EP0892152B1 - Dispositif de refroidissement ou d'échauffement d'un carter circulaire - Google Patents

Dispositif de refroidissement ou d'échauffement d'un carter circulaire Download PDF

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Publication number
EP0892152B1
EP0892152B1 EP98401800A EP98401800A EP0892152B1 EP 0892152 B1 EP0892152 B1 EP 0892152B1 EP 98401800 A EP98401800 A EP 98401800A EP 98401800 A EP98401800 A EP 98401800A EP 0892152 B1 EP0892152 B1 EP 0892152B1
Authority
EP
European Patent Office
Prior art keywords
tubes
networks
gas
manifolds
network
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
EP98401800A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0892152A1 (fr
Inventor
Jérôme Friedel
Jean-Luc Soupizon
Patrick Didier Michel Lestoille
Jean Bernard Vache
Christophe Schultz
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 Moteurs SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP0892152A1 publication Critical patent/EP0892152A1/fr
Application granted granted Critical
Publication of EP0892152B1 publication Critical patent/EP0892152B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular

Definitions

  • the invention relates to a device for crankcase cooling or heating circular.
  • a device already used consists of have two networks of semicircular tubes around of the casing, each of the networks therefore extending over a half circumference of the housing and being powered by a conduit, which is connected to a distributor box connected to each of the pipes in the network, in the middle of their length.
  • the gas therefore disperses in the tubes of the network by traversing them towards their ends at from the middle, and leaves them by borrowing orifices directed towards the housing.
  • This construction explains that these tubes are called "necklaces of shower ".
  • Such a device is described in document EP-A-541,325.
  • the known device Like the known device, it includes a gas distribution network in distributors connecting to networks of tubes surrounding the casing on respective parts of the circumferences; at place where a distributor is connected in the middle of tube networks, two distributors are arranged at ends of the networks, each of these two distributors connecting to a respective group of tubes of the considered network: the gas flows through the two groups of tubes in opposite directions, which balances heat gain around the circumference, each generator of the casing being subjected to a double gas blowing, the first of which originates from one of the network tube groups, is hotter as the other, from the other group, is fresher.
  • conduits opening into a pair of distributors are connected to a duct link occupying half of their section and extending to at least one of the sockets in passing through a stop surface of said socket.
  • This last duct slightly penetrates into the duct more distribution network, therefore recovers the half the bit rate that comes out and transmits that half of flow to the distributor located beyond the socket liaison; the other half of the gas flow comes out of distribution duct around the connecting duct and enters the other distributor.
  • the connecting duct having a section half as small as that of the duct distribution, to which it is connected with play, completes the system, the aim of which is to equalize heating or cooling.
  • a possible improvement consists in provide the device with a flow control valve heating or cooling gas, which is controlled by a calculator or by plan function reached by the machine.
  • a flow control valve heating or cooling gas which is controlled by a calculator or by plan function reached by the machine.
  • it is particularly advantageous to reduce the gas flow blown during start-up: if a large flow is delivered from this moment, while the machine is still cold, the housing heats up much more slowly as the rotor and its blades, whose ends expand to the point of rubbing against the inner wall of the housing.
  • This wall is normally filled with a layer of soft material, called abradable, which erodes under the effect of friction and prevents damage to the rotor blades, but play reappearing between them and the abradable layer now eroded is increased when the housing is heated and expanded in turn. It is therefore a question of avoiding this result.
  • abradable a layer of soft material
  • the device illustrated as a whole at Figure 1, has substantially the shape of a crown that we have to imagine placed around a housing cylindrical or conical shown elsewhere.
  • This crown consists essentially of three networks of tubes 1, identical and each extending over a third of the circumference of the housing thus forming an almost entirely continuous surface.
  • Each of the tube networks 1 includes six parallel tubes 2 and as an extension from one network to another and is completed by two distributor boxes 3 to which branch their tubes 2, which gives three pairs distributor boxes 3 adjacent to the limits of the three tube networks 1.
  • the housings distributors 3 and the tubes 2 are supplied with gas heating or cooling by a network of conduits first comprising a single conduit 4 which is splits into a first conduit 5 which goes towards a first pair of distributor boxes 3, at the top in the figure, and in a second conduit 6 which itself splits into two conduits, one of which extends over 7 the lower right of the figure and supplies a second pair of enclosures dispensers 3 at this location, while the other is not visible in the figure but extends behind one of the tube networks 1 to connect to the third pair of distributor boxes 3, also invisible but located behind the lower left of the Fig.
