream disk 3.
  • the sampled air is conducted radially inwards by the radial channels 15 and deflected rearwardly by the radially inner portion 16 of the upstream disk 3, and flows axially to the stages of the turbine driving the compressor 1.
  • the speed chart of the figure 3 shows that the relative speed Vr 1 of the air in the vicinity of the bores 14 relative to the periphery of the upstream disk 3 is relatively high.
  • Va 1 denotes the absolute speed of the air and
  • Ve represents the speed of the rim of the disc 3.
  • the figure 2 shows the same compressor 1 equipped with fixed guide means 20 for printing air flowing in the groove 12 between the gap 13 and the holes 14 a centripetal swirling motion in the direction of rotation of the compressor 1.
  • the air has an absolute velocity Va 2 whose norm is equal to the norm of the absolute velocity Va 1 , but which is substantially directed tangentially to the periphery of the outer shell 9, so that the velocity relative Vr 2 of the air relative to the upstream disk 3 is significantly lower than the relative speed Vr 1 of the state of the art, as is shown in FIG. figure 4 .
  • the guide means 20 are arranged in the groove 12 under the upstream portion of the inner platforms 11 of the straightening vanes 8.
  • These guide means 20 comprise a plurality of blade profiles 21 or fins regularly distributed around the axis of rotation X of the compressor 1 and whose leading edges 22 extend at least partly in the gap 13.
  • the angle of attack ⁇ of these profiles 21 is determined as a function of the tangential speed and the local radial velocity of the air passing through the gap 13.
  • the vane profiles 21 are drawn in such a way that the air entering through the gap 13 and flowing between the vane profiles 21 comes out with a velocity Va 2 , represented by an arrow or vector on the Figures 4 and 6 substantially tangential to the drive speed Ve of the rotor in order to substantially reduce the relative speed Vr 2 of the air entering the bores 14.

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

Claims (6)

  1. Axialverdichter einer Turbomaschine, der mit einer Vorrichtung (2) zur zentripetalen Entnahme von Luft aus dem Kanal (5) des Verdichters ausgestattet ist, wobei diese Luft zur Kühlung der Turbine bestimmt ist, wobei der Verdichter zwei Laufschaufelkränze (4, 7), die sich am Umfang von zwei aufeinanderfolgenden Scheiben (3, 6), die durch einen mit Bohrungen (14) versehenen Außenring (9) verbunden sind, radial nach außen erstrecken, sowie einen Kranz fester Leitschaufeln (8) umfaßt, der in dem Kanal (5) zwischen den zwei Laufschaufelkränzen angeordnet ist, wobei die Bohrungen der Entnahmevorrichtung als Lufteinlässe dienen und in eine ringförmige Nut (12) münden, die unter dem Zwischenraum (13) vorgesehen ist, welcher die Innenplattformen (11) der Leitschaufeln (8) von dem Bund der stromaufwärtigen Scheibe trennt, wobei die Nut über den Zwischenraum mit dem Kanal in Verbindung steht, dadurch gekennzeichnet, daß die ringförmige Nut (12), in welche die Bohrungen (14) münden, zwischen dem am weitesten stromaufwärts gelegenen Laufschaufelkranz (4) und dem Leitschaufelkranz (8) gelegen ist und daß feste Führungsmittel (20), die dem in der Nut (12) zirkulierenden Luftstrom eine zentripetale Wirbelbewegung in Rotationsrichtung des Verdichters mitteilen, wenigstens teilweise unter den Innenplattformen (11) der Leitschaufeln angeordnet und mit diesen fest verbunden sind, um die Relativgeschwindigkeit der in die Bohrungen (14) eintretenden Luft gegenüber diesen in Rotation befindlichen Bohrungen zu verringern.
  2. Verdichter nach Anspruch 1, dadurch gekennzeichnet, daß die Mittel zum Führen der Luft in der Nut eine Vielzahl von Schaufelprofilen (21) umfassen, die um die Rotationsachse (X) des Verdichters gleichmäßig verteilt sind und die mit den Innenplattformen (11), unter diesen vorspringend, fest verbunden sind.
  3. Verdichter nach Anspruch 2, dadurch gekennzeichnet, daß sich die Eintrittskanten (22) der Schaufelprofile (21) wenigstens teilweise in den Zwischenraum (13) erstrecken.
  4. Verdichter nach Anspruch 3, dadurch gekennzeichnet, daß der Anstellwinkel (α) der Profile in Abhängigkeit der Tangentialgeschwindigkeit und der lokalen Radialgeschwindigkeit der den Zwischenraum durchlaufenden Luft bestimmt wird.
  5. Verdichter nach irgendeinem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die Entnahmevorrichtung (20) in der stromaufwärtigen Scheibe (3) ausgebildete Entnahmekanäle (15) umfaßt.
  6. Turbomaschine, die einen Verdichter nach einem der Ansprüche 1 bis 5 umfaßt.
EP03290061A 2002-01-17 2003-01-10 Zentripetale Abblasvorrichtung Expired - Lifetime EP1329639B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0200519 2002-01-17
FR0200519A FR2834758B1 (fr) 2002-01-17 2002-01-17 Dispositif pour redresser l'air d'alimentation d'un prelevement centripete dans un compresseur

