EP1775427B1 - Dispositif de contrôle de jeu entre le sommet d'aube et un anneau fixe dans une turbine à gaz - Google Patents

Dispositif de contrôle de jeu entre le sommet d'aube et un anneau fixe dans une turbine à gaz Download PDF

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Publication number
EP1775427B1
EP1775427B1 EP06120571A EP06120571A EP1775427B1 EP 1775427 B1 EP1775427 B1 EP 1775427B1 EP 06120571 A EP06120571 A EP 06120571A EP 06120571 A EP06120571 A EP 06120571A EP 1775427 B1 EP1775427 B1 EP 1775427B1
Authority
EP
European Patent Office
Prior art keywords
casing
turbine
support
ring
wall
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
EP06120571A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1775427A1 (fr
Inventor
Franck Denece
Vincent Philippot
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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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1775427A1 publication Critical patent/EP1775427A1/fr
Application granted granted Critical
Publication of EP1775427B1 publication Critical patent/EP1775427B1/fr
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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
    • 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
    • F01D25/12—Cooling
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings

Definitions

  • the present invention relates to the general field of play control between the rotary blade tip and a fixed ring assembly in 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 circumferentially by a fixed ring assembly. This fixed ring assembly defines the flow path of the hot gases through the vanes of the turbine.
  • the document DE 2,556,519 discloses a turbine casing in which a ring is secured to an annular ring which surrounds the blades of the turbine.
  • a cylindrical structure placed between the housing and this ring has orifices that allow air to ventilate the outer face of the ring.
  • the present invention aims to overcome such drawbacks by proposing a turbine casing in which can be mounted a support for fixing a ring surrounding the blades of the turbine, the support having a circumferential wall surrounding the ring co-axially, the housing characterized in that it comprises a plurality of perforations for supplying air for evenly ventilating the outer face of the circumferential wall.
  • the turbine casing according to the invention thus makes it possible to homogenize the thermal field of the ring support, so that this support deforms in a homogeneous manner over its entire circumference, without any negative influence on the game at the top of the blades.
  • the perforations are made on an internal radial wall of the housing, this wall substantially closing a ventilation space, further defined by an inner face of the housing and the outer face of the circumferential wall of the support, this space having a reduced opening for the evacuation of the air.
  • the perforations are constituted by holes of the same size made regularly along a circumference of the internal radial wall of the housing.
  • the axis of these holes is inclined relative to the axis of the turbine with an angle advantageously allowing to animate the air with a gyration movement necessary and sufficient to ensure the desired thermal homogeneity, namely a angle in the range [30 °, 60 °].
  • this angle is chosen equal to 45 °.
  • the axis of the holes is horizontal in the longitudinal section plane of the turbine, so that the movement of air gyration does not directly impact the support.
  • the casing according to the invention thus makes it possible to improve the performance of the motor, to increase the lifetime of the ring support because of the lower thermal gradients and therefore the reduced mechanical stresses.
  • the invention also relates to a turbine as mentioned briefly above, and a turbine engine comprising such a turbine.
  • the figure 1 illustrates, in a half-view in longitudinal section, a turbomachine 100 according to the invention in a preferred embodiment.
  • This turbomachine 100 comprises, in known manner, a combustion chamber 110.
  • the turbomachine 100 Downstream of the combustion chamber 110, the turbomachine 100 comprises a turbine 120 according to the invention, the housing of which, according to the invention, has the reference 10.
  • This ring 30 is fixed on an annular support 20.
  • the ring 30 has a first circular groove 30a in its upstream part, adapted to receive a rail 21 for mounting the support 20.
  • the ring 30 In its downstream part, the ring 30 has a circumferential flat surface 31 against which an annular edge 23 of the support 20 bears. Substantially at the level of the first circular groove 30a, the ring 30 has, downstream, a second groove circular 30b substantially below the flat 31.
  • the support 20 is thus fixed to the ring 30, in its downstream part, by an annular holding piece 40 of the C-clip type arranged in the second groove 30b to clamp the annular edge 23 of the support 20 against the circumferential flat 31 of the ring 30.
  • any deformation of the support 20 causes, via the mounting rail 21 and the annular clamping piece 40, a deformation of the ring 30 thus modifying the clearance between the top of the blade 32 and the inner surface of this ring.
  • the support 20 comprises a circumferential wall 22 coaxially surrounding the ring 30, this circumferential wall ending, in its upstream part, with a radial annular flange 27 directed outwards.
  • this radial annular flange 27 allows, by bolting 11, the fixing of the support 20 to the casing 10.
  • the casing 10 has a radial wall 14 which is flush with a radial rib 28 of the support 20 thus defining a chamber 29 delimited by the inner face 10i of the casing 10 and the outer face. 22e of the circumferential wall 22.
  • the turbine casing 10 comprises a plurality of perforations 12 for supplying air to ventilate in a homogeneous manner the external face 22e of the circumferential wall 22.
  • these perforations 12 are made on the internal radial wall 14 of the casing, the air escaping from this ventilation chamber 29 through a reduced opening between the radial rib 28 of the support 20 and the inner face. 14i of the radial wall 14.
  • the air intended to ventilate the outer face 22e of the circumferential wall 22 is taken from a stage of a high-pressure compressor of the turbomachine 100, and conveyed by an inlet 130 made in downstream of the radial wall 14in the turbine casing 10.
  • the figure 2 represents in perspective, a partial view and cut away of the housing 10 of the figure 1 , in its environment.
  • This figure 2 corresponds to a preferred embodiment of the casing 10 according to the invention, in which the perforations 12 are constituted by holes of the same dimension made regularly along a circumference of the internal radial wall 14 of the casing 10.
  • this circumference has 22 holes 1.2 mm in diameter.
  • the figure 3 represents a AA cut of the assembly of the figure 1 .
  • this angle ⁇ is an angle of 30 ° which makes it possible to establish in the ventilation space 29 a flow of air established in gyration.