  • the ducts are chosen so that the three pairs of distributors 3 are supplied by equal gas flows at the same temperature: the lengths of conduit to travel to reach each pair of cases are all equal, the single duct 4 dividing at the junction of two networks of tubes 1, and the conduit 6 in the middle of one of these two networks of tubes 1; the conduit 5 extends over about a third of the circumference of the housing, and the duct 6 on a sixth in circumference, as well as the two conduits in which it splits.
  • Figure 2 shows that the tube networks 1 are composed of two corrugated sheets 8 returned and joined so that their corrugations 9 are opposite and come face to face to form the tubes 2.
  • the corrugated sheets 8 have flat portions 10 adjoining corrugations 9, in contact when the 8 sheets are assembled and riveted or united by a other way.
  • the tubes 2 are provided with orifices 11 directed to casing 12 to project gas there heating or cooling. This gas builds up in an annular chamber 13 delimited by the casing 12 and tube networks 1 but can escape from it by additional orifices 14 formed through of the adjoining portions 10.
  • Figure 3 shows that the gas distribution each lead into one of the distributor boxes 3 adjacent pairs mentioned above and their content is spreading first in this distributor box 3 before a half goes into the other distributor box 3 in passing through a cuff 17 which joins them.
  • the six tubes 2 of the networks of tubes 1 are alternately connected to one of the opposite 3 distributor boxes and located at the ends of these networks, so that the gas flows through three of tubes 2 in one direction and in the other three tubes 2 in the direction opposite: the gas heats up in tubes 2 as in the anterior device and therefore exits through the orifices 11 at increasing temperatures away from distributor boxes, but if we consider a generator of the casing 12, it receives gas from three tubes 2 having traveled a relatively long way and gas from three tubes 2 having traveled a path relatively short, i.e. both gas strongly heated and weakly heated gas and therefore a practically uniform quantity of heat: the object of the invention is thus achieved.
  • the housings distributors 3 have protrusions 18 to the exterior and in extension, and that the conduits feed such as 5 and 7 end up in the alignment of these protrusions 18 and penetrate into one of them.
  • the protrusions 18 each contain a socket 19 which partially delimits them, the sockets 19 being facing facing and connected by one of the cuffs 17; the cuff 17 is terminated by two spherical portions 20, open at their opposite ends 21 and which are able to roll and slide on the internal surface of sockets 19.
  • Tube networks 1 and sockets 19 can therefore move mutually without producing more than a rotation or a sliding movement of the cuff 17 in sockets 19, and without sealing and even less the connection between distributor boxes 3 is broken.
  • the cuff 17 must obviously be inserted sufficiently into the sockets 19 so that its extraction is impossible even if the networks of tubes 1 deviate; through elsewhere, the sockets 19 are provided with surfaces stop 22 which surround the cuff 17 and him prohibit moving indefinitely in the same direction, because it would come up against them.
  • the surfaces stop 22 include a central opening 23 for allow the entry of gas into the boxes distributors 3.
  • a connecting tube 24 is welded to one of these openings 23, and the other of the openings is free.
  • the connecting tube 24 is connected to the conduit power supply such as 5 occupying only the half of its section, which guarantees the passage of the half of the gas flow in the distributor box 3 opposite, on the left in the figure, by the connecting tube 24, while the other half of the flow stops against the sleeve 19 and is forced back into the tubes 2 of the distributor 3 on the right.
  • gas flow can be controlled by a progressive opening valve 25, controlled by a computer 26 depending on the speed reached, for adjust the gas flow rate supplied to the device and therefore the expansion undergone by the casing 12.
  • the computer 26 can be informed by speed sensors, temperature, pressure, etc. who measure quantities present in the machine, and it uses these measurements using empirically established tables or formulas.
  • We finally figured point 27 of sampling gas through the supply line 4 it's about usually from a point in the gas flow stream of the machine, from which part of the flow is withdrawn, in a manner widely known in the art.
  • the invention will especially find utility on turbomachine turbines, where the hotter gases that elsewhere make it more necessary.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Quick-Acting Or Multi-Walled Pipe Joints (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
  • Pipeline Systems (AREA)
EP98401800A 1997-07-18 1998-07-17 Dispositif de refroidissement ou d'échauffement d'un carter circulaire Expired - Lifetime EP0892152B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9709137 1997-07-18
FR9709137A FR2766232B1 (fr) 1997-07-18 1997-07-18 Dispositif de refroidissement ou d'echauffement d'un carter circulaire

Publications (2)

Publication Number Publication Date
EP0892152A1 EP0892152A1 (fr) 1999-01-20
EP0892152B1 true EP0892152B1 (fr) 2003-07-09

