EP1555394B1 - Dispositif de contrôle de jeu dans une turbine à gaz - Google Patents

Dispositif de contrôle de jeu dans une turbine à gaz Download PDF

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Publication number
EP1555394B1
EP1555394B1 EP04292774A EP04292774A EP1555394B1 EP 1555394 B1 EP1555394 B1 EP 1555394B1 EP 04292774 A EP04292774 A EP 04292774A EP 04292774 A EP04292774 A EP 04292774A EP 1555394 B1 EP1555394 B1 EP 1555394B1
Authority
EP
European Patent Office
Prior art keywords
perforations
air
downstream
upstream
ridge
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
EP04292774A
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German (de)
English (en)
French (fr)
Other versions
EP1555394A1 (fr
Inventor
Denis Amiot
Anne-Marie Arraitz
Thierry Fachat
Alain Gendraud
Pascal Lefebvre
Delphine Roussin-Moynier
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 EP1555394A1 publication Critical patent/EP1555394A1/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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers

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 a wall of the hot gas flow vein through the blades 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 fixed ring assembly and thereby causes thermal expansion or contraction of the fixed ring assembly which is adapted to vary its diameter. Thermal expansions and contractions are controlled according to the operating speed of the turbine through a valve that controls the flow and 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.
  • Pilot boxes 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 temperature homogeneity causes distortions of the fixed ring assembly which are particularly detrimental to the efficiency and life of the gas turbine.
  • the injection of air on the outer surface of the fixed ring assembly is generally not optimized so that it is often necessary to take a large amount of air to ensure cooling of the fixed ring assembly. Too much air intake impairs the performance of the turbomachine.
  • the present invention therefore aims to overcome such drawbacks by providing a game control device that optimizes the injection of air to obtain a better efficiency and homogeneity of the cooling of the fixed ring assembly.
  • a device for controlling the clearance between a top of rotating blades and a stationary ring assembly of a gas turbine said fixed ring assembly comprising an annular housing having a longitudinal axis and provided with at least two annular fins axially spaced from one another and extending radially outwardly of the housing, the game control device comprising a circular control box surrounding the housing of the fixed ring assembly, the control unit comprising air circulation means formed of at least three annular ramps spaced axially from one another and arranged on either side of lateral faces of each of the fins, feed means air to supply air to the air circulation ramps, and air discharge means on the vanes to change the temperature of the fixed ring assembly, characterized in that the air discharge means is trained, for each airflow ramp, by at least one upper row of N bores arranged facing one of the lateral faces of the fins and by at least one row bottom of 2N holes arranged with respect to a connecting radius between the fins and the casing of the fixed ring assembly.
  • the distribution and positioning of the air discharge bores makes it possible to optimize the heat exchange coefficient between the fins and the flow of air passing through them. This provides a better efficiency and homogeneity of cooling fins, and thus a greater range of displacement of the housing to control the game at the top of the blades of the turbine.
  • the central ramp preferably comprises at least two upper rows of each N bores arranged facing side faces of the upstream and downstream fins, and at least two lower rows each of 2N holes arranged with respect to connection radii between the upstream and downstream fins and the casing of the fixed ring assembly.
  • the upstream and downstream ramps each have substantially identical air flow sections and the central ramp has an air flow section which is substantially twice as large as that of the upstream and downstream ramps.
  • the N bores of each upper row and the 2N bores of each lower row have substantially identical air flow sections.
  • the N bores of each upper row and the 2N bores of each lower row are arranged in staggered rows.
  • the figure 1 illustrates, in longitudinal section, a turbomachine high-pressure turbine 2 of longitudinal axis XX.
  • the present invention could also be applied to a turbomachine low-pressure turbine or to any other gas turbine equipped with a blade tip control device.
  • the high-pressure turbine 2 is composed in particular of a plurality of blades 4 arranged in a flow path 6 of hot gases 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 flow line 6.
  • the blades 4 of the high-pressure turbine 2 are surrounded by a plurality of ring segments 12 arranged circumferentially around the axis X-X of the turbine so as to form a circular and continuous surface.
  • the ring segments 12 are mounted on an annular casing 14, also of longitudinal axis X-X, through a plurality of spacers 16.
  • the assembly formed by the ring segments 12, the casing 14 and the spacers 16 will be referred to as the "fixed ring assembly”.
  • the casing 14 of the fixed ring assembly is provided with at least two annular fins or bosses 18, 20 which are axially spaced from one another and which extend radially outwardly of the casing 14. These two fins will differentiate with respect to the flow direction of the hot gases in the flow duct 6 by designating them by upstream fin 18 and downstream fin 20.
  • the main function of the upstream and downstream fins 18 is to act as heat exchangers.
  • the ring segments 12 each have an inner surface 12a which is in direct contact with the hot gases and which partly defines the flow channel 6 of the gases through the high-pressure turbine 2.