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)
EP06120571A 2005-09-23 2006-09-13 Dispositif de contrôle de jeu entre le sommet d'aube et un anneau fixe dans une turbine à gaz Active EP1775427B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0509749A FR2891300A1 (fr) 2005-09-23 2005-09-23 Dispositif de controle de jeu dans une turbine a gaz

Publications (2)

Publication Number Publication Date
EP1775427A1 EP1775427A1 (fr) 2007-04-18
EP1775427B1 true EP1775427B1 (fr) 2008-11-05

Family

ID=36600208

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06120571A Active EP1775427B1 (fr) 2005-09-23 2006-09-13 Dispositif de contrôle de jeu entre le sommet d'aube et un anneau fixe dans une turbine à gaz

Country Status (8)

Country Link
US (1) US7641442B2 (ru)
EP (1) EP1775427B1 (ru)
JP (1) JP4990586B2 (ru)
CN (1) CN1936279B (ru)
CA (1) CA2560227C (ru)
DE (1) DE602006003502D1 (ru)
FR (1) FR2891300A1 (ru)
RU (1) RU2435039C2 (ru)

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US7721433B2 (en) * 2005-03-28 2010-05-25 United Technologies Corporation Blade outer seal assembly
US20100260599A1 (en) * 2008-03-31 2010-10-14 Mitsubishi Heavy Industries, Ltd. Rotary machine
EP2184445A1 (de) * 2008-11-05 2010-05-12 Siemens Aktiengesellschaft Axial segmentierter Leitschaufelträger für einen Gasturbine
US20110103939A1 (en) * 2009-10-30 2011-05-05 General Electric Company Turbine rotor blade tip and shroud clearance control
FR2979662B1 (fr) * 2011-09-07 2013-09-27 Snecma Procede de fabrication d'un secteur de distributeur de turbine ou redresseur de compresseur en materiau composite pour turbomachine et turbine ou compresseur incorporant un distributeur ou un redresseur forme de tels secteurs
US9010127B2 (en) * 2012-03-02 2015-04-21 General Electric Company Transition piece aft frame assembly having a heat shield
RU2490474C1 (ru) * 2012-04-16 2013-08-20 Николай Борисович Болотин Турбина газотурбинного двигателя
RU2499892C1 (ru) * 2012-04-24 2013-11-27 Николай Борисович Болотин Турбина газотурбинного двигателя
RU2500894C1 (ru) * 2012-04-27 2013-12-10 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
RU2501956C1 (ru) * 2012-07-31 2013-12-20 Николай Борисович Болотин Двухконтурный газотурбинный двигатель, способ регулирования радиального зазора в турбине двухконтурного газотурбинного двигателя
RU2511860C1 (ru) * 2012-09-10 2014-04-10 Николай Борисович Болотин Двухконтурный газотурбинный двигатель и способ регулирования радиального зазора в турбине двухконтурного газотурбинного двигателя
US9091171B2 (en) * 2012-10-30 2015-07-28 Siemens Aktiengesellschaft Temperature control within a cavity of a turbine engine
US9752592B2 (en) * 2013-01-29 2017-09-05 Rolls-Royce Corporation Turbine shroud
EP2971577B1 (en) 2013-03-13 2018-08-29 Rolls-Royce Corporation Turbine shroud
RU2519127C1 (ru) * 2013-04-24 2014-06-10 Николай Борисович Болотин Турбина газотурбинного двигателя и способ регулирования радиального зазора в турбине
