EP0821134B1 - Anordnung und Verfahren zur Regelung des Durchmessers eines Leitschaufelkranzes - Google Patents

Anordnung und Verfahren zur Regelung des Durchmessers eines Leitschaufelkranzes Download PDF

Info

Publication number
EP0821134B1
EP0821134B1 EP97401775A EP97401775A EP0821134B1 EP 0821134 B1 EP0821134 B1 EP 0821134B1 EP 97401775 A EP97401775 A EP 97401775A EP 97401775 A EP97401775 A EP 97401775A EP 0821134 B1 EP0821134 B1 EP 0821134B1
Authority
EP
European Patent Office
Prior art keywords
stator ring
diameter
arrangement
setting
ducts
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
EP97401775A
Other languages
English (en)
French (fr)
Other versions
EP0821134A1 (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
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 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

Links

Images

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 play 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.
  • US-A-4,337,016 describes arrangements for cooling a turbine stator ring associated with an external blowing device on the turbine casing.
  • 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 at one stage upstream 1 and one stage downstream 2.
  • 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 8 and 9 circular 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, flat 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 little agitated and remains even little near stagnating in their bottoms, where conduits 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 significant air sampling 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 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 previous. 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 a realization without the spacer 30: the fastening elements 49 to 53 defined above then directly join the stator ring 5 to the ribs 13 and 14. All other provisions of the Figure 4 are unchanged.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Claims (9)

  1. Anordnung zur Regelung des Durchmessers eines Statorrings mit Hilfe einer umschließenden Gaseinblasvorrichtung (10, 56, 65),
       dadurch gekennzeichnet, daß sie ein mit dem Ring (5) verbundenes und zwischen dem Ring und der Gaseinblasvorrichtung (10, 56, 65) angeordnetes Gehäuseelement (7, 43, 44, 45) umfaßt, das ausgehöhlt und von einem Hohlraum (16) besetzt ist, der über Leitungen (20, 22, 55, 61, 62) mit Kammern (21, 23, 56, 60, 663) auf der stromaufwärtigen und der stromabwärtigen Seite des Rings in Verbindung steht, die eine von dem Ring begrenzte Gaszirkulationsströmung umschließen und die vor den Leitungen (20, 22, 55, 61, 62) von fast stagnierendem Gas besetzt sind, wobei der Hohlraum (16) und die Leitungen (20, 22, 55, 59, 61, 62) im Abstand von dem Statorring verlaufen,
       und daß der Hohlraum von einer gelochte Trennwand (19) unterteilt wird in eine stromaufwärtige Hälfte (17), in der die Leitungen (20, 55, 61) münden, die mit der stromaufwärtigen Kammer (21, 56, 60) in Verbindung stehen, und eine stromabwärtige Hälfte (18), in der die Leitungen (22, 59, 62) münden, die mit der stromabwärtigen Kammer (23, 60, 66) in Verbindung stehen.
  2. Anordnung zur Regelung des Durchmessers eines Statorrings nach Anspruch 1, dadurch gekennzeichnet, daß die Trennwand (19) mit Öffnungen (24, 54) versehen ist, die gegenüber den Leitungen radial versetzt sind.
  3. Anordnung zur Regelung des Durchmessers eines Statorrings nach Anspruch 1, dadurch gekennzeichnet, daß die Trennwand mit Öffnungen (24, 54) versehen ist, die gegenüber den Leitungen winkelversetzt sind.
  4. Anordnung zur Regelung des Durchmessers eines Statorrings nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß eine der Kammern (21) zu einem Kreis zum Einblasen von Gas auf den Statorring (5) gehört.
  5. Anordnung zur Regelung des Durchmessers eines Statorrings nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß eine der Kammern (56) zu der umschließenden Gaseinblasvorrichtung gehört.
  6. Anordnung zur Regelung des Durchmessers eines Statorrings nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß der Hohlraum auf einer Rippe (13, 14) zum Halten des Statorrings angeordnet ist.
  7. Anordnung zur Regelung des Durchmessers eines Statorrings nach Anspruch 6, dadurch gekennzeichnet, daß sie zwei Hohlräume aufweist, die in zwei parallelen Rippen (13, 14) zum Halten des Statorrings angeordnet sind, wobei die Hohlräume (16) über Leitungen (49, 61) und einen Zwischenkammer (60) miteinander in Verbindung stehen.
  8. Anordnung zur Regelung des Durchmessers eines Statorrings nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß eine der Kammern (21, 56) Sitz einer Gasströmung ist und daß eine in der Kammer angeordnete Verkleidung (40, 67) dort einen im wesentlichen strömungsfreien Kammerboden begrenzt, in welchem die Leitungen (20, 55) des Hohlraums münden, die mit der genannten Kammer in Verbindung stehen.
  9. Verfahren zur Regelung des Durchmessers eines mit einem Innenumfang eines Gehäuseelements (7) verbundenen Statorrings (5), bei dem auf einen Außenumfang des Gehäuseelements Gas geblasen wird,
       dadurch gekennzeichnet,    daß eine im wesentlichen konvektive Gasströmung durch das Gehäuseelement, im Abstand von dem Statorring und zwischen dem Innenumfang und dem Außenumfang erzeugt wird.
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 EP0821134A1 (de) 1998-01-28
EP0821134B1 true 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)

