EP1505261B1 - Vorrichtung für die Regelung von Spalten in einer Gasturbine - Google Patents

Vorrichtung für die Regelung von Spalten in einer Gasturbine Download PDF

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Publication number
EP1505261B1
EP1505261B1 EP04291818A EP04291818A EP1505261B1 EP 1505261 B1 EP1505261 B1 EP 1505261B1 EP 04291818 A EP04291818 A EP 04291818A EP 04291818 A EP04291818 A EP 04291818A EP 1505261 B1 EP1505261 B1 EP 1505261B1
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EP
European Patent Office
Prior art keywords
air
ring assembly
feed channel
air circulation
control box
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
EP04291818A
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English (en)
French (fr)
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EP1505261A1 (de
Inventor
Alain Gendraud
Delphine Roussin
David Audeon
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
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1505261A1 publication Critical patent/EP1505261A1/de
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Publication of EP1505261B1 publication Critical patent/EP1505261B1/de
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components

Definitions

  • the present invention relates to the general field of play control between the rotary blade tip and a fixed ring assembly of a gas turbine.
  • a gas turbine for example a turbomachine high-pressure turbine, typically comprises a plurality of stationary vanes arranged alternately with a plurality of blades in the passage of hot gases from the combustion chamber of the turbomachine.
  • the turbine blades are surrounded around the circumference of the turbine by a fixed ring assembly. This fixed ring assembly defines the flow path of the hot gases through the vanes of the turbine.
  • Such means are generally in the form of annular conduits which surround the fixed ring assembly and which are traversed by air taken from other parts of the turbomachine. This air is injected onto the outer surface of the stationary ring assembly which is opposed to the hot gas flow path and thereby causes thermal expansion or contraction of the fixed ring assembly varying its diameter.
  • thermal expansions and contractions are controlled according to the operating speed of the gas turbine by means of a valve which makes it possible to control the flow rate and the temperature of the air supplying the pipes.
  • the assembly constituted by the pipes and the valve thus forms a game steering box at the top of the blades.
  • control casings known until now do not always make it possible to obtain a great uniformity of temperature over the entire circumference of the fixed ring assembly.
  • a lack of homogeneity The temperature causes distortions in the fixed ring assembly which are particularly detrimental to the efficiency and life of the gas turbine.
  • the air from the driver housings that has been injected onto the outer surface of the fixed ring assembly must be exhausted to the outside. This evacuation of the air must be able to proceed without disturbing the flow of the air which is injected on the outer surface of the fixed ring assembly.
  • the air to be evacuated generally tends to disturb the flow of air that is injected, which decreases the effectiveness of the game control box at the top of the blades .
  • the present invention therefore aims to overcome such drawbacks by proposing a game control device which makes it possible to obtain a high temperature homogeneity of the fixed ring assembly while avoiding disturbances between the air to be evacuated and the air to inject.
  • a device for controlling clearance between the top of rotating blades and a stationary ring assembly of a gas turbine comprising a circular control box surrounding the fixed ring assembly, characterized in that the control box comprises at least two annular air circulation rings spaced from each other in the axial direction and each having a plurality of perforations for changing the temperature of the fixed ring assembly by discharge. of air, an annular air supply channel radially spaced from the air circulation ramps, at least one air duct for supplying air to the supply channel, and a plurality of hollow distribution spacers connecting the air supply duct to the airflow ramps to supply air to the same while allowing air that has been discharged from the fixed ring assembly to flow between the supply channel and the air ducts. traffic meters to be evacuated.
