EP1577502A1 - 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
EP1577502A1
EP1577502A1 EP04293170A EP04293170A EP1577502A1 EP 1577502 A1 EP1577502 A1 EP 1577502A1 EP 04293170 A EP04293170 A EP 04293170A EP 04293170 A EP04293170 A EP 04293170A EP 1577502 A1 EP1577502 A1 EP 1577502A1
Authority
EP
European Patent Office
Prior art keywords
air
diaphragm
flow
air duct
ramps
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.)
Granted
Application number
EP04293170A
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English (en)
French (fr)
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EP1577502B1 (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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Publication date
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Publication of EP1577502A1 publication Critical patent/EP1577502A1/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 piloting play at the top of moving blades of a gas turbine. She aims more particularly a device for driving a high-pressure turbine turbomachine equipped with balancing means of air flow.
  • a gas turbine such as a high-pressure turbine turbomachine, comprises a plurality of blades arranged in the passage of hot gases from a combustion chamber.
  • the blades the turbine are surrounded, all around the circumference of the turbine, by an annular stator. This stator defines one of the walls of the vein of flow of hot gases through the turbine.
  • Such means are generally in the form of annular conduits which surround the stator and which are traveled by air taken from other parts of the turbomachine. Depending on the operating speed of the turbine, the air is injected onto the outer surface of the stator to change the temperature and causes thermal dilations or contractions of the casing which are able to vary its diameter.
  • the present invention therefore aims to overcome such drawbacks by proposing a game steering device at the top of the blades of a gas turbine for balancing the air flows in the device of control in order to limit the thermal heterogeneities of the stator of the turbine.
  • the subject of the invention is a control device for blade clearance of a gas turbine rotor, having at least one annular ramp of air circulation mounted circumferentially on an annular casing of a stator of the turbine and intended to discharge air to the casing in order to modify the temperature, an air collection tube arranged at least partly around the at least one air circulation ramp, at least one supply tube air to supply air to the air collection pipe, and at least one pipe air opening in the air collection tube and opening into the air circulation ramps, characterized in that the air duct is provided with means for balancing the air flow therethrough.
  • the means for balancing the air flow crossing the air duct consist of a diaphragm arranged by example at the entrance of the air duct.
  • Balancing the air flow through the air duct allows thus to limit thermal heterogeneities at the crankcase of the turbine. Indeed, it is possible to determine the losses of level of the supply of the air circulation ramp or ramps) for to balance the air flows, and thus the characteristics of the diaphragm.
  • the diaphragm is advantageously disposed at a inlet of the air duct so as to create pressure losses additional. It can be in the form of a ring of internal diameter smaller than the internal diameter of the air duct.
  • each air duct is advantageously provided with a balancing diaphragm of the flow of air passing through it.
  • characteristics of each diaphragm preferably are individualized depending on the air duct in which the diaphragm is placed.
  • FIGS. 1 and 2 illustrate a control device 10 according to the invention.
  • a control device 10 can be applied to any turbine to gas whose game control at the top of the blades is necessary.
  • This device is particularly applicable to a high-pressure turbine turbomachine.
  • control device 10 is mounted on a annular housing 12 forming part of the stator of the turbine.
  • This housing 12 longitudinal axis X-X surrounds a plurality of moving blades (no shown) forming the rotor of the turbine.
  • the control device 10 has the function of controlling the game between the top of the blades of the turbine and the parts of the stator facing them.
  • the blades of the turbine are surrounded by a plurality ring segments (not shown) which are mounted on the housing 12 via spacers (not shown).
