EP4185765A1 - Turbine mit druckhohlräumen - Google Patents

Turbine mit druckhohlräumen

Info

Publication number
EP4185765A1
EP4185765A1 EP21752581.5A EP21752581A EP4185765A1 EP 4185765 A1 EP4185765 A1 EP 4185765A1 EP 21752581 A EP21752581 A EP 21752581A EP 4185765 A1 EP4185765 A1 EP 4185765A1
Authority
EP
European Patent Office
Prior art keywords
annular
air
rotor
upstream
drum
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.)
Pending
Application number
EP21752581.5A
Other languages
English (en)
French (fr)
Inventor
Matthieu Simon
Ulysse Jacques Bernard DANTENY
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP4185765A1 publication Critical patent/EP4185765A1/de
Pending legal-status Critical Current

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
    • F01D1/26—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially axially
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/44—Movement of components by counter rotation
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the primary air flow from the combustion chamber 5 has a high temperature and heats the parts located downstream, such as the fixed and moving parts of the turbine 6, 7.
  • the downstream annular cavity is supplied with cooling air with air having a lower pressure, this air proving to be much less penalizing on the performance of the turbomachine.
  • This cooling air is inexpensive and can be used in large quantities.
  • the low supply pressure of this cooling air does not allow the purging of the entire annular space, that is to say the upstream annular cavity and the downstream annular cavity, which explains the separation of the two cavities by sealing means. Downstream of the external drum, the air is expanded and the slightly pressurized air coming from the secondary stream can still reach the primary stream.
  • This document also relates to a turbomachine, such as a turboprop or an aircraft turbojet, comprising at least one turbine as described above.
  • a turbomachine such as a turboprop or an aircraft turbojet, comprising at least one turbine as described above.
  • the annular stream of secondary air refers here to the annular stream of air surrounding the annular stream of primary air and which is well known in the state of the art relating to dual-flow turbomachines.
  • the turbomachine comprises a fan which blows air in a primary annular stream and in a secondary annular stream.
  • the turbine blades according to this document extend into the primary stream and the air for the downstream cavity is taken from the secondary stream.
  • At least a third annular housing can communicate fluidly with the intermediate annular cavity.
  • Said third annular housing can be arranged radially opposite the intermediate annular cavity and it can communicate fluidly with the annular primary air stream.
  • the downstream end of the turbine casing may be connected to an exhaust casing which may comprise an inner annular shroud and an outer annular shroud connected to each other by substantially radial stationary vanes.
  • FIGS. 4 to 6 illustrate a low-pressure turbomachine turbine 7 according to four possible embodiments.
  • the turbine 7 is of the counter-rotating type and comprises a first rotor 25 comprising one or more stages formed by bladed wheels 26, rotating around the longitudinal axis X of the turbine 7 in a first direction of rotation, and a second rotor 27 comprising one or more stages formed by bladed wheels 28, rotating around axis X in a second direction of rotation, opposite to the first direction of rotation.
  • annular cavity 40 In the embodiments of Figures 4 and 5, only an upstream annular cavity 40 and a downstream annular cavity 42 are present, whereas in the embodiments of Figures 5 and 6, an intermediate annular cavity 46 is formed longitudinally between the upstream annular cavity 40 and the downstream annular cavity 42 and sealing means 44 separate the intermediate annular cavity 46 from the upstream annular cavity 40 and from the downstream annular cavity 42.
  • the sealing means 44 comprise annular wipers 44a formed at the radially inner end of a radial annular wall 46 of the casing 31, this radial annular wall 46 being connected at its radially outer end to the radially outer annular wall 32 .
  • the wipers 44a cooperate with the radially outer drum 29 in order to seal against the circulation of air.
  • the upstream annular cavity 40 connected to first means 48 for supplying cooling air at a first pressure and at a first temperature and the downstream annular cavity is connected to second means 50 for supplying cooling air at a second pressure. lower than the first pressure and having a second temperature lower than the first temperature.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP21752581.5A 2020-07-23 2021-07-22 Turbine mit druckhohlräumen Pending EP4185765A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2007781A FR3112811B1 (fr) 2020-07-23 2020-07-23 Turbine à cavités pressurisées
PCT/FR2021/051374 WO2022018385A1 (fr) 2020-07-23 2021-07-22 Turbine à cavités pressurisées

Publications (1)

Publication Number Publication Date
EP4185765A1 true EP4185765A1 (de) 2023-05-31

Family

ID=73401655

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21752581.5A Pending EP4185765A1 (de) 2020-07-23 2021-07-22 Turbine mit druckhohlräumen

Country Status (5)

Country Link
US (1) US20230296023A1 (de)
EP (1) EP4185765A1 (de)
CN (1) CN115885091A (de)
FR (1) FR3112811B1 (de)
WO (1) WO2022018385A1 (de)