JP5889266B2 (ja) * 2013-11-14 2016-03-22 三菱重工業株式会社 タービン
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
JP6441611B2 (ja) * 2014-08-25 2018-12-19 三菱日立パワーシステムズ株式会社 ガスタービンの排気部材及び排気室メンテナンス方法
US10190434B2 (en) 2014-10-29 2019-01-29 Rolls-Royce North American Technologies Inc. Turbine shroud with locating inserts
CA2915246A1 (en) 2014-12-23 2016-06-23 Rolls-Royce Corporation Turbine shroud
CA2915370A1 (en) 2014-12-23 2016-06-23 Rolls-Royce Corporation Full hoop blade track with axially keyed features
EP3045674B1 (en) 2015-01-15 2018-11-21 Rolls-Royce Corporation Turbine shroud with tubular runner-locating inserts
US10215099B2 (en) * 2015-02-06 2019-02-26 United Technologies Corporation System and method for limiting movement of a retainer ring of a gas turbine engine
CA2925588A1 (en) 2015-04-29 2016-10-29 Rolls-Royce Corporation Brazed blade track for a gas turbine engine
CA2924855A1 (en) 2015-04-29 2016-10-29 Rolls-Royce Corporation Keystoned blade track
US10240476B2 (en) 2016-01-19 2019-03-26 Rolls-Royce North American Technologies Inc. Full hoop blade track with interstage cooling air
US10415415B2 (en) 2016-07-22 2019-09-17 Rolls-Royce North American Technologies Inc. Turbine shroud with forward case and full hoop blade track
US10287906B2 (en) 2016-05-24 2019-05-14 Rolls-Royce North American Technologies Inc. Turbine shroud with full hoop ceramic matrix composite blade track and seal system
FR3079874B1 (fr) * 2018-04-09 2020-03-13 Safran Aircraft Engines Dispositif de refroidissement pour une turbine d'une turbomachine
FR3099787B1 (fr) * 2019-08-05 2021-09-17 Safran Helicopter Engines Anneau pour une turbine de turbomachine ou de turbomoteur
US11174754B1 (en) * 2020-08-26 2021-11-16 Solar Turbines Incorporated Thermal bridge for connecting sections with a large temperature differential under high-pressure conditions

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BE756582A (fr) * 1969-10-02 1971-03-01 Gen Electric Ecran circulaire et support d'ecran avec dispositif de reglage de la temperature pour turbomachine
FR2280791A1 (fr) * 1974-07-31 1976-02-27 Snecma Perfectionnements au reglage du jeu entre les aubes et le stator d'une turbine
US3966354A (en) * 1974-12-19 1976-06-29 General Electric Company Thermal actuated valve for clearance control
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FR2548733B1 (fr) * 1983-07-07 1987-07-10 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine
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Also Published As

Publication number Publication date
US20070071598A1 (en) 2007-03-29
CA2560227A1 (fr) 2007-03-23
RU2006133869A (ru) 2008-04-27
EP1775427A1 (fr) 2007-04-18
DE602006003502D1 (de) 2008-12-18
RU2435039C2 (ru) 2011-11-27
CN1936279B (zh) 2011-06-29
US7641442B2 (en) 2010-01-05
JP2007085346A (ja) 2007-04-05
FR2891300A1 (fr) 2007-03-30
JP4990586B2 (ja) 2012-08-01
CN1936279A (zh) 2007-03-28
CA2560227C (fr) 2013-09-10

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