  • the parts of the stator which face the top of the blades are thus formed by the inner surface of the ring segments.
  • the driving device 10 of FIGS. 1 and 2 consists of three air circulation ramps 14; an internal ramp 14a, a ramp central 14b and an external ramp 14c. These ramps are mounted circumferentially on the outer surface of the housing 12 by through fastening rules 16. A single traffic ramp air could also be considered.
  • the air circulation ramps 14 are spaced axially each other and are substantially parallel to each other. They are arranged on either side of two annular fins (or humps) 18 which extend radially outwardly of the housing 12.
  • Ramps 14 are provided with a plurality of holes 19 disposed opposite the outer surface of the housing 12 and the fins 18. These holes 19 allow the air circulating in the ramps 14 to unload on the housing 12 to change the temperature.
  • the ramps air circulation 14 can be segmented into several sectors angular ramps (six in Figure 1) and regularly distributed over the entire circumference of the housing 12.
  • the control device 10 further comprises at least one air collection tube 20 which at least partially surrounds the ramps of air circulation 14.
  • at least one air collection tube 20 which at least partially surrounds the ramps of air circulation 14.
  • two air collection tubes are provided 20.
  • the air collection tube or 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 an air supply tube 22.
  • the air supply tube 22 is connected to areas of the turbomachine in which air can be taken to supply the control device 10.
  • the zones of air intake can be one or more stages of a compressor of the turbomachine.
  • Air sampling in the areas of the turbomachine provided for this purpose can be regulated by a control valve (no shown) interposed between these air sampling zones and the tube 22.
  • a control valve no shown
  • Such a valve makes it possible to control the control device 10 according to the operating regime of the turbine.
  • the control device 10 further comprises at least one air duct 24 opening into the air collection tube 20 and opening in the air circulation ramps 14 to supply them with air.
  • each air collection tube 20 extends circumferentially on approximately 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 tube supply air 22, second air line 24b for driving placed directly downstream of the first pipe 24a, and third air line 24c for the pipe farthest from the feed tube in air 22.
  • Each air duct 24 is in a form of a cylinder, for example metallic, having edges 26 that come engage in lateral openings 28 of the air circulation ramps 14. The air ducts 24 are thus welded to the ramps 14.
  • At least one of the air ducts 24 is provided with means for balancing the air flow therethrough.
  • Such means are advantageously in the form 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 flow of air from the air collection tube 20. More particularly, the diaphragm 30 is placed upstream of the ramp internal 14a.
  • this diaphragm 30 in at least one of the air ducts 24, and preferably in each air duct 24a, 24b and 24c, makes it possible to balance the flow rates of air coming from the collecting tube 20 and supplying the air circulation ramps 14 in which open the air line.
  • the diaphragm 30 is in the form of a metal ring (or washer) which is, for example, welded to the internal walls of the air duct 24 and whose internal diameter d1 represents the flow section of air is lower than 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 losses 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 duct. 24 air 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 breakdown highlight a heterogeneity in the distribution of airflows, on the one hand at the inlet 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 line 24c has a pressure supply air superior to the other two lines 24a, 24b because the decrease of the flow velocity of the air in the collecting tube air. It results from the heterogeneity of the air flows between each pipe of air that the cooling of the housing 12 is not homogeneous. of the temperature gradients can therefore appear and lead to 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
  • balancing of airflows can be carried out individually for each sector of ramps air circulation 14 by adapting the diaphragm section according to the needs for a particular boom section.
  • Each air line 24 can thus be provided with a diaphragm 30 whose characteristics (air debiting section) are different for a sector of ramps to one other.

