EP1555394A1 - Vorrichtung für die Regelung von Spalten in einer Gasturbine - Google Patents

Vorrichtung für die Regelung von Spalten in einer Gasturbine Download PDF

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Publication number
EP1555394A1
EP1555394A1 EP04292774A EP04292774A EP1555394A1 EP 1555394 A1 EP1555394 A1 EP 1555394A1 EP 04292774 A EP04292774 A EP 04292774A EP 04292774 A EP04292774 A EP 04292774A EP 1555394 A1 EP1555394 A1 EP 1555394A1
Authority
EP
European Patent Office
Prior art keywords
bores
downstream
upstream
fins
fixed ring
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
EP04292774A
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English (en)
French (fr)
Other versions
EP1555394B1 (de
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
Original Assignee
SNECMA Moteurs SA
SNECMA SAS
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.)
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Publication date
Application filed by SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1555394A1 publication Critical patent/EP1555394A1/de
Application granted granted Critical
Publication of EP1555394B1 publication Critical patent/EP1555394B1/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
    • 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 game control between the top of rotating blades and a set to fixed ring of a gas turbine.
  • a gas turbine for example a high-pressure turbine of turbomachine, typically comprises a plurality of stationary vanes arranged alternating with a plurality of blades in the gas passage hot from the combustion chamber of the turbomachine.
  • the blades movable turbine are surrounded on the entire circumference of the turbine by a set with fixed ring. This fixed ring set defines a wall of the flow vein of the hot gases through the blades of the turbine.
  • Such means generally present in the form of annular conduits which surround the fixed ring assembly and are traversed by air taken from other parts of the turbomachine. This air is injected on the outer surface of the fixed ring assembly and thereby causes dilations or thermal contractions of the fixed ring assembly which are able to vary its diameter. Expatiations and contractions thermal devices are controlled according to the operating regime of the turbine through a valve that allows to control the flow and the temperature of the air supplying the pipes. The group constituted by the pipes and the valve thus forms a steering box of the game in top of blades.
  • the present invention therefore aims to overcome such drawbacks by offering a game control device that optimizes air injection to obtain a better efficiency and homogeneity of the cooling of the fixed ring assembly.
  • a game control device between a top of rotating vanes and a fixed ring assembly of a turbine to gas
  • said fixed ring assembly having an annular housing having a longitudinal axis and provided with at least two spaced annular fins axially from each other and extending radially outwardly of the caster
  • the game control device comprising a circular casing of steering surrounding the casing of the fixed ring assembly
  • the housing of control comprising air circulation means formed of at least three annular ramps axially spaced from one another and arranged sides of each of the fins, means supply air to supply air to the air circulation ramps, and means for discharging air on the fins to modify the temperature of the fixed ring assembly, characterized in that the means for discharging air are formed for each traffic ramp of air, by at least one upper row of N bores arranged at view of one of the lateral faces of the fins and by at least one row lower than 2N holes arranged in relation to a connection radius between the fins and the casing of the fixed
  • the distribution and positioning of the discharge holes of air optimizes the heat exchange coefficient between fins and the flow of air passing through them. We thus obtain a better efficiency and homogeneity of cooling fins, and therefore more large range of displacement of the housing to drive the game at the top blades of the turbine.
  • the central ramp preferably comprises at least two rows upper each of N bores arranged in front of side faces upstream and downstream fins, and at least two lower rows of each 2N holes arranged in connection with connecting radii between the upstream and downstream fins and the casing of the fixed ring assembly.
  • the ramps upstream and downstream each have airflow sections substantially identical and the central ramp has a section debiting air which is substantially twice as large as that ramps upstream and downstream.
  • the N holes in each top row and 2N holes in each lower row have air flow sections substantially identical
  • the N bores of each upper row and the 2N holes in each lower row are arranged in staggered rows.
  • FIG. 1 illustrates, in longitudinal section, a high-pressure turbine 2 of turbomachine with longitudinal axis X-X.
  • this invention could also be applied to a low-pressure turbine of turbomachine or any other gas turbine equipped with a device game control at the top of the blades.
  • the high-pressure turbine 2 is composed in particular of a plurality of blades 4 arranged in a flow vein 6 of hot gases from a combustion chamber (not shown) of the turbine engine. These blades 4 are arranged downstream of blades 8 of the turbine with respect to the flow direction of the hot gases in the flow vein 6.
  • the blades 4 of the high-pressure turbine 2 are surrounded by a plurality of ring segments 12 arranged circumferentially around the X-X axis of the turbine so as to form a circular and continuous surface.
  • Ring segments 12 are mounted on an annular casing 14, also of longitudinal axis X-X, by via a plurality of spacers 16.
  • the casing 14 of the fixed ring assembly is provided with at least two vanes or annular bumps 18, 20 which are spaced axially from each other and which extend radially outwardly of the casing 14. These two fins will be differentiated with respect to the direction of flow 10 hot gases in the flow vein 6 by designating them by upstream fin 18 and downstream fin 20.
  • the upstream and downstream fins 18 and 20 have for main function to act as heat exchangers.
  • the ring segments 12 each have a surface 12a which is in direct contact with the hot gases and which partially defines the flow vein 6 of the gases through the turbine high pressure 2.
