FR3125082B1 - FIRE-FIGHTING SYSTEM FOR A TURBOMACHINE INCLUDING A COOLING AIR DIFFUSER AND CORRESPONDING TURBOMACHINE - Google Patents

FIRE-FIGHTING SYSTEM FOR A TURBOMACHINE INCLUDING A COOLING AIR DIFFUSER AND CORRESPONDING TURBOMACHINE Download PDF

Info

Publication number
FR3125082B1
FR3125082B1 FR2107503A FR2107503A FR3125082B1 FR 3125082 B1 FR3125082 B1 FR 3125082B1 FR 2107503 A FR2107503 A FR 2107503A FR 2107503 A FR2107503 A FR 2107503A FR 3125082 B1 FR3125082 B1 FR 3125082B1
Authority
FR
France
Prior art keywords
turbomachine
fire
fighting system
cooling air
annular
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.)
Active
Application number
FR2107503A
Other languages
French (fr)
Other versions
FR3125082A1 (en
Inventor
Philippe Marc Pierre Yannovitch
Jean-Luc Breining
Mathieu Pierre Cladiere
Hervé Chalons
Yann Bernard Danis
Jerome Dