EP1577502B1 - Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern - Google Patents

Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern Download PDF

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Publication number
EP1577502B1
EP1577502B1 EP04293170A EP04293170A EP1577502B1 EP 1577502 B1 EP1577502 B1 EP 1577502B1 EP 04293170 A EP04293170 A EP 04293170A EP 04293170 A EP04293170 A EP 04293170A EP 1577502 B1 EP1577502 B1 EP 1577502B1
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EP
European Patent Office
Prior art keywords
air
diaphragm
flow
turbine
air flow
Prior art date
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EP04293170A
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English (en)
French (fr)
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EP1577502A1 (de
Inventor
Denis Amiot
Anne-Marie Arraitz
Thierry Fachat
Alain Gendraud
Delphine Roussin
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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SNECMA SAS
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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 game control at the top of moving blades of a gas turbine. It is more particularly a device for controlling a turbomachine high-pressure turbine equipped with means for balancing the air flow rates.
  • a gas turbine such as a high-pressure turbomachine turbine, comprises a plurality of blades arranged in the passage of hot gases from a combustion chamber.
  • the blades of the turbine are surrounded, around the entire circumference of the turbine, by an annular stator. This stator defines one of the walls of the flow passage of the hot gases through the turbine.
  • game-steering means at the top of the blades have been developed.
  • Such means are generally in the form of annular conduits which surround the stator and which are traversed by air taken from other parts of the turbomachine.
  • the air is injected on the outer surface of the stator in order to modify the temperature thereof and thus causes thermal expansion or contraction of the casing which are able to vary its diameter.
  • EP 1 205 637 describes a control device according to the preamble of claim 1.
  • the present invention therefore aims at overcoming such drawbacks by proposing a device for controlling blade clearance at the top of a gas turbine which makes it possible to balance the flow rates of air in the device. control to limit the thermal heterogeneities of the stator of the turbine.
  • the subject of the invention is a device for controlling the clearance of the blades of a gas turbine rotor according to claim 1.
  • the balancing of the air flow through the air duct thus makes it possible to limit the thermal heterogeneities at the level of the casing of the turbine. Indeed, it is possible to determine the pressure losses (at the supply of the air circulation ramp or ramps) to balance the air flow rates, and thus the characteristics of the diaphragm.
  • Each diaphragm is advantageously disposed at an inlet of the air duct so as to create additional pressure drops. It may be in the form of a ring of internal diameter smaller than the internal diameter of the air duct.
  • the figures 1 and 2 illustrate a control device 10 according to the invention.
  • a control device 10 can be applied to any gas turbine whose game control at the top of the blades is necessary.
  • This device is particularly applicable to a high-pressure turbomachine turbine.
  • control device 10 is mounted on an annular casing 12 forming part of the stator of the turbine.
  • This housing 12 of longitudinal axis X-X surrounds a plurality of blades (not shown) forming the rotor of the turbine.
  • control device 10 The function of the control device 10 is to control the clearance that exists between the top of the blades of the turbine and the parts of the stator that face them.
  • the blades of the turbine are surrounded by a plurality of ring segments (not shown) which are mounted on the housing 12 via spacers (not shown).
  • the stator parts that face the top of the blades are thus formed by the inner surface of the ring segments.
  • the control device 10 figures 1 and 2 consists of three air circulation ramps 14; an internal ramp 14a, a central ramp 14b and an outer ramp 14c. These ramps are mounted circumferentially on the outer surface of the casing 12 by means of fastening rules 16.
  • the air circulation ramps 14 are spaced axially from each other and are substantially parallel to each other. They are disposed on either side of two annular fins (or bosses) 18 which extend radially outwardly of the housing 12.
  • the ramps 14 are provided with a plurality of bores 19 arranged facing the external surface of the casing 12 and the fins 18. These bores 19 allow the air circulating in the ramps 14 to be discharged on the casing 12 in order to change the temperature.
  • the air circulation ramps 14 can be segmented into several angular sectors of distinct ramps (six in number on the figure 1 ) and regularly distributed over the entire circumference of the housing 12.
  • the control device 10 further comprises two air collection tubes 20 which surround at least part of the air circulation ramps 14.
  • the air collection tubes 20 are intended to supply air to the air circulation ramps 14.
  • Each air collection tube 20 is supplied with air by at least one air supply tube 22.