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

Family

ID=34834196

Family Applications (1)

Application Number Title Priority Date Filing Date
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)

Cited By (1)

* Cited by examiner, † Cited by third party
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EP1798381A3 (de) * 2005-12-16 2008-02-27 General Electric Company Thermische Kontrolle von Turbinenringen zur aktiven Spaltregelung bei Gasturbinen

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US7503179B2 (en) * 2005-12-16 2009-03-17 General Electric Company System and method to exhaust spent cooling air of gas turbine engine active clearance control
US7914254B2 (en) * 2007-02-13 2011-03-29 General Electric Company Integrated support/thermocouple housing for impingement cooling manifolds and cooling method
US8152446B2 (en) * 2007-08-23 2012-04-10 General Electric Company Apparatus and method for reducing eccentricity and out-of-roundness in turbines
US8616827B2 (en) * 2008-02-20 2013-12-31 Rolls-Royce Corporation Turbine blade tip clearance system
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
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
US7983040B2 (en) 2008-10-23 2011-07-19 International Business Machines Corporation Apparatus and method for facilitating pumped 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
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
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
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
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
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)
US8345423B2 (en) 2010-06-29 2013-01-01 International Business Machines Corporation Interleaved, immersion-cooling apparatuses and methods for cooling electronic subsystems
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
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
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
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
US8248801B2 (en) 2010-07-28 2012-08-21 International Business Machines Corporation Thermoelectric-enhanced, liquid-cooling apparatus and method for facilitating dissipation of heat
US8967951B2 (en) 2012-01-10 2015-03-03 General Electric Company Turbine assembly and method for supporting turbine components
US9341074B2 (en) 2012-07-25 2016-05-17 General Electric Company Active clearance control manifold system
WO2014137577A1 (en) * 2013-03-08 2014-09-12 United Technologies Corporation Ring-shaped compliant support
EP3105438B1 (de) 2014-02-13 2018-11-21 United Technologies Corporation Lüftungsverteiler für triebwerksgondel
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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
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
US11788425B2 (en) * 2021-11-05 2023-10-17 General Electric Company Gas turbine engine with clearance control system

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Publication number Priority date Publication date Assignee Title
FR2652858A1 (fr) * 1989-10-11 1991-04-12 Snecma Stator de turbomachine associe a des moyens de deformation.
US5100291A (en) * 1990-03-28 1992-03-31 General Electric Company Impingement manifold
EP0492865A1 (de) * 1990-12-21 1992-07-01 General Electric Company Regelungssystem für das Schaufelspitzenspiel einer Turbine
EP0541325A1 (de) * 1991-11-04 1993-05-12 General Electric Company Thermische Steuerung eines Gehäuses eines Gasturbinentriebwerks
EP0892152A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP0892153A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP1205637A1 (de) * 2000-11-09 2002-05-15 Snecma Moteurs Kühlungsvorrichtung für einen Statorring

Family Cites Families (1)

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Publication number Priority date Publication date Assignee Title
FR2614073B1 (fr) * 1987-04-15 1992-02-14 Snecma Dispositif d'ajustement en temps reel du jeu radial entre un rotor et un stator de turbomachine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2652858A1 (fr) * 1989-10-11 1991-04-12 Snecma Stator de turbomachine associe a des moyens de deformation.
US5100291A (en) * 1990-03-28 1992-03-31 General Electric Company Impingement manifold
EP0492865A1 (de) * 1990-12-21 1992-07-01 General Electric Company Regelungssystem für das Schaufelspitzenspiel einer Turbine
EP0541325A1 (de) * 1991-11-04 1993-05-12 General Electric Company Thermische Steuerung eines Gehäuses eines Gasturbinentriebwerks
EP0892152A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP0892153A1 (de) * 1997-07-18 1999-01-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Heiz- b.z.w. Kühleinrichtung für ein Gehäuse mit kreisförmigem Querschnitt
EP1205637A1 (de) * 2000-11-09 2002-05-15 Snecma Moteurs Kühlungsvorrichtung für einen Statorring

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1798381A3 (de) * 2005-12-16 2008-02-27 General Electric Company Thermische Kontrolle von Turbinenringen zur aktiven Spaltregelung bei Gasturbinen

Also Published As

Publication number Publication date
CA2500491C (fr) 2012-11-13
RU2379522C2 (ru) 2010-01-20
RU2005106889A (ru) 2006-08-20
US20070264120A1 (en) 2007-11-15
UA91667C2 (ru) 2010-08-25
JP4538347B2 (ja) 2010-09-08
ES2310706T3 (es) 2009-01-16
JP2005264936A (ja) 2005-09-29
DE602004015063D1 (de) 2008-08-28
FR2867806A1 (fr) 2005-09-23
US7309209B2 (en) 2007-12-18
FR2867806B1 (fr) 2006-06-02
EP1577502B1 (de) 2008-07-16
CA2500491A1 (fr) 2005-09-18

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