Family

ID=9509363

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98401800A Expired - Lifetime EP0892152B1 (fr) 1997-07-18 1998-07-17 Dispositif de refroidissement ou d'échauffement d'un carter circulaire

Country Status (12)

Country Link
US (1) US6149074A (ja)
EP (1) EP0892152B1 (ja)
JP (1) JP3474206B2 (ja)
KR (1) KR100545340B1 (ja)
CN (1) CN1199003C (ja)
CA (1) CA2266343A1 (ja)
DE (1) DE69816190T2 (ja)
ES (1) ES2205410T3 (ja)
FR (1) FR2766232B1 (ja)
RU (1) RU2210674C2 (ja)
UA (1) UA46126C2 (ja)
WO (1) WO1999004142A1 (ja)

Families Citing this family (50)

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EP1079068A3 (en) * 1999-08-27 2004-01-07 General Electric Company Connector tube for a turbine rotor cooling circuit
JP4274666B2 (ja) * 2000-03-07 2009-06-10 三菱重工業株式会社 ガスタービン
US6454529B1 (en) * 2001-03-23 2002-09-24 General Electric Company Methods and apparatus for maintaining rotor assembly tip clearances
FR2829176B1 (fr) * 2001-08-30 2005-06-24 Snecma Moteurs Carter de stator de turbomachine
FR2867806B1 (fr) * 2004-03-18 2006-06-02 Snecma Moteurs Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air
FR2867805A1 (fr) * 2004-03-18 2005-09-23 Snecma Moteurs Stator de turbine haute-pression de turbomachine et procede d'assemblage
DE102005035540A1 (de) * 2005-07-29 2007-02-01 Mtu Aero Engines Gmbh Vorrichtung zur aktiven Spaltkontrolle für eine Strömungsmaschine
US7597537B2 (en) * 2005-12-16 2009-10-06 General Electric Company Thermal control of gas turbine engine rings for active clearance control
KR100674118B1 (ko) * 2006-07-07 2007-01-24 (주)씨앤스페이스 로켓 추진용 메탄엔진
US8801370B2 (en) * 2006-10-12 2014-08-12 General Electric Company Turbine case impingement cooling for heavy duty gas turbines
US8393855B2 (en) * 2007-06-29 2013-03-12 General Electric Company Flange with axially curved impingement surface for gas turbine engine clearance control
US8197186B2 (en) * 2007-06-29 2012-06-12 General Electric Company Flange with axially extending holes for gas turbine engine clearance control
EP2112335A1 (de) * 2008-04-21 2009-10-28 Siemens Aktiengesellschaft Dampfturbine mit Kühlvorrichtung
FR2965010B1 (fr) * 2010-09-17 2015-02-20 Snecma Refroidissement de la paroi exterieure d'un carter de turbine
FR2977276B1 (fr) * 2011-06-30 2016-12-09 Snecma Agencement pour le raccordement d'un conduit a un boitier de distribution d'air
JP5609795B2 (ja) * 2011-07-12 2014-10-22 株式会社デンソー 車両用過給装置
US20130149107A1 (en) * 2011-12-08 2013-06-13 Mrinal Munshi Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow
US10094285B2 (en) * 2011-12-08 2018-10-09 Siemens Aktiengesellschaft Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity
US8894359B2 (en) * 2011-12-08 2014-11-25 Siemens Aktiengesellschaft Gas turbine engine with outer case ambient external cooling system
US9664062B2 (en) * 2011-12-08 2017-05-30 Siemens Energy, Inc. Gas turbine engine with multiple component exhaust diffuser operating in conjunction with an outer case ambient external cooling system
RU2495256C1 (ru) * 2012-04-12 2013-10-10 Николай Борисович Болотин Турбина газотурбинного двигателя
RU2499894C1 (ru) * 2012-05-11 2013-11-27 Николай Борисович Болотин Двухконтурный газотурбинный двигатель
RU2506435C2 (ru) * 2012-05-11 2014-02-10 Николай Борисович Болотин Газотурбинный двигатель и способ регулирования радиального зазора в турбине газотурбинного двигателя
RU2499145C1 (ru) * 2012-05-21 2013-11-20 Николай Борисович Болотин Турбина двухконтурного газотурбинного двигателя
RU2496991C1 (ru) * 2012-05-21 2013-10-27 Николай Борисович Болотин Турбина двухконтурного газотурбинного двигателя
ITTO20120519A1 (it) * 2012-06-14 2013-12-15 Avio Spa Turbina a gas per motori aeronautici