  • the air supply tube 22 is connected to zones of the turbomachine in which air can be drawn to supply the piloting device 10.
  • the air sampling zones may be one or more stages of a compressor of the turbomachine.
  • the sampling of air in the areas of the turbomachine provided for this purpose can be regulated by a control valve (not shown) interposed between these air sampling zones and the air supply tube 22.
  • a control valve (not shown) interposed between these air sampling zones and the air supply tube 22.
  • Such a valve allows to control the control device 10 according to the operating speed of the turbine.
  • the control device 10 further comprises three air ducts 24 opening in the air collection tube 20 and opening into the air circulation ramps 14 to supply them with air.
  • An air duct 24 is provided for each angular sector of air circulation ramps 14, that is to say that the piloting device comprises six air ducts 24 regularly distributed over the entire circumference of the casing 12.
  • each air collection tube 20 extends circumferentially about one half of a circle and thus feeds three air ducts 24. distinguishes these three air ducts 24 by naming them respectively: first air duct 24a for the duct which is closest to the air supply tube 22, second air duct 24b for the duct placed directly downstream of the first pipe 24a, and third air pipe 24c for the pipe farthest from the air supply tube 22.
  • Each air duct 24 is in the form of a cylinder, for example a metal cylinder, having edges 26 which engage in lateral openings 28 of the air circulation ramps 14. The air ducts 24 are thus welded to the ramps 14.
  • each air duct 24 is provided with means for balancing the air flow therethrough.
  • Such means are in the form of a diaphragm 30 disposed at the inlet of the air duct 24, that is to say upstream of the air circulation ramps 14 with respect to the direction of flow of the air. the air coming from the air collection tube 20. More particularly, the diaphragm 30 is placed upstream of the internal ramp 14a.
  • each air duct 24a, 24b and 24c makes it possible to balance the flow rates of air coming from the air collection tube 20 and supplying the air circulation ramps 14 into which the duct opens. air.
  • the diaphragm 30 is in the form of a ring (or washer) metal which is for example welded to the inner walls of the air duct 24 and whose internal diameter d1 representing the air flow section is lower the internal diameter d2 of the air duct 24.
  • the characteristics of the diaphragm 30 for balancing air flows are determined in order to generate additional head losses at the inlet. of each air duct 24 fed by it. Indeed, since the pressure drops are not identical for each air duct 24 fed by the same manifold tube 20, the characteristics of the diaphragms 30 are modeled to generate additional head losses at the inlet of each air duct 24 to obtain a balance in the distribution of air flow.
  • Table I below gives, for a control device of the prior art (that is to say devoid of air flow balancing means), the distribution of the air flow rates in the three ducts of FIG. air 24a, 24b, 24c supplied by the same air collection tube 20 and in each air circulation ramp 14 of the same ramp sector supplied by each of these air ducts. These air flows were modeled for a cruising operating speed of a turbomachine whose high-pressure turbine is equipped with a game control device.
  • the results of the ventilation show a heterogeneity in the distribution of air flows, on the one hand at the entrance of each air duct 24a, 24b and 24c (which reaches 6% ), and on the other hand between each sector of air circulation ramps (which reaches 5.8%).
  • the third air duct 24c has an air supply pressure higher than the other two ducts 24a, 24b because of the decrease in the air flow rate in the collector tube air. It results from the heterogeneity of the air flow rates between each air duct that the cooling of the casing 12 is not homogeneous. Temperature gradients may therefore appear and cause mechanical distortions.
  • the diameter d1 of the diaphragm 30 to be put in place at the inlet of the second air duct 24b is then of the order of 28.4 mm for a diameter d2 of the air duct 24b of the order of 39.8 mm.
  • each diaphragm 30 put in place in each air duct 24 which are thus determined from the modeling of additional head losses to be generated are individualized for each air duct.
  • the results of the setting up of such diaphragms are expressed in Table II below. II) - Flow in the first air line 24a (g / s) 32.59 Flow in the internal ramp 14a (g / s) 4.14 Flow in the central ramp 14b (g / s) 7.82 Flow in the external ramp 14c (g / s) 4.37 - Flow in the second air line 24b (g / s) 32.67 Flow in the internal ramp 14a (g / s) 4.12 Flow in the central ramp 14b (g / s) 7.78 Flow in the external ramp 14c (g / s) 4.35 - Flow in the third air line 24c (g / s) 32.52 Flow in the internal ramp 14a (g / s) 4.13 Flow in the central ramp 14b
  • airflow balancing can be done individually for each airflow ramp sector 14 by adjusting the diaphragm section as needed for a particular boom section.
  • Each air duct 24 can thus be provided with a diaphragm 30 whose characteristics (air flow section) are different for one sector of ramps to another.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (4)