  • the radial spacing between the supply channel and the air circulation ramps of the control box thus provides a space for evacuating the air having been discharged onto the fixed ring assembly. In this way, the air which has been discharged is discharged radially and does not disturb the flow of air discharging on the fixed ring assembly.
  • This radial spacing also makes it possible to avoid any heat exchange between the supply channel and the air circulation ramps of the control box, which improves the efficiency of the game control device.
  • the control unit may be in sealing engagement, at an upstream axial end, against the outer casing, and, at one axial end downstream, against the inner casing in order to define, inside the annular chamber, an upstream chamber of air discharge and a downstream air evacuation enclosure sealed with respect to the upstream enclosure.
  • the arrangement, the number and the diameter of drilling of the hollow distribution spacers makes it possible to regulate the flow of air supplying the air circulation ramps and thus to homogenize the temperature of the fixed ring assembly.
  • the distribution spacers connecting the supply channel to one of the air circulation ramps can be angularly aligned or offset with respect to the distribution spacers of the other air circulation ramps, and the angular spacing between two successive distribution spacers preferably do not exceed 45 °.
  • the figure 1 illustrates, in longitudinal section, a turbomachine high-pressure turbine 2 equipped with a game control device according to the invention.
  • the present invention could also be applied to a turbomachine low-pressure turbine or to any other type of machine equipped with a game control device.
  • the high-pressure turbine 2 is composed in particular of a plurality of blades 4 arranged in a flow passage of hot gas 6 from a combustion chamber (not shown) of the turbomachine. These blades 4 are arranged downstream of the blades 8 of the turbine relative to the flow direction 10 of the hot gases in the passage 6.
  • the blades 4 of the high-pressure turbine 2 are surrounded by a plurality of fixed ring segments 14 arranged circumferentially around the axis of the turbine so as to form a circular and continuous surface.
  • These ring segments 12 are mounted on an internal casing 14 of the turbomachine by means of a plurality of spacers 16.
  • spacers 16 For the following description, we designate the set formed of fixed ring segments 12, internal casing 14 and spacers 16 by the term "fixed ring assembly".
  • the inner housing 14 of the fixed ring assembly is provided with annular fins or bosses 18 which have a disk shape extending in a radial direction. These fins 18 have the main function of acting as a heat exchanger. On the figure 1 , the fins 18 are two in number. However, we can imagine a larger number of fins.
  • the fixed ring segments 12 have an inner surface 12a directly in contact with the hot gases and which partly defines the flow passage of the hot gases 6.
  • a radial space is left between the inner surface 12a of the ring segments 12 and the top 4a of the blades 4 of the turbine to allow rotation of the latter.
  • This radial space thus defines a clearance that must be reduced as much as possible in order to increase the efficiency of the turbine.
  • a game control device formed of a circular control box 22 surrounding the fixed ring assembly, and more specifically the inner casing 14.
  • this control unit 22 is intended to cool or heat the fins 18 of the inner casing 14 by discharge (or impact) of air thereon. Under the effect of this air discharge, the inner casing 14 retracts or expands, which decreases or increases the diameter of the fixed ring segments 12 of the turbine.
  • the air circulation ramps 24 approximately match the shape of the fins 18. In this case, they each have a substantially rectangular cross section.
  • the control unit 22 also comprises an annular air supply duct 28 for supplying air to the air circulation ramps 24.
  • the air supply duct 28 surrounds the circulation ramps 24.
  • At least one air duct 30 opens into the feed channel 28 to supply it with air.
  • the air circulating in the air duct 30 is taken from other parts of the turbomachine.
  • this air can be taken at one or more stages of the high or low pressure compressors of the turbomachine, or at the level of the fan thereof.