  • a radial clearance 22 is left between the inner surface 12a of the ring segments 12 and the top 4a of the turbine blades 4 of the turbine high pressure 2 to allow the rotation of the latter. To to increase the efficiency of the turbine, it is necessary to reduce as much as possible this game 22.
  • the control device of game 24 includes a circular steering box 26 surrounding the fixed ring assembly, and more specifically the casing 14.
  • the pilot housing 26 is intended to cool or heat the fins upstream 18 and downstream 20 of the casing 14 by discharge (or impact) of air on them. Under the effect of this air discharge, the casing 14 retracts or dilates, which decreases or increases the diameter of the ring segments fixed 12 of the turbine to adjust the game 22 at the top of the blades.
  • the piloting box 26 comprises in particular at least three annular air circulation ramps 28, 30 and 32 surrounding the housing 14 of the fixed ring assembly. These ramps are axially spaced from each other and are substantially parallel to each other other. They are arranged on either side of the lateral faces of each of the fins 18, 20 of which they marry approximately the form.
  • the air circulation ramps 28, 30 and 32 consist of a upstream ramp 28 which is disposed upstream of the upstream vane 18 (by ratio to the flow direction of hot gases in the vein 6), a downstream ramp 30 which is arranged downstream of the fin downstream 20 and a central ramp which is arranged between the upstream fins 18 and downstream 20.
  • the pilot housing 26 also comprises a collector tube of air (not shown in the figures) for supplying air to the ramps of air circulation 28, 30 and 32.
  • This air collector tube surrounds the ramps 28, 30 and 32 and supplies them with air through air ducts (not shown in the figures).
  • each air circulation ramp 28, 30 and 32 of the pilot housing 26 have at least one upper row of N holes 34 arranged opposite one of the lateral faces of the fins 18, 20 and at least one lower row of 2N bores 36 disposed at view of a connection radius between the fins 18, 20 and the casing 14 of the fixed ring assembly.
  • the holes 34, 36 which are for example obtained by laser, allow to discharge the air circulating in the ramps 28, 30 and 32 on the fins 18, 20 to change the temperature.
  • the upstream ramp 28 has, 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 vane 18 and at least one lower row of 2N bores 36 arranged in relation 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 has, on the side of its wall upstream 30a, at least one upper row of N bores 34 arranged with regard to the downstream lateral face 20b of the downstream fin 20 and at least one lower row of 2N bores 36 arranged with respect to a radius of connection 20d between the downstream vane 20 and the casing 14 of the assembly to fixed ring. 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 holes 34 arranged in relation to the side faces 18b, 20a of the upstream fins 18 and downstream 20, and at least two lower rows of each 2N holes 36 disposed to look 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 has at least one upper row of N bores 34 disposed at view of the downstream side face 18b of the upstream fin 18 and at least one lower row of 2N bores 36 arranged with respect to a radius of 18d connection between the upstream vane 18 and the casing 14 of the assembly to fixed ring.
  • the central ramp 32 comprises at less than an upper row of N bores 34 disposed in view of the upstream side face 20a of the downstream fin 20 and at least one row lower than 2N holes 36 arranged in relation to a radius of connection 20c between the downstream vane 20 and the casing 14 of the assembly to fixed ring.
  • the air discharge bores 34, 36 are arranged in two rows, with two thirds of the holes on the lower row and the remaining third on the top row.
  • the air from 2N holes 36 of each lower row "impact" on the lower area of the fins 18, 20, while the air discharged by the N holes 34 of each upper row has an impact on an area median fins.
  • the heat exchange obtained with fins is thus homogeneous and allows a greater range of movement of the housing to drive the game at the top of the blades of the turbine. Influence calculations thermal tests have shown that such a configuration makes it possible to gain up to more than 50 ° C on the average temperature of a fin by compared to a single row configuration of holes.
  • the ramps upstream 28 and downstream 30 each have air flow sections substantially identical and the central ramp 32 has a section debiting air which is substantially twice as large as that ramps upstream 28 and downstream 30.
  • the central ramp 32 being advantageously pierced on both sides, the flow of air flowing in this ramp must be double the airflow flowing in the ramps upstream 28 and downstream 30.
  • the N bores 34 of each upper row and the 2N bores 36 of each lower row presents, for each traffic ramp 28, 30 and 32 air flow sections substantially identical.
  • one third of the airflow circulating in the ramp central 32 is discharged by each of the two lower rows of holes 36 and a sixth of the same air flow is evacuated by each two upper rows of holes 34.
  • two thirds of the airflow flowing in the upstream and downstream ramps 28 is discharged by the lower rows of holes 36 of these ramps and a third of the same air flow is evacuated by the upper rows of holes 34 of these ramps.
  • the N bores 34 of each row upper and the 2N holes 36 of each lower row are arranged in staggered rows for each air circulation ramp.
  • the holes 34 of each upper row and the holes 36 of each lower row are preferably evenly spaced all around the longitudinal axis X-X of the housing 14 of the fixed ring assembly.
  • the angular spacing between two adjacent holes 34 of the same upper row advantageously corresponds to at least three times the diameter of the holes.
  • the choice of the number and the diameter of the holes 34, 36 of air discharge can be optimized by modeling based on a compromise between efficient ventilation of the fins and the constraints of manufacture of the pilot box. For example, for fins having a radial height of 18 mm, 288 holes can be made for each top row and 576 holes for each row lower (which corresponds to a value of 288 for N). For this configuration, the diameter of each hole can be fixed at 1 mm and the spacing between two adjacent holes in an upper row may be 3.8 mm (which corresponds to 3.8 times the diameter of the bores).

