EP0103260A2 - Régulation du jeu des extrémités des aubes de turbine - Google Patents

Régulation du jeu des extrémités des aubes de turbine Download PDF

Info

Publication number
EP0103260A2
EP0103260A2 EP83108779A EP83108779A EP0103260A2 EP 0103260 A2 EP0103260 A2 EP 0103260A2 EP 83108779 A EP83108779 A EP 83108779A EP 83108779 A EP83108779 A EP 83108779A EP 0103260 A2 EP0103260 A2 EP 0103260A2
Authority
EP
European Patent Office
Prior art keywords
turbine
guide vane
shrouds
vane segments
casing
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.)
Withdrawn
Application number
EP83108779A
Other languages
German (de)
English (en)
Other versions
EP0103260A3 (fr
Inventor
Masami Noda
Takashi Ikeguchi
Kazuhiko Kawaike
Katsuo Wada
Yasuhiro Mr. Kato
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.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
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
Priority claimed from JP15392382A external-priority patent/JPS5943905A/ja
Priority claimed from JP19898682A external-priority patent/JPS5990706A/ja
Application filed by Hitachi Ltd filed Critical Hitachi Ltd
Publication of EP0103260A2 publication Critical patent/EP0103260A2/fr
Publication of EP0103260A3 publication Critical patent/EP0103260A3/fr
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Definitions

  • This invention relates to a turbine in which clearance between turbine blade tips and shrouds is controlled.
  • the clearance between turbine blade tips and shrouds causes fluid used to drive the turbine to leak. If the clearance is large, the amount of the leakage increases, resulting in deteriorated heat efficiency of turbines such as a gas turbine or a steam 'turbine.
  • An object of the invention is to provide a turbine whose clearance between turbine blade tips and shrouds can be controlled automatically during operation by simple structure.
  • shrouds are mounted to a body stationary in the rotating direction of a turbine rotor and movable freely in a radial direction under expansion thereof, and which can be expanded radially from the centre of said turbine rotor substantially in the same manner as said turbine blades.
  • FIG 1 there is illustrated a part of a gas turbine in which a turbine rotor assembly 10 is disposed downstream of a guide vane assembly 11 inside a turbine casing 12.
  • the turbine rotor assembly 10 is rotated by high temperature gas which flows from an entrance site A of the turbine, i.e. an exit of combustion chamber to an exit site B of the turbine rotor assembly 10.
  • the turbine rotor assembly 10 comprises an annular disc 13 fixed to a turbine rotor 14 which is supported rotatably by a bearing 15 and a plurality of turbine blades 16 attached by dave-tail structure around the annular disc 13.
  • the turbine blades 16 exposed to the high temperature gas expand radially from the centre of the turbine rotor 14 corresponding to a standard position of expansion.
  • the guide vane assembly 11 comprises a plurality of guide vane segments 17, each of which forming a body, which are mounted to a stationary part 18 of a bearing 15 through pins 19 respectively and an annular member 20.
  • the guide vane segments 17 are disposed around the annular member 20 as shown Figure 2.
  • the guide vane segments 17 are diposed radially free against the casing 12.
  • the guide vane segments 17 expand radially from the center line of the stationary part of the bearing 18, i.e. the centre of the bearing 15 or the centre line (c-c) of the turbine rotor 14, in the same manner as the turbine blades 16.
  • the guide vane segments 17 each is a united body providing guide vanes 21, an outer endwall 22, a pair of projections 23a, 23b, an inner endwall 24 and a pair of flanges 25a, 25b.
  • the inner endwall 24 extended substantially in parallel with the shaft of the turbine at the inner side of the guide vanes 21.
  • the flanges 25a, 25b provide pin holes for pin 19 to be inserted.
  • the outer endwall 22 extends substantially in parallel with the shaft of the turbine at the outer side of the guide vanes 21 and also extends downstream so as to face the turbine blade tip 26. Thus extended portion of the outer endwall 22 corresponds to a shroud 27.
  • the shroud 27 may be constructed separately and be fixed to the outer endwall 22.
  • a pair of projections 23a, 23b extending outward from the guide vanes 21 are disposed respectively so as to face a pair of support rings 28, 29 which extend inward from the casing 12.
  • the projections 23a, 23b provide a plurality of coaxial slots 30a, 30b so that cooling fluid which may be flown in a space 31 to cool the guide vane segments 17 can be sealed by labyrinth effect based on the slots 30a, 30b.
  • a seal plate 34 to seal in a radial direction is inserted as shown in figure 3.
  • the same seal mechanism comprising the slot 32 and the seal plate 34 as mentioned above is adapted at circumferential end portions of the inner endwall 24 (not shown).
  • parallel meandering slots are formed at both ends 33a, 33b of the outer endwall 22 so that each slot of adjacent endwalls 22 can be engaged with each other, resulting in sealing contact surface of each outer endwall 22.
  • the guide vane segments 17 are movable radially against the casing 12, sealing the space 31. Accordingly, as already mentioned above, the guide vane segments 17 can expand radially during operation from the centre of the shaft in the same manner as the turbine blades 16 without being undue affected by p.e. thermal expansion of the casing 12.
  • Each amount of thermal expansion of the guide vane segments 17 and turbine blades 16 is almost the same because temperature of the gas is nearly the same both at the guide vane segments 17 and at-the turbine blades 16. Therefore the clearance between the turbine blade tips 26 and the shrouds 27 mounted to the guide vane segments 17 is kept constant, as shown in Figure 4, in all the operation modes, i.e. during accelaration, steady state running and deceleration.
  • clearance can be set very small without necessity to take into account conflict between the turbine blade tips 26 and the shrouds 27 due to transient change of the clearance during operation.
  • the pressure of the cooling fluid in the space 31 is adjusted to the same static pressure as that of the gas passing the guide vanes 21 and the turbine blades 16 so that deformation of the shrouds 27 can be avoided by cancelling each force acting on each side of the shrouds 27.
  • Such eliminatinq of deformation of the shrouds 27 can be further improved by the embodiment illustrated in Figure 5. That is, in practise two pressures of the gas are different at positions of the guide vane 21 and the turbine blade 16 respectively.
  • the space for the cooling fluid is divided into two compartments, i.e.
  • an upstream compartment 50 and a downstream compartment 51 by a dividing plate 52 of which one end is fixed to a portion 53 of the outer endwall 22, and the other end is inserted in a slot 54 of the casing 12.
  • this plate 52 slides in the slot 54, maintaining sealing between the other end portion of the dividing plate 52 and the casing 12.
  • Said end portion 53 is chosen at a region corresponding to a guide vane end portion adjacent to the turbine blade 16.
  • the cooling fluid supplied from an opening 55 flows from the upstream compartment 50 to the downstream compartment 51 through an orifice 56 in the dividing plate 52.
  • the pressure in the upstream compartment 50 can be the same pressure as the gas pressure at the guide vane 21.
  • the size of the orifice 56 is chosen so that the pressure reduced thereby is the same pressure as that of the gas passing at the turbine blade 16.
  • the cooling fluid can flow out through small gap between projections 23a, 23b and support rings 28, 29. This embodiment can serve to allow the clearance to be set even smaller without the negative influence on the shrouds 27.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP83108779A 1982-09-06 1983-09-06 Régulation du jeu des extrémités des aubes de turbine Withdrawn EP0103260A3 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
JP153923/82 1982-09-06
JP15392382A JPS5943905A (ja) 1982-09-06 1982-09-06 軸流タ−ビンの動翼先端すきま調整装置
JP19898682A JPS5990706A (ja) 1982-11-15 1982-11-15 軸流タ−ビンの動翼先端すきま調整装置
JP198986/82 1982-11-15