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3540943A1 (de) * 1985-11-19 1987-05-21 Mtu Muenchen Gmbh Gasturbinenstrahltriebwerk in mehr-wellen-zweistrom-bauweise
US4752185A (en) * 1987-08-03 1988-06-21 General Electric Company Non-contacting flowpath seal
GB9027986D0 (en) * 1990-12-22 1991-02-13 Rolls Royce Plc Gas turbine engine clearance control
US5152666A (en) * 1991-05-03 1992-10-06 United Technologies Corporation Stator assembly for a rotary machine
WO1996006267A1 (en) * 1994-08-24 1996-02-29 United Technologies Corporation Rotatable seal element for a rotary machine
FR2766232B1 (fr) * 1997-07-18 1999-08-20 Snecma Dispositif de refroidissement ou d'echauffement d'un carter circulaire
US6227800B1 (en) * 1998-11-24 2001-05-08 General Electric Company Bay cooled turbine casing
FR2938293B1 (fr) * 2008-11-12 2015-08-21 Snecma Dispositif de regulation du debit d'air alimentant une cavite de ventillation de turbine d'une section de turbine de turbomachine
US8011877B2 (en) * 2008-11-24 2011-09-06 General Electric Company Fiber composite reinforced aircraft gas turbine engine drums with radially inwardly extending blades
EP2518278A1 (de) * 2011-04-28 2012-10-31 Siemens Aktiengesellschaft Kühlleitung eines Turbinengehäuses mit stromaufwärts fliessender Kühlflüssigkeit
US10302015B2 (en) * 2013-12-17 2019-05-28 United Technologies Corporation Adaptive turbomachine cooling system
FR3021700B1 (fr) 2014-05-27 2016-07-01 Snecma Dispositif de maintien d'un tube de refroidissement pour carter de turboreacteur
US10738791B2 (en) * 2015-12-16 2020-08-11 General Electric Company Active high pressure compressor clearance control
JP6639338B2 (ja) * 2016-07-11 2020-02-05 三菱日立パワーシステムズ株式会社 ガスタービン及びガスタービンの運転方法
US10612466B2 (en) * 2017-09-11 2020-04-07 United Technologies Corporation Gas turbine engine active clearance control system using inlet particle separator
US10480322B2 (en) * 2018-01-12 2019-11-19 General Electric Company Turbine engine with annular cavity
FR3082872B1 (fr) * 2018-06-25 2021-06-04 Safran Aircraft Engines Dispositif de refroidissement d'un carter de turbomachine

Also Published As

Publication number Publication date
FR3112811A1 (fr) 2022-01-28
CN115885091A (zh) 2023-03-31
FR3112811B1 (fr) 2022-07-22
WO2022018385A1 (fr) 2022-01-27
US20230296023A1 (en) 2023-09-21

Similar Documents

Publication Publication Date Title
CA2758175C (fr) Moteur a turbine a gaz a double corps pourvu d ' un palier inter-arbres
CA2605947C (fr) Canal de transition entre deux etages de turbine
EP3172411B1 (de) System zum zuführen von druckluft in einem flugzeugturbinentriebwerk mit dichtungsvorrichtung
FR3054263A1 (fr) Carter intermediaire de turbomachine d'aeronef realise d'une seule piece de fonderie avec une canalisation de lubrifiant
FR3046200B1 (fr) Turbomachine comprenant un reservoir d'huile et un echangeur air-huile associe
WO2019069011A1 (fr) Conduit de décharge d'un moyeu de carter intermédiaire pour turboréacteur d'aéronef comportant des canaux de refroidissement
EP2078822B1 (de) Gasturbinenmotor mit Ventil für die Verbindung von zwei Behältern
EP4127405A1 (de) Turbomaschine mit einer vorrichtung zur kühlung und druckbeaufschlagung einer turbine
EP4185765A1 (de) Turbine mit druckhohlräumen
FR3108655A1 (fr) Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement
FR3005991A1 (fr) Dispositif d'interface entre deux elements de turbomachine
EP4136327B1 (de) Kühlvorrichtung für turbinengehäuse
FR3119199A1 (fr) Conduit de decharge a etancheite perfectionnee
WO2020193913A1 (fr) Aube de turbomachine equipee d'un circuit de refroidissement optimise
FR3097907A1 (fr) Contrôle actif du débit de refroidissement du compresseur haute pression
FR3095003A1 (fr) Aube de turbine comportant une fente de refroidissement en plateforme
FR3092135A1 (fr) Turbomachine, telle qu’un turboreacteur d’avion
EP4041993B1 (de) Turbinendüse, die eine beschaufelung aus einem keramischen matrix-verbundwerkstoff aufweist, durch die ein metall-ventilationskreislauf verläuft
FR3107312A1 (fr) Ensemble rotatif pour turbomachine
FR3127520A1 (fr) Turbine a gaz haute-pression pour turbomachine
WO2021148739A1 (fr) Ensemble de stator de turbomachine comprenant une virole interne comprenant des parties amont et aval assemblées par translation axiale
WO2023156733A1 (fr) Turbomachine pour un aeronef
FR3097271A1 (fr) Dispositif de refroidissement d’un carter d’une turbomachine
FR3127251A1 (fr) Refroidissement d’aubes de turbine de turbomachines
FR3108362A1 (fr) Etage d’aubes à orientation variable pour une turbomachine axiale comprenant un organe de régulation du débit d’air dépendant de l’orientation des aubes

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20230220

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)