  1. Vorrichtung zur Steuerung des Spiels an der Spitze von Laufschaufeln eines Gasturbinenrotors, umfassend:
    drei ringförmige Luftzirkulationsleitungen (14), die umfangseitig an einem ringförmigen Gehäuse (12) eines Stators der Turbine angebracht und dazu bestimmt sind, Luft auf das Gehäuse (12) zu entladen, um dessen Temperatur zu verändern;
    wenigstens ein Luftsammelrohr (20), das wenigstens teilweise um die Luftzirkuiationsteitungen (14) angeordnet ist;
    wenigstens ein Luftzufuhrrohr (22), um das Luftsammefrohr (20) mit Luft zu versorgen; und
    wenigstens eine Luftleitung (24), die sich in das Luftsammelrohr (20) öffnet und in die Luftzirkulationsleitungen (14) mündet,
    dadurch gekennzeichnet, daß sie zwei Luftsammelrohre (20) aufweist, die jeweils mit drei Luftleitungen (24) verbunden sind, welche jeweils in die drei Luftzirkulationsleitungen (14) münden, wobei jede Luftleitung (24) mit einer Drossel (30) zum Ausgleichen der sie durchströmenden Luftmenge ausgestattet ist, wobei die Merkmale einer jeden Drossel in Abhängigkeit der Luftleitung (24), in der die Drossel angeordnet ist, individualisiert sind.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, daß jede Drossel (30) im Bereich eines Eingangs der Luftleitung (24) angeordnet ist, so daß zusätzliche Druckverluste erzeugt werden.
  3. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, daß jede Drossel (30) in Form eines Rings vorliegt, dessen Innendurchmesser (d1) geringer ist als der Innendurchmesser (d2) der Luftleitung (24).
  4. Turbomaschine, die wenigstens eine Vorrichtung zur Steuerung des Spiels an der Spitze von Laufschaufeln eines Rotors nach irgendeinem der Ansprüche 1 bis 3 umfaßt.
EP04293170A 2004-03-18 2004-12-30 Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern Active EP1577502B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0402826A FR2867806B1 (fr) 2004-03-18 2004-03-18 Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air
FR0402826 2004-03-18

Publications (2)

Publication Number Publication Date
EP1577502A1 EP1577502A1 (de) 2005-09-21
EP1577502B1 true EP1577502B1 (de) 2008-07-16

Family

ID=34834196

Family Applications (1)

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EP04293170A Active EP1577502B1 (de) 2004-03-18 2004-12-30 Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern

Country Status (9)

Country Link
US (1) US7309209B2 (de)
EP (1) EP1577502B1 (de)
JP (1) JP4538347B2 (de)
CA (1) CA2500491C (de)
DE (1) DE602004015063D1 (de)
ES (1) ES2310706T3 (de)
FR (1) FR2867806B1 (de)
RU (1) RU2379522C2 (de)
UA (1) UA91667C2 (de)