  • a radial clearance 22 is left between the inner surface 12a of the ring segments 12 and the top 4a of the blades 4 of the high-pressure turbine 2 to allow rotation of the latter. In order to increase the efficiency of the turbine, it is necessary to reduce this game as much as possible.
  • the game control device 24 comprises in particular a circular control box 26 surrounding the fixed ring assembly, and more precisely the casing 14.
  • control unit 26 is intended to cool or heat the upstream fins 18 and downstream 20 of the housing 14 by discharge (or impact) of air thereon. Under the effect of this air discharge, the housing 14 retracts or expands, which decreases or increases the diameter of the fixed ring segments 12 of the turbine to adjust the game 22 at the top of the blades.
  • the control unit 26 comprises in particular at least three annular air circulation ramps 28, 30 and 32 which surround the casing 14 of the fixed ring assembly. These ramps are spaced axially from one another and are substantially parallel to each other. They are arranged on either side of the lateral faces of each of the fins 18, 20 of which they conform approximately to the shape.
  • the air circulation ramps 28, 30 and 32 consist of an upstream ramp 28 which is arranged upstream of the upstream fin 18 (with respect to the direction of flow of the hot gases in the flow vein 6), a downstream ramp 30 which is arranged downstream of the downstream fin 20 and a central ramp which is disposed between the upstream fins 18 and downstream 20.
  • the control unit 26 also comprises an air collection tube (not shown in the figures) for supplying air to the air circulation ramps 28, 30 and 32.
  • This air collection tube surrounds the ramps 28, 30 and 32 and feeds air through air ducts (not shown in the figures).
  • each air circulation ramp 28, 30 and 32 of the control box 26 have at least one upper row of N bores 34 arranged facing one of the side faces of the fins 18, 20 and at least a lower row of 2N holes 36 arranged with respect to a connecting radius between the fins 18, 20 and the housing 14 of the fixed ring assembly.
  • the holes 34, 36 which are for example obtained by laser, can discharge the air flowing in the ramps 28, 30 and 32 on the fins 18, 20 to change the temperature.
  • the upstream ramp 28 comprises, on the side of its downstream wall 28b, at least one upper row of N bores 34 arranged with respect to the upstream side face 18a of the upstream fin 18 and at least one lower row of 2N bores 36 arranged with regard to a connection radius 18c between the upstream fin 18 and the casing 14 of the fixed ring assembly. No drilling is performed on the upstream wall 28a of the upstream ramp 28.
  • the downstream ramp 30 comprises, on the side of its upstream wall 30a, at least one upper row of N bores 34 arranged with respect to the downstream side face 20b of the downstream vane 20 and at least one lower row of 2N bores. 36 arranged with respect to a connecting radius 20d between the downstream fin 20 and the casing 14 of the fixed ring assembly. No drilling is performed on the downstream wall 30b of the downstream ramp 30.
  • the central ramp 32 comprises at least two upper rows of each N bores 34 arranged facing the side faces 18b, 20a of the upstream fins 18 and downstream 20, and at least two lower rows of each 2N holes 36 arranged with respect to connecting radii 18d, 20c between the upstream fins 18 and downstream 20 and the casing 14 of the fixed ring assembly.
  • the central ramp 32 comprises at least one upper row of N bores 34 arranged with respect to the downstream side face 18b of the upstream fin 18 and at least one lower row of 2N holes 36 arranged in relation to a radius of connection 18d between the upstream vane 18 and the casing 14 of the fixed ring assembly.
  • the central ramp 32 comprises at least one upper row of N bores 34 arranged facing the upstream side face 20a of the downstream vane 20 and at least one lower row of 2N bores 36 arranged in the view a connecting radius 20c between the downstream fin 20 and the casing 14 of the fixed ring assembly.
  • the air discharge bores 34, 36 are arranged in two rows, with two thirds of the bores on the lower row. and the remaining third on the top row.
  • the air issuing from the 2N bores 36 of each lower row "impacts" on the lower zone of the fins 18, 20, whereas the air discharged by the N bores 34 of each upper row impinges on a central zone of the fins.
  • the heat exchange obtained with fins is thus homogeneous and allows a greater range of movement of the housing to control the game at the top of the blades of the turbine. Calculations of thermal influences made it possible to show that such a configuration makes it possible to gain up to more than 50 ° C on the mean temperature of a fin compared to a single-row configuration of bores.
  • the upstream and downstream ramps 28 each have substantially identical air flow sections and the central ramp 32 has an air flow section which is substantially twice as large as that of the upstream ramps. 28 and downstream 30.
  • the central ramp 32 is advantageously pierced on both sides, the flow rate of air flowing in this ramp must be twice the flow of air flowing in the upstream ramps 28 and downstream 30.
  • the N bores 34 of each upper row and the 2N bores 36 of each lower row have, for each airflow ramp 28, 30 and 32, substantially identical airflow sections. .
  • the N bores 34 of each upper row and the 2N bores 36 of each lower row are staggered for each airflow ramp.
  • the bores 34 of each upper row and the bores 36 of each lower row are preferably regularly spaced around the longitudinal axis XX of the casing 14 of the casing. fixed ring assembly.
  • the angular spacing between two adjacent bores 34 of the same upper row advantageously corresponds to at least three times the diameter of the bores.
  • the choice of the number and the diameter of the air discharge bores 34, 36 can be optimized by modeling based on a compromise between efficient ventilation of the fins and the manufacturing constraints of the control box.
  • the diameter of each hole can be fixed at 1 mm and the spacing between two adjacent holes of an upper row may be 3.8 mm (which corresponds to 3.8 times the diameter of the holes).