  • the air supply duct 28 and the air circulation ramps 24 are spaced in the radial direction and are interconnected by a plurality of hollow distribution spacers 32.
  • the figure 2 illustrates more precisely the path of the air to be evacuated.
  • the arrows F1 represent the tangential directions of flow of the air in the feed channel 28 and in the air circulation ramps 24, whereas the arrow F2 illustrates the axial direction of flow of the air. air having been discharged on the fins of the inner casing.
  • the turbine 2 is advantageously provided with an outer casing 34 surrounding the inner casing 14 of the fixed ring assembly. At an upstream axial end, this outer casing 34 is fixed to the inner casing 14 by a fastener 36 of screw / nut type.
  • the inner casings 14 and outer 34 define between them an annular chamber 38 in which is mounted the control box 22 of the game control device according to the invention. More precisely, the control box 22 bears, at an upstream axial end 22a, against the outer casing 34, and, at a downstream axial end 22b, against the inner casing 14. Preferably, the support of the upstream ends 22a and downstream 22b of the control box 22 is effected in a sealed manner, by means of seals 40.
  • the inner casing 14 has, at a downstream axial end, an opening 44 opening in the downstream exhaust air chamber 42b to evacuate the air confined thereto.
  • This opening 44 which may be provided with a bushing 46, thus evacuates the air having been discharged on the fins 18 of the inner casing in order to supply, for example, the first stage of a low-pressure distributor (not shown) of the turbomachine.
  • control box consists of more than two distinct angular sectors of housing which, when put end to end, together form a 360 ° housing.
  • the housing sectors 48 represented on the Figures 3A and 3B are closed at each of their angular ends, so that air does not flow from one housing sector to another. However, it is also possible to make a connection between the housing sectors to allow an air passage from one housing sector to another.
  • Each housing sector 48 is further supplied by a single air duct 30 opening into the supply channel 28 equidistant from the two angular ends of the housing sector.
  • the air duct could also lead to one of the angular ends of the housing sector. Several air ducts are also possible.
  • each housing sector 48 there is provided, for each housing sector 48, four hollow distribution spacers 32 connecting the feed channel 28 to the circulation ramp 24 shown. These hollow distribution spacers 32 are disposed on the half-circumference of the housing sector 48 so that the angular distance between two successive spacers preferably does not exceed 45 °.
  • the angular offset of the hollow distribution spacers between the air circulation ramps makes it possible to obtain a better temperature homogeneity in the control box and thus to avoid any distortion of the fixed ring assembly.
  • Such an angular offset can for example be obtained in the case of the same housing sector comprising three air circulation ramps as illustrated in FIGS. figures 1 and 2 .
  • the central ramp 24a (or reciprocally the upstream ramps 24b and downstream 24c) can have the configuration of the figure 3A
  • the upstream ramp 24b and the downstream ramp 24c (or conversely the central ramp 24a) can have the configuration of the figure 3B .
  • Such a provision is similar, for the three ramps 24a, 24b and 24c, in a staggered arrangement distribution spacers 32 with a symmetry of arrangement between the upstream ramp 24b and downstream 24c.
  • This symmetry of arrangement makes it possible to obtain a substantially identical thermal expansion or contraction between the two fins 18 of the inner casing 14 so as to improve the temperature homogeneity of the fixed ring assembly.
  • the hollow distribution spacers connecting the supply channel of the same housing sector to one of the air circulation ramps can be aligned angularly with respect to the hollow distribution spacers connecting the feed channel with the other air circulation ramps.
  • an angular alignment of the hollow distribution spacers can be obtained by giving the three air circulation ramps the same configuration.
  • this configuration of the three air circulation ramps may be identical to that of the figure 3A or from figure 3B .

