EP0821134A1 - Anordnung und Verfahren zur Regelung des Durchmessers eines Leitschaufelkranzes - Google Patents

Anordnung und Verfahren zur Regelung des Durchmessers eines Leitschaufelkranzes Download PDF

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Publication number
EP0821134A1
EP0821134A1 EP97401775A EP97401775A EP0821134A1 EP 0821134 A1 EP0821134 A1 EP 0821134A1 EP 97401775 A EP97401775 A EP 97401775A EP 97401775 A EP97401775 A EP 97401775A EP 0821134 A1 EP0821134 A1 EP 0821134A1
Authority
EP
European Patent Office
Prior art keywords
stator ring
conduits
cavity
gas
adjustment arrangement
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
EP97401775A
Other languages
English (en)
French (fr)
Other versions
EP0821134B1 (de
Inventor
Marc Marchi
Laurent Palmisano
Patrick Rossi
Jean-Claude Taillant
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0821134A1 publication Critical patent/EP0821134A1/de
Application granted granted Critical
Publication of EP0821134B1 publication Critical patent/EP0821134B1/de
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
    • 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
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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 invention relates to an arrangement and a stator ring diameter adjustment process so reduce the clearance with the rotor blade ends that this ring surrounds; it therefore applies to turbomachinery and was first designed for a turbine at high pressure of a two-stage turbine, without this application is exclusive.
  • the adjustment arrangement in accordance with the invention is characterized in that it comprises a housing element hollowed out and occupied by a cavity communicating through conduits to rooms located in upstream and downstream of the ring and which surround a vein gas circulation delimited by the ring.
  • This housing element is linked to the ring and located between the ring facing the rotor and the device surrounding gas blowing.
  • the corresponding method of adjusting diameter of a stator ring linked to a periphery housing element internal consists, while blowing gas on an outer periphery of this element like previously to produce a gas flow essentially convective through the element of casing, away from the stator ring and between the outer and inner edges.
  • FIG. 1 shows part of high-pressure turbine with an upstream stage 1 and a stage downstream 2.
  • Each of stages 1 and 2 comprises, from of a rotor 3 and towards the outside, a group of blades mobile 4 linked to the rotor 3, a hoop 5 surrounding the movable blades 4, from which it is separated by a small play 6, a casing element 7 to which the hoop 5 is fixed by circular 8 and 9 adjustments on its sides upstream and downstream, and the blowing distributor 10, called shower collar as already mentioned, and which consists of a circular tube with holes 11 opening towards the casing element 7 a little distance from him.
  • the blowing distributor 10 is supplied with air by a duct not shown leading to the compressor.
  • the essential element of the invention is located on a part outer 15 of the casing element 7, which is hollowed out a cavity 16 divided into two halves, a groove upstream 17 and a downstream groove 18, by a partition 19 transverse, planar and circular.
  • Upstream conduits 20 leading to an upstream chamber 21 open into the upstream groove 17, and likewise downstream conduits 22 leading downstream chamber 23 open into the downstream groove 18.
  • the upstream 21 and downstream 23 chambers are located around bladed distributors 33 and 34 preceding each of the movable blade stages 4.
  • Blade rings 35 and 36 intended to support the vanes of the distributors 33 and 34 isolate the chambers 21 and 23 from the vein 31 of gas flow in which the vanes and movable extend, so that the air which occupies them rooms 21 and 23 is not very agitated and remains even little near stagnant in their bottoms, where the ducts 20 and 22 open.
  • a rollover 40 which isolates a chamber background 41 from the rest of the chamber 21 and into which the upstream conduits 20 open.
  • the draft that can pass through chamber 21 runs along the cowling 40 and can only cross it by holes 42 perpendicular to its flow for enter the chamber bottom 41
  • the flow towards downstream through cavity 16 and conduits 20 and 22 is therefore of low flow, which favors convection movements and heat exchanges obtained by this means, in particular in the cavity 16.
  • the temperature of the casing element 7 thus tends to equalize without a significant air intake being product.
  • the flow is further slowed by the eccentric position of 24 days piercing the partition 19 to communicate the gorges 17 and 18.
  • These days 24 are in the form of axially offset lunules and radially of conduits 20 and 22: while these emerge at the bottom of gorges 17 and 18, days 24 are operated against their edge, near the distributor 10, from which they are only separated by a hoop 25 integrated into the casing element 7 and used to close the cavity 16 once it has been dug.
  • the air travels the upstream gorge 17 outwards and turn back in the downstream groove 18 by crossing the cavity 16.
  • the Figure 3 also shows that the days 24 extend, in angular direction in the cavity 16, halfway pairs of upstream 20 or downstream 22 conduits, which produces air circulation in the cavity 16. All of these provisions further increase convection.
  • Air from the upstream chamber 21 can also be taken and directed directly to the turbine ring hoop 5 to adjust the diameter of this one directly.
  • a distributor 30 in the form of an openwork plate divides and equalizes the air flow in front of the surface internal hoop 5. It is actually a known system used concurrently with the invention and which is only recalled here to better distinguish this last. In particular, a relatively important gas is directly blown on the hoop 5.
  • the convection circuit is here placed closer to the stator ring 5 and is split into two elements each of which is located in an annular rib 43 or 44 for connecting a casing outside 45 to a spacer 46 carrying the ring stator 5.
  • the ribs 43 and 44 are provided with spoilers 47 engaged under retaining edges 48 of the spacer 46 to constitute this connection, and we finds a spoiler 49 on the spacer 46, which is engaged under an edge 50 of the stator ring 5; all these borders 48 and 50 are retained in circular grooves drawn by the spoilers 47 and 49.
  • a jumper 51 connects two flanges circulars 52 and 53 of the spacer 30 and the ring stator 5 to prevent it from moving axial.
  • the two elements of the convection circuit here also include a cavity 16 divided in two parallel circular grooves 17 and 18 by a partition 19.
  • the communication channels of the grooves outside extend around the cavities 16, and the days (54 here) drilled through the partitions 19 are located at their inner circumferences to be offset radially of the conduits, as in the embodiment former. They can also be offset angularly from these conduits.
  • the upstream conduits 55 of the cavity 16 in the rib 43 open into a circular collecting chamber 56 substantially closed by a cover 57 and which communicates with conduits gas supply 65 by as many holes 58.
  • the downstream conduits 59 of this same cavity 16 open out in an intermediate chamber 60 in which still open the upstream conduits 61 on the other cavity 16, located in the rib 14; the conduits downstream 62 from this other cavity 16 open into a other chamber 66.
  • a deflector cover 67 is arranged in room 56, in front of the outlet of the conduits gas supply 65, to reverse the flow of it and make it gradually take a angular direction.
  • An upstream conduit 55 is sheltered from the gas inlet through the deflector cowling 67 and is So found in the bottom of room 56 where the gas is pretty much stagnant.
  • FIG. 5 finally shows the application of this system to an embodiment without the spacer 30: the fastening elements 49 to 53 defined above then directly connect the stator ring 5 to the ribs 13 and 14. All the other provisions of the Figure 4 are unchanged.