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)
EP04292774A 2004-01-16 2004-11-25 Dispositif de contrôle de jeu dans une turbine à gaz Active EP1555394B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0400393A FR2865237B1 (fr) 2004-01-16 2004-01-16 Perfectionnements apportes aux dispositifs de controle de jeu dans une turbine a gaz
FR0400393 2004-01-16

Publications (2)

Publication Number Publication Date
EP1555394A1 EP1555394A1 (fr) 2005-07-20
EP1555394B1 true EP1555394B1 (fr) 2008-09-24

Family

ID=34610777

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04292774A Active EP1555394B1 (fr) 2004-01-16 2004-11-25 Dispositif de contrôle de jeu dans une turbine à gaz

Country Status (9)

Country Link
US (1) US7287955B2 (es)
EP (1) EP1555394B1 (es)
JP (1) JP2005201277A (es)
CA (1) CA2491666C (es)
DE (1) DE602004016722D1 (es)
ES (1) ES2314355T3 (es)
FR (1) FR2865237B1 (es)
RU (1) RU2304221C2 (es)
UA (1) UA83001C2 (es)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7597537B2 (en) * 2005-12-16 2009-10-06 General Electric Company Thermal control of gas turbine engine rings for active clearance control
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
US7819626B2 (en) * 2006-10-13 2010-10-26 General Electric Company Plasma blade tip clearance control
US7823389B2 (en) * 2006-11-15 2010-11-02 General Electric Company Compound clearance control engine
JP5078341B2 (ja) * 2006-12-15 2012-11-21 三菱重工業株式会社 タービン翼環構造およびその組立方法
US7785063B2 (en) * 2006-12-15 2010-08-31 Siemens Energy, Inc. Tip clearance control
FR2921410B1 (fr) * 2007-09-24 2010-03-12 Snecma Organe de verrouillage de secteurs d'anneau sur un carter de turbomachine, comprenant des moyens permettant sa prehension
FR2931872B1 (fr) * 2008-05-28 2010-08-20 Snecma Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles.
GB2469490B (en) * 2009-04-16 2012-03-07 Rolls Royce Plc Turbine casing cooling
US8342798B2 (en) 2009-07-28 2013-01-01 General Electric Company System and method for clearance control in a rotary machine
GB201013723D0 (en) * 2010-08-17 2010-09-29 Rolls Royce Plc Manifold mounting arrangement
US8864450B2 (en) 2011-02-01 2014-10-21 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US8794910B2 (en) 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
FR2972483B1 (fr) * 2011-03-07 2013-04-19 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
US8973373B2 (en) 2011-10-31 2015-03-10 General Electric Company Active clearance control system and method for gas turbine
US9341074B2 (en) * 2012-07-25 2016-05-17 General Electric Company Active clearance control manifold system
EP2803822B1 (fr) * 2013-05-13 2019-12-04 Safran Aero Boosters SA Système de prélèvement d'air de turbomachine axiale
US9874105B2 (en) * 2015-01-26 2018-01-23 United Technologies Corporation Active clearance control systems
US20160326915A1 (en) * 2015-05-08 2016-11-10 General Electric Company System and method for waste heat powered active clearance control
FR3045717B1 (fr) 2015-12-22 2020-07-03 Safran Aircraft Engines Dispositif de pilotage de jeu en sommets d'aubes rotatives de turbine
US10890085B2 (en) 2018-09-17 2021-01-12 Rolls-Royce Corporation Anti-rotation feature
US11788425B2 (en) * 2021-11-05 2023-10-17 General Electric Company Gas turbine engine with clearance control system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3909369A1 (de) * 1988-03-31 1989-10-26 Gen Electric Gasturbinen-spaltsteuerung
US5205115A (en) * 1991-11-04 1993-04-27 General Electric Company Gas turbine engine case counterflow thermal control
FR2766231B1 (fr) * 1997-07-18 1999-08-20 Snecma Dispositif d'echauffement ou de refroidissement d'un carter circulaire
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
UA83001C2 (ru) 2008-06-10
FR2865237A1 (fr) 2005-07-22
ES2314355T3 (es) 2009-03-16
JP2005201277A (ja) 2005-07-28
DE602004016722D1 (de) 2008-11-06
EP1555394A1 (fr) 2005-07-20
US7287955B2 (en) 2007-10-30
FR2865237B1 (fr) 2006-03-10
CA2491666C (fr) 2012-06-26
CA2491666A1 (fr) 2005-07-16
US20050158169A1 (en) 2005-07-21
RU2304221C2 (ru) 2007-08-10
RU2005100469A (ru) 2006-06-20

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