Claims (9)

  1. Vorrichtung zur Kontrolle des Spiels zwischen der Spitze (4a) umlaufender Schaufeln (4) und einer Einheit mit festem Ring einer Gasturbine (2), wobei die Vorrichtung ein kreisförmiges Steuergehäuse (22) umfaßt, das die Einheit mit festem Ring umschließt, wobei das Steuergehäuse (22) folgendes umfaßt:
    wenigstens zwei ringförmige Luftzirkulationsleitungen (24a, 24b, 24c), die in axialer Richtung voneinander beabstandet sind und jeweils eine Vielzahl von Perforierungen (26) aufweisen, um die Temperatur der Einheit mit festem Ring durch Luftentladung zu ändern;
    einen ringförmigen Luftzufuhrkanal (28), der von den Luftzirkulationsleitungen (24a, 24b, 24c) radial beabstandet ist;
    wenigstens eine Luftleitung (30), um den Zufuhrkanal (28) mit Luft zu versorgen; und
    dadurch gekennzeichnet, daß eine Vielzahl hohler Verteilungsstege (32) den Luftzufuhrkanal (28) mit den Luftzirkulationsleitungen (24a, 24b, 24c) verbindet, um letztere mit Luft zu versorgen und gleichzeitig der Luft, die auf die Einheit mit festem Ring entladen wurde, zu ermöglichen, zwischen dem Zufuhrkanal (28) und den Zirkulationsleitungen (24a, 24b, 24c) zu zirkulieren, um dort abgeführt zu werden.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß die Einheit mit festem Ring ein Innengehäuse (14) umfaßt, das von einem Außengehäuse (34) der Gasturbine (2) derart umgeben ist, daß ein ringförmiger Raum (38) definiert wird, in dem das Steuergehäuse (22) angebracht ist.
  3. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, daß das Steuergehäuse (22) an einem stromaufwärtigen axialen Ende (22a) an dem Außengehäuse (34) und an einem stromabwärtigen axialen Ende (22b) an dem Innengehäuse (14) dicht anliegt, um innerhalb des ringförmigen Raums (38) einen stromaufwärtigen Luftentladungsraum (42a) sowie einen gegenüber dem stromaufwärtigen Raum (42a) dichten stromabwärtigen Luftabführraum (42b) zu definieren.
  4. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, daß das Innengehäuse (14) an einem stromabwärtigen axialen Ende eine sich in den stromabwärtigen Luftabführraum (42b) öffnende Luftöffnung (44) aufweist, um die Luft, die auf die Einheit mit festem Ring entladen worden ist, abzuführen.
  5. Vorrichtung nach irgendeinem der Ansprüche 2 bis 4, dadurch gekennzeichnet, daß das Innengehäuse (14) ringförmige Rippen (18) umfaßt und daß die Luftzirkulationsleitungen (24a, 24b, 24c) im wesentlichen die Form der Rippen (18) annehmen.
  6. Vorrichtung nach irgendeinem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß das Steuergehäuse (22) aus wenigstens zwei getrennten Gehäusewinkelabschnitten (48) besteht.
  7. Vorrichtung nach irgendeinem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die hohlen Verteilungsstege (32), welche den Zufuhrkanal (28) mit einer der Luftzirkulationsleitungen (24a, 24b, 24c) verbinden, gegenüber den hohlen Verteilungsstegen (32), welche den Zufuhrkanal (28) mit wenigstens einer der anderen Luftzirkulationsleitungen (24a, 24b, 24c) verbinden, winkelmäßig versetzt sind.
  8. Vorrichtung nach irgendeinem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die hohlen Verteilungsstege (32), welche den Zufuhrkanal (28) mit einer der Luftzirkulationsleitungen (24a, 24b, 24c) verbinden, gegenüber den hohlen Verteilungsstegen (32), welche den Zufuhrkanal (28) mit den anderen Luftzirkulationsleitungen (24a, 24b, 24c) verbinden, winkelmäßig ausgerichtet sind.
  9. Vorrichtung nach irgendeinem der Ansprüche 1 bis 8, dadurch gekennzeichnet, daß der Winkelabstand zwischen zwei aufeinanderfolgenden hohlen Verteilungsstegen (32) etwa 45° nicht übersteigt.
EP04291818A 2003-08-06 2004-07-16 Vorrichtung für die Regelung von Spalten in einer Gasturbine Active EP1505261B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0309686A FR2858652B1 (fr) 2003-08-06 2003-08-06 Dispositif de controle de jeu dans une turbine a gaz
FR0309686 2003-08-06

Publications (2)

Publication Number Publication Date
EP1505261A1 EP1505261A1 (de) 2005-02-09
EP1505261B1 true EP1505261B1 (de) 2008-02-20

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US (1) US7114914B2 (de)
EP (1) EP1505261B1 (de)
JP (1) JP4185476B2 (de)
CA (1) CA2475081C (de)
DE (1) DE602004011859T2 (de)
ES (1) ES2300722T3 (de)
FR (1) FR2858652B1 (de)
RU (1) RU2290515C2 (de)
UA (1) UA83188C2 (de)

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US10513944B2 (en) * 2015-12-21 2019-12-24 General Electric Company Manifold for use in a clearance control system and method of manufacturing
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US20050042080A1 (en) 2005-02-24
UA83188C2 (uk) 2008-06-25
JP2005054777A (ja) 2005-03-03
RU2004122668A (ru) 2006-01-27
ES2300722T3 (es) 2008-06-16
FR2858652B1 (fr) 2006-02-10
US7114914B2 (en) 2006-10-03
DE602004011859D1 (de) 2008-04-03
FR2858652A1 (fr) 2005-02-11
JP4185476B2 (ja) 2008-11-26
EP1505261A1 (de) 2005-02-09
RU2290515C2 (ru) 2006-12-27
CA2475081A1 (fr) 2005-02-06
CA2475081C (fr) 2011-09-13
DE602004011859T2 (de) 2009-02-12

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