Publications (2)

Publication Number Publication Date
EP0103260A2 true EP0103260A2 (fr) 1984-03-21
EP0103260A3 EP0103260A3 (fr) 1984-09-26

Family

ID=26482405

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83108779A Withdrawn EP0103260A3 (fr) 1982-09-06 1983-09-06 Régulation du jeu des extrémités des aubes de turbine

Country Status (1)

Country Link
EP (1) EP0103260A3 (fr)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2206651A (en) * 1987-07-01 1989-01-11 Rolls Royce Plc Turbine blade shroud structure
US5868553A (en) * 1996-05-08 1999-02-09 Asea Brown Boveri Ag Exhaust gas turbine of an exhaust gas turbocharger
GB2380527A (en) * 2001-08-11 2003-04-09 Rolls Royce Plc Gas turbine engine guide vane assembly with noise reduction
CN100400797C (zh) * 2001-04-12 2008-07-09 西门子公司 具有可轴向相对移动的引导部件的燃气轮机
JP2008255989A (ja) * 2007-04-05 2008-10-23 Alstom Technology Ltd ターボ機械の羽根における隙間シール
WO2011035947A1 (fr) 2009-09-25 2011-03-31 Evonik Rohmax Additives Gmbh Composition pour améliorer les propriétés d'écoulement à froid des combustibles
WO2012130535A1 (fr) 2011-03-25 2012-10-04 Evonik Rohmax Additives Gmbh Composition pour améliorer la stabilité à l'oxydation de mazouts
US8347633B2 (en) 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8418458B2 (en) 2009-01-20 2013-04-16 Williams International Co., L.L.C. Turbocharger core
US8459035B2 (en) 2007-07-27 2013-06-11 United Technologies Corporation Gas turbine engine with low fan pressure ratio
CN114607474A (zh) * 2022-03-21 2022-06-10 中国联合重型燃气轮机技术有限公司 静叶间隙控制系统和具有其的燃气轮机