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US8152446B2 (en) * 2007-08-23 2012-04-10 General Electric Company Apparatus and method for reducing eccentricity and out-of-roundness in turbines
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US7885070B2 (en) 2008-10-23 2011-02-08 International Business Machines Corporation Apparatus and method for immersion-cooling of an electronic system utilizing coolant jet impingement and coolant wash flow
US7961475B2 (en) 2008-10-23 2011-06-14 International Business Machines Corporation Apparatus and method for facilitating immersion-cooling of an electronic subsystem
US7916483B2 (en) 2008-10-23 2011-03-29 International Business Machines Corporation Open flow cold plate for liquid cooled electronic packages
US7983040B2 (en) 2008-10-23 2011-07-19 International Business Machines Corporation Apparatus and method for facilitating pumped immersion-cooling of an electronic subsystem
US7944694B2 (en) * 2008-10-23 2011-05-17 International Business Machines Corporation Liquid cooling apparatus and method for cooling blades of an electronic system chassis
US8123406B2 (en) * 2008-11-10 2012-02-28 General Electric Company Externally adjustable impingement cooling manifold mount and thermocouple housing
GB2469490B (en) * 2009-04-16 2012-03-07 Rolls Royce Plc Turbine casing cooling
US8322154B2 (en) * 2009-09-09 2012-12-04 International Business Machines Corporation Control of system coolant to facilitate two-phase heat transfer in a multi-evaporator cooling system
US8208258B2 (en) * 2009-09-09 2012-06-26 International Business Machines Corporation System and method for facilitating parallel cooling of liquid-cooled electronics racks
US20110058637A1 (en) * 2009-09-09 2011-03-10 International Business Machines Corporation Pressure control unit and method facilitating single-phase heat transfer in a cooling system
US20110056675A1 (en) 2009-09-09 2011-03-10 International Business Machines Corporation Apparatus and method for adjusting coolant flow resistance through liquid-cooled electronics rack(s)
US8583290B2 (en) * 2009-09-09 2013-11-12 International Business Machines Corporation Cooling system and method minimizing power consumption in cooling liquid-cooled electronics racks
US8351206B2 (en) 2010-06-29 2013-01-08 International Business Machines Corporation Liquid-cooled electronics rack with immersion-cooled electronic subsystems and vertically-mounted, vapor-condensing unit
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US8184436B2 (en) 2010-06-29 2012-05-22 International Business Machines Corporation Liquid-cooled electronics rack with immersion-cooled electronic subsystems
US8369091B2 (en) 2010-06-29 2013-02-05 International Business Machines Corporation Interleaved, immersion-cooling apparatus and method for an electronic subsystem of an electronics rack
US8179677B2 (en) 2010-06-29 2012-05-15 International Business Machines Corporation Immersion-cooling apparatus and method for an electronic subsystem of an electronics rack
US8248801B2 (en) 2010-07-28 2012-08-21 International Business Machines Corporation Thermoelectric-enhanced, liquid-cooling apparatus and method for facilitating dissipation of heat
US8472182B2 (en) 2010-07-28 2013-06-25 International Business Machines Corporation Apparatus and method for facilitating dissipation of heat from a liquid-cooled electronics rack
US8967951B2 (en) 2012-01-10 2015-03-03 General Electric Company Turbine assembly and method for supporting turbine components
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WO2014137577A1 (en) * 2013-03-08 2014-09-12 United Technologies Corporation Ring-shaped compliant support
WO2015122992A1 (en) 2014-02-13 2015-08-20 United Technologies Corporation Nacelle ventilation manifold
US9869196B2 (en) * 2014-06-24 2018-01-16 General Electric Company Gas turbine engine spring mounted manifold
US10513944B2 (en) * 2015-12-21 2019-12-24 General Electric Company Manifold for use in a clearance control system and method of manufacturing
US10329941B2 (en) * 2016-05-06 2019-06-25 United Technologies Corporation Impingement manifold
FR3058459B1 (fr) 2016-11-04 2018-11-09 Safran Aircraft Engines Dispositif de refroidissement pour une turbine d'une turbomachine
FR3079874B1 (fr) * 2018-04-09 2020-03-13 Safran Aircraft Engines Dispositif de refroidissement pour une turbine d'une turbomachine
FR3081911B1 (fr) * 2018-06-04 2021-05-28 Safran Aircraft Engines Dispositif de refroidissement d'un carter de turbine pour turbomachine
FR3089545B1 (fr) 2018-12-07 2021-01-29 Safran Aircraft Engines Dispositif de refroidissement d’un carter de turbine pour une turbomachine
FR3096071B1 (fr) 2019-05-16 2022-08-26 Safran Aircraft Engines Contrôle de jeu entre des aubes de rotor d’aéronef et un carter
CN113882954A (zh) * 2021-09-17 2022-01-04 北京动力机械研究所 一种低流阻分流装置
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FR2816352B1 (fr) * 2000-11-09 2003-01-31 Snecma Moteurs Ensemble de ventilation d'un anneau de stator

Also Published As

Publication number Publication date
UA91667C2 (ru) 2010-08-25
DE602004015063D1 (de) 2008-08-28
FR2867806A1 (fr) 2005-09-23
US7309209B2 (en) 2007-12-18
RU2379522C2 (ru) 2010-01-20
RU2005106889A (ru) 2006-08-20
JP2005264936A (ja) 2005-09-29
ES2310706T3 (es) 2009-01-16
US20070264120A1 (en) 2007-11-15
CA2500491A1 (fr) 2005-09-18
EP1577502A1 (de) 2005-09-21
JP4538347B2 (ja) 2010-09-08
FR2867806B1 (fr) 2006-06-02
CA2500491C (fr) 2012-11-13

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