Families Citing this family (8)

* 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
US8801370B2 (en) * 2006-10-12 2014-08-12 General Electric Company Turbine case impingement cooling for heavy duty gas turbines
US7740443B2 (en) * 2006-11-15 2010-06-22 General Electric Company Transpiration clearance control turbine
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
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

Family Cites Families (13)

* 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
US3966354A (en) * 1974-12-19 1976-06-29 General Electric Company Thermal actuated valve for clearance control
GB2047354B (en) * 1979-04-26 1983-03-30 Rolls Royce Gas turbine engines
US4337016A (en) * 1979-12-13 1982-06-29 United Technologies Corporation Dual wall seal means
GB2062117B (en) * 1980-10-20 1983-05-05 Gen Electric Clearance control for turbine blades
FR2540560B1 (fr) * 1983-02-03 1987-06-12 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine
DE3909369A1 (de) * 1988-03-31 1989-10-26 Gen Electric Gasturbinen-spaltsteuerung
GB2236147B (en) * 1989-08-24 1993-05-12 Rolls Royce Plc Gas turbine engine with turbine tip clearance control device and method of operation
FR2685936A1 (fr) * 1992-01-08 1993-07-09 Snecma Dispositif de controle des jeux d'un carter de compresseur de turbomachine.
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.
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

Also Published As

Publication number Publication date
DE69728222D1 (de) 2004-04-29
CA2211428A1 (fr) 1998-01-25
FR2751694A1 (fr) 1998-01-30
EP0821134A1 (de) 1998-01-28
US5915919A (en) 1999-06-29
FR2751694B1 (fr) 1998-09-04
DE69728222T2 (de) 2005-03-10
CA2211428C (fr) 2006-03-14

Similar Documents

Publication Publication Date Title
JP4248785B2 (ja) ガスタービン固定子の径を調節するための装置
US6390771B1 (en) High-pressure compressor stator
US20110129332A1 (en) Axial-centrifugal compressor having system for controlling play
EP0816639B1 (de) Kühlgaskrümmer für Dichtungsspaltregelung einer Turbomaschine
US5586860A (en) Turbo aero engine provided with a device for heating turbine disks on revving up
EP0821134B1 (de) Anordnung und Verfahren zur Regelung des Durchmessers eines Leitschaufelkranzes
JPH0689653B2 (ja) ガスタービンエンジンの圧縮機用の羽根及びパツキングの隙間最適化装置
EP2732145B1 (de) Gasturbine mit einem druckbeaufschlagten sumpf
EP2948642B1 (de) Mehrsegmentale verstellbare statorschaufel für schaufelanordnung mit einem variablen bereich
CN107023391B (zh) 用于燃气涡轮发动机的压缩机
EP0636765B1 (de) Kühlung von Turbinenrotorscheibe
CN108252748A (zh) 涡轮发动机诱导器组件
US7140836B2 (en) Casing arrangement
JP2008057537A (ja) タービンエンジンで使用するノズルセグメントを製作するためのノズルシングレット及びガスタービンエンジン
EP1188901A2 (de) Durchfuhröffnungen zur Rotorkühlung
CN109958478A (zh) 翼型件及其制造方法
CN107084002A (zh) 一种组件的热应力释放
JP2005009410A (ja) ガスタービン及びロータシール空気導入方法
US10513947B2 (en) Adjustable flow split platform cooling for gas turbine engine
US20180038236A1 (en) Gas turbine engine stator vane baffle arrangement
FR3055355A1 (fr) Dispositif et procede de reglage de jeux entre un rotor et un stator concentrique d'une turbomachine
FR3002972A1 (fr) Dispositif de ventilation d'un carter de stator d'une turbomachine comprenant un ajustement en direction axiale
US10495107B2 (en) Guide vane assembly with compensation device
FR3115562A1 (fr) Injecteur d’air de refroidissement pour turbine de turbomachine
CN114144573A (zh) 涡轮机械整流器级，带有具有根据叶片的取向的可变截面的冷却空气泄漏通道

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19970812

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20020221

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA MOTEURS

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 69728222

Country of ref document: DE

Date of ref document: 20040429

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20040419

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20041228

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20150626

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20150623

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20160720

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69728222

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160724

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160724

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719