Publications (2)

Publication Number Publication Date
EP1329639A1 EP1329639A1 (de) 2003-07-23
EP1329639B1 true EP1329639B1 (de) 2008-03-12

Family

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Family Applications (1)

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EP03290061A Expired - Lifetime EP1329639B1 (de) 2002-01-17 2003-01-10 Zentripetale Abblasvorrichtung

Country Status (6)

Country Link
US (1) US6908278B2 (de)
EP (1) EP1329639B1 (de)
CA (1) CA2416157C (de)
DE (1) DE60319607T2 (de)
FR (1) FR2834758B1 (de)
RU (1) RU2295656C2 (de)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7686576B2 (en) * 2006-10-24 2010-03-30 General Electric Company Method and apparatus for assembling gas turbine engines
US7661924B2 (en) * 2007-03-28 2010-02-16 General Electric Company Method and apparatus for assembling turbine engines
RU2451840C2 (ru) * 2010-06-21 2012-05-27 Открытое акционерное общество "Авиадвигатель" Ротор компрессора газотурбинного двигателя
DE102010063071A1 (de) * 2010-12-14 2012-06-14 Rolls-Royce Deutschland Ltd & Co Kg Kühlvorrichtung für ein Strahltriebwerk
US20130177430A1 (en) * 2012-01-05 2013-07-11 General Electric Company System and method for reducing stress in a rotor
US9121413B2 (en) * 2012-03-22 2015-09-01 General Electric Company Variable length compressor rotor pumping vanes
US9091173B2 (en) * 2012-05-31 2015-07-28 United Technologies Corporation Turbine coolant supply system
US9039357B2 (en) * 2013-01-23 2015-05-26 Siemens Aktiengesellschaft Seal assembly including grooves in a radially outwardly facing side of a platform in a gas turbine engine
CN109209980B (zh) * 2017-06-30 2020-06-05 中国航发商用航空发动机有限责任公司 一种用于轴流压气机的导流板
RU189794U1 (ru) * 2017-08-29 2019-06-04 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Ротор компрессора газотурбинного двигателя
RU2728550C1 (ru) * 2019-09-05 2020-07-31 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Устройство отбора воздуха в роторе компрессора турбореактивного двигателя
WO2022066471A1 (en) 2020-09-22 2022-03-31 General Electric Company Turbomachine and system for compressor operation
CN113006880B (zh) * 2021-03-29 2022-02-22 南京航空航天大学 一种用于涡轮叶片端壁的冷却装置

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2618433A (en) * 1948-06-23 1952-11-18 Curtiss Wright Corp Means for bleeding air from compressors
GB712051A (en) * 1951-10-10 1954-07-14 Rolls Royce Improvements in or relating to axial-flow fluid machines
US3085400A (en) * 1959-03-23 1963-04-16 Gen Electric Cooling fluid impeller for elastic fluid turbines
FR2609500B1 (fr) 1987-01-14 1991-04-12 Snecma Disque de compresseur de turbomachine avec accelerateur centripete pour l'aspiration d'air de refroidissement de la turbine
FR2614654B1 (fr) 1987-04-29 1992-02-21 Snecma Disque de compresseur axial de turbomachine a prelevement d'air centripete
US5475313A (en) 1994-09-20 1995-12-12 Dykes; Wallace E. Primary charge roller evaluator

Also Published As

Publication number Publication date
RU2295656C2 (ru) 2007-03-20
DE60319607T2 (de) 2009-04-02
FR2834758A1 (fr) 2003-07-18
US6908278B2 (en) 2005-06-21
FR2834758B1 (fr) 2004-04-02
DE60319607D1 (de) 2008-04-24
CA2416157A1 (fr) 2003-07-17
EP1329639A1 (de) 2003-07-23
US20030133787A1 (en) 2003-07-17
CA2416157C (fr) 2011-05-17

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