RU2501956C1 (ru) * 2012-07-31 2013-12-20 Николай Борисович Болотин Двухконтурный газотурбинный двигатель, способ регулирования радиального зазора в турбине двухконтурного газотурбинного двигателя
FR3002971B1 (fr) * 2013-03-06 2015-04-17 Snecma Dispositif de ventilation d'un carter de stator d'une turbomachine, comprenant un ajustement sur des circonferences
FR3002972B1 (fr) * 2013-03-06 2015-04-17 Snecma Dispositif de ventilation d'un carter de stator d'une turbomachine comprenant un ajustement en direction axiale
EP2789803A1 (en) * 2013-04-09 2014-10-15 Siemens Aktiengesellschaft Impingement ring element attachment and sealing
RU2519127C1 (ru) * 2013-04-24 2014-06-10 Николай Борисович Болотин Турбина газотурбинного двигателя и способ регулирования радиального зазора в турбине
EP2987966A1 (de) * 2014-08-21 2016-02-24 Siemens Aktiengesellschaft Gasturbine mit in Ringsektoren unterteiltem Kühlringkanal
US10378379B2 (en) * 2015-08-27 2019-08-13 General Electric Company Gas turbine engine cooling air manifolds with spoolies
FR3041037B1 (fr) * 2015-09-15 2018-08-17 Safran Aircraft Engines Dispositif de ventilation d'un carter de turbine d'une turbomachine
FR3050228B1 (fr) * 2016-04-18 2019-03-29 Safran Aircraft Engines Dispositif de refroidissement par jets d'air d'un carter de turbine
US10612409B2 (en) * 2016-08-18 2020-04-07 United Technologies Corporation Active clearance control collector to manifold insert
FR3058459B1 (fr) * 2016-11-04 2018-11-09 Safran Aircraft Engines Dispositif de refroidissement pour une turbine d'une turbomachine
FR3067751B1 (fr) * 2017-06-15 2019-07-12 Safran Aircraft Engines Dispositif de refroidissement d'un carter annulaire externe de turbine
US10914187B2 (en) * 2017-09-11 2021-02-09 Raytheon Technologies Corporation Active clearance control system and manifold for gas turbine engine
RU2673924C1 (ru) * 2017-10-17 2018-12-03 Акционерное общество "ОДК-Авиадвигатель" Статор газовой турбины
FR3073007B1 (fr) * 2017-10-27 2019-09-27 Safran Aircraft Engines Dispositif de maintien d'un tube de refroidissement pour carter de turbomachine
FR3082872B1 (fr) 2018-06-25 2021-06-04 Safran Aircraft Engines Dispositif de refroidissement d'un carter de turbomachine
FR3085719B1 (fr) * 2018-09-06 2021-04-16 Safran Aircraft Engines Boitier d'alimentation en air sous pression d'un dispositif de refroidissement par jets d'air
FR3089545B1 (fr) * 2018-12-07 2021-01-29 Safran Aircraft Engines Dispositif de refroidissement d’un carter de turbine pour une turbomachine
FR3096084B1 (fr) * 2019-05-16 2021-04-16 Safran Aircraft Engines Procédé et dispositif d’estimation d’une zone morte d’une vanne de décharge de turbomachine
FR3101104B1 (fr) * 2019-09-23 2021-09-03 Safran Aircraft Engines Dispositif de refroidissement par jets d’air d’un carter de turbine
US11560843B2 (en) 2020-02-25 2023-01-24 General Electric Company Frame for a heat engine
US11326519B2 (en) 2020-02-25 2022-05-10 General Electric Company Frame for a heat engine
US11255264B2 (en) 2020-02-25 2022-02-22 General Electric Company Frame for a heat engine
FR3112811B1 (fr) * 2020-07-23 2022-07-22 Safran Aircraft Engines Turbine à cavités pressurisées

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Also Published As

Publication number Publication date
DE69816190T2 (de) 2004-05-27
DE69816190D1 (de) 2003-08-14
FR2766232A1 (fr) 1999-01-22
CN1234847A (zh) 1999-11-10
CN1199003C (zh) 2005-04-27
JP3474206B2 (ja) 2003-12-08
KR100545340B1 (ko) 2006-01-24
FR2766232B1 (fr) 1999-08-20
CA2266343A1 (en) 1999-01-28
KR20000068582A (ko) 2000-11-25
US6149074A (en) 2000-11-21
ES2205410T3 (es) 2004-05-01
WO1999004142A1 (fr) 1999-01-28
EP0892152A1 (fr) 1999-01-20
JP2001500947A (ja) 2001-01-23
RU2210674C2 (ru) 2003-08-20
UA46126C2 (uk) 2002-05-15

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