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2849209A (en) * 1950-10-11 1958-08-26 Gen Electric Nozzle construction for turbines
CH482915A (de) * 1967-11-03 1969-12-15 Sulzer Ag Leitvorrichtung für Axialturbine
SE398659B (sv) * 1976-05-05 1978-01-09 Stal Laval Turbin Ab Tetningsanordning i en gasturbin
US4248569A (en) * 1978-11-13 1981-02-03 General Motors Corporation Stator mounting
GB2061396B (en) * 1979-10-24 1983-05-18 Rolls Royce Turbine blade tip clearance control

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2206651B (en) * 1987-07-01 1991-05-08 Rolls Royce Plc Turbine blade shroud structure
GB2206651A (en) * 1987-07-01 1989-01-11 Rolls Royce Plc Turbine blade shroud structure
US5868553A (en) * 1996-05-08 1999-02-09 Asea Brown Boveri Ag Exhaust gas turbine of an exhaust gas turbocharger
CN100400797C (zh) * 2001-04-12 2008-07-09 西门子公司 具有可轴向相对移动的引导部件的燃气轮机
GB2380527A (en) * 2001-08-11 2003-04-09 Rolls Royce Plc Gas turbine engine guide vane assembly with noise reduction
US6764276B2 (en) 2001-08-11 2004-07-20 Rolls-Royce Plc Guide vane assembly
GB2380527B (en) * 2001-08-11 2004-10-27 Rolls Royce Plc A guide vane assembly
JP2008255989A (ja) * 2007-04-05 2008-10-23 Alstom Technology Ltd ターボ機械の羽根における隙間シール
US8347633B2 (en) 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8459035B2 (en) 2007-07-27 2013-06-11 United Technologies Corporation Gas turbine engine with low fan pressure ratio
US8418458B2 (en) 2009-01-20 2013-04-16 Williams International Co., L.L.C. Turbocharger core
EP2305753A1 (fr) 2009-09-25 2011-04-06 Evonik RohMax Additives GmbH Composition pour améliorer les propriétés d'écoulement à froid d'huiles combustibles
WO2011035947A1 (fr) 2009-09-25 2011-03-31 Evonik Rohmax Additives Gmbh Composition pour améliorer les propriétés d'écoulement à froid des combustibles
US10131776B2 (en) 2009-09-25 2018-11-20 Evonik Oil Additives Gmbh Composition to improve cold flow properties of fuel oils
WO2012130535A1 (fr) 2011-03-25 2012-10-04 Evonik Rohmax Additives Gmbh Composition pour améliorer la stabilité à l'oxydation de mazouts
CN114607474A (zh) * 2022-03-21 2022-06-10 中国联合重型燃气轮机技术有限公司 静叶间隙控制系统和具有其的燃气轮机

Also Published As

Publication number Publication date
EP0103260A3 (fr) 1984-09-26

Similar Documents

Publication Publication Date Title
US4805398A (en) Turbo-machine with device for automatically controlling the rate of flow of turbine ventilation air
US4242042A (en) Temperature control of engine case for clearance control
US4193738A (en) Floating seal for a variable area turbine nozzle
US4668163A (en) Automatic control device of a labyrinth seal clearance in a turbo-jet engine
US5601402A (en) Turbo machine shroud-to-rotor blade dynamic clearance control
US4343592A (en) Static shroud for a rotor
US4379677A (en) Device for adjusting the clearance between moving turbine blades and the turbine ring
EP0770761B1 (fr) Virole entourant un rotor d'une turbomachine
US3301527A (en) Turbine diaphragm structure
US3227418A (en) Variable clearance seal
US3391904A (en) Optimum response tip seal
US20210355844A1 (en) Turbine shroud sector with cooled sealing strips
US5022817A (en) Thermostatic control of turbine cooling air
US5211534A (en) Blade tip clearance control apparatus
US3314648A (en) Stator vane assembly
EP0532303A1 (fr) Système et méthode pour le refroidissement amélioré de moteurs
EP0103260A2 (fr) Régulation du jeu des extrémités des aubes de turbine
US4804310A (en) Clearance control apparatus for a bladed fluid flow machine
US10823184B2 (en) Engine with face seal
JPH07279605A (ja) 流体機械の運転法
US20180298820A1 (en) Variable vane segment
EP3536903B1 (fr) Passage de refroidissement comportant une nervure structurelle et une fente de refroidissement de film
US5269648A (en) Arrangement for controlling the flow cross section of a turbomachine
JPS63239301A (ja) ガスタ−ビンシユラウド
JPS62195402A (ja) タ−ビンロ−タ翼の先端間隙を制御するシユラウド装置

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: 19830906

AK Designated contracting states

Designated state(s): CH DE FR GB IT LI

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Designated state(s): CH DE FR GB IT LI

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

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Withdrawal date: 19851203

RIN1 Information on inventor provided before grant (corrected)

Inventor name: NODA, MASAMI

Inventor name: KATO, YASUHIRO, MR.

Inventor name: IKEGUCHI, TAKASHI

Inventor name: KAWAIKE, KAZUHIKO

Inventor name: WADA, KATSUO