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)
  • Control Of Turbines (AREA)
EP97401775A 1996-07-25 1997-07-24 Anordnung und Verfahren zur Regelung des Durchmessers eines Leitschaufelkranzes Expired - Lifetime EP0821134B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9609364 1996-07-25
FR9609364A FR2751694B1 (fr) 1996-07-25 1996-07-25 Agencement et procede de reglage de diametre d'anneau de stator

Publications (2)

Publication Number Publication Date
EP0821134A1 true EP0821134A1 (de) 1998-01-28
EP0821134B1 EP0821134B1 (de) 2004-03-24

Family

ID=9494470

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97401775A Expired - Lifetime EP0821134B1 (de) 1996-07-25 1997-07-24 Anordnung und Verfahren zur Regelung des Durchmessers eines Leitschaufelkranzes

Country Status (5)

Country Link
US (1) US5915919A (de)
EP (1) EP0821134B1 (de)
CA (1) CA2211428C (de)
DE (1) DE69728222T2 (de)
FR (1) FR2751694B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1914392A2 (de) * 2006-10-12 2008-04-23 General Electric Company Turbinengehäuse-Prallkühlung für Hochleistungsgasturbinen
EP1923538A2 (de) * 2006-11-15 2008-05-21 General Electric Company Turbine mit Regelung des Schaufelspitzenspiels durch Transpiration