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  • 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 Vorrichtung für die Regelung von Spalten in einer Gasturbine Active EP1555394B1 (de)

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 true EP1555394A1 (de) 2005-07-20
EP1555394B1 EP1555394B1 (de) 2008-09-24

Family

ID=34610777

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04292774A Active EP1555394B1 (de) 2004-01-16 2004-11-25 Vorrichtung für die Regelung von Spalten in einer Gasturbine

Country Status (9)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1798381A2 (de) 2005-12-16 2007-06-20 General Electric Company Thermische Kontrolle von Turbinenringen zur aktiven Spaltregelung bei Gasturbinen
US10539037B2 (en) 2015-12-22 2020-01-21 Safran Aircraft Engines Device for controlling clearance at the tops of turbine rotating blades

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US8794910B2 (en) 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US8864450B2 (en) 2011-02-01 2014-10-21 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 (de) * 2013-05-13 2019-12-04 Safran Aero Boosters SA Luftentnahmesystem aus einer axialen Turbomaschine
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
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2629517A1 (fr) * 1988-03-31 1989-10-06 Gen Electric Dispositif de controle de jeu dans une turbine a gaz
EP0541325A1 (de) * 1991-11-04 1993-05-12 General Electric Company Thermische Steuerung eines Gehäuses eines Gasturbinentriebwerks
US6035929A (en) * 1997-07-18 2000-03-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Apparatus for heating or cooling a circular housing
US20020053837A1 (en) * 2000-11-09 2002-05-09 Snecma Moteurs Stator ring ventilation assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2629517A1 (fr) * 1988-03-31 1989-10-06 Gen Electric Dispositif de controle de jeu dans une turbine a gaz
EP0541325A1 (de) * 1991-11-04 1993-05-12 General Electric Company Thermische Steuerung eines Gehäuses eines Gasturbinentriebwerks
US6035929A (en) * 1997-07-18 2000-03-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Apparatus for heating or cooling a circular housing
US20020053837A1 (en) * 2000-11-09 2002-05-09 Snecma Moteurs Stator ring ventilation assembly

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1798381A2 (de) 2005-12-16 2007-06-20 General Electric Company Thermische Kontrolle von Turbinenringen zur aktiven Spaltregelung bei Gasturbinen
EP1798381A3 (de) * 2005-12-16 2008-02-27 General Electric Company Thermische Kontrolle von Turbinenringen zur aktiven Spaltregelung bei Gasturbinen
US10539037B2 (en) 2015-12-22 2020-01-21 Safran Aircraft Engines Device for controlling clearance at the tops of turbine rotating blades

Also Published As

Publication number Publication date
DE602004016722D1 (de) 2008-11-06
FR2865237A1 (fr) 2005-07-22
FR2865237B1 (fr) 2006-03-10
CA2491666C (fr) 2012-06-26
UA83001C2 (ru) 2008-06-10
US7287955B2 (en) 2007-10-30
JP2005201277A (ja) 2005-07-28
RU2304221C2 (ru) 2007-08-10
CA2491666A1 (fr) 2005-07-16
ES2314355T3 (es) 2009-03-16
US20050158169A1 (en) 2005-07-21
EP1555394B1 (de) 2008-09-24
RU2005100469A (ru) 2006-06-20

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