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2780443B1 (fr) * 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
DE10019437A1 (de) * 2000-04-19 2001-12-20 Rolls Royce Deutschland Verfahren und Vorrichtung zum Kühlen der Gehäuse von Turbinen von Strahltriebwerken
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
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
DE102018203442A1 (de) 2018-03-07 2019-09-12 MTU Aero Engines AG Innenring für eine Turbomaschine, Leitschaufelkranz mit einem Innenring, Turbomaschine und Verfahren zur Herstellung eines Innenrings
US11015475B2 (en) * 2018-12-27 2021-05-25 Rolls-Royce Corporation Passive blade tip clearance control system for gas turbine engine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2295239A1 (fr) * 1974-12-19 1976-07-16 Gen Electric Turbine a gaz a vanne thermosensible pour le reglage du jeu entre le rotor et le stator
GB2062117A (en) * 1980-10-20 1981-05-20 Gen Electric Clearance Control for Turbine Blades
US4337016A (en) * 1979-12-13 1982-06-29 United Technologies Corporation Dual wall seal means
EP0115984A1 (de) * 1983-02-03 1984-08-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dichtung für die Laufschaufeln einer Gasturbine
GB2217788A (en) * 1988-03-31 1989-11-01 Gen Electric Gas turbine engine shroud clearance control
GB2263138A (en) * 1992-01-08 1993-07-14 Snecma Turbomachine compressor casing with clearance control means
FR2688539A1 (fr) * 1992-03-11 1993-09-17 Snecma Stator de turbomachine comprenant des dispositifs de reglage de jeu entre le stator et les aubes du rotor.

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2712727A (en) * 1950-05-17 1955-07-12 Rolls Royce Gas turbine power plants with means for preventing or removing ice formation
GB2047354B (en) * 1979-04-26 1983-03-30 Rolls Royce Gas turbine engines
GB2236147B (en) * 1989-08-24 1993-05-12 Rolls Royce Plc Gas turbine engine with turbine tip clearance control device and method of operation
GB9210642D0 (en) * 1992-05-19 1992-07-08 Rolls Royce Plc Rotor shroud assembly
JPH06173712A (ja) * 1992-12-14 1994-06-21 Toshiba Corp ガスタービンケーシングの冷却装置
US5593277A (en) * 1995-06-06 1997-01-14 General Electric Company Smart turbine shroud

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2295239A1 (fr) * 1974-12-19 1976-07-16 Gen Electric Turbine a gaz a vanne thermosensible pour le reglage du jeu entre le rotor et le stator
US4337016A (en) * 1979-12-13 1982-06-29 United Technologies Corporation Dual wall seal means
GB2062117A (en) * 1980-10-20 1981-05-20 Gen Electric Clearance Control for Turbine Blades
EP0115984A1 (de) * 1983-02-03 1984-08-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dichtung für die Laufschaufeln einer Gasturbine
GB2217788A (en) * 1988-03-31 1989-11-01 Gen Electric Gas turbine engine shroud clearance control
GB2263138A (en) * 1992-01-08 1993-07-14 Snecma Turbomachine compressor casing with clearance control means
FR2688539A1 (fr) * 1992-03-11 1993-09-17 Snecma Stator de turbomachine comprenant des dispositifs de reglage de jeu entre le stator et les aubes du rotor.

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1914392A2 (de) * 2006-10-12 2008-04-23 General Electric Company Turbinengehäuse-Prallkühlung für Hochleistungsgasturbinen
EP1914392A3 (de) * 2006-10-12 2013-01-02 General Electric Company Turbinengehäuse-Prallkühlung für Hochleistungsgasturbinen
US8801370B2 (en) 2006-10-12 2014-08-12 General Electric Company Turbine case impingement cooling for heavy duty gas turbines
EP1923538A2 (de) * 2006-11-15 2008-05-21 General Electric Company Turbine mit Regelung des Schaufelspitzenspiels durch Transpiration
EP1923538A3 (de) * 2006-11-15 2014-07-23 General Electric Company Turbine mit Regelung des Schaufelspitzenspiels durch Transpiration

Also Published As

Publication number Publication date
EP0821134B1 (de) 2004-03-24
FR2751694A1 (fr) 1998-01-30
FR2751694B1 (fr) 1998-09-04
US5915919A (en) 1999-06-29
CA2211428C (fr) 2006-03-14
DE69728222T2 (de) 2005-03-10
CA2211428A1 (fr) 1998-01-25
DE69728222D1 (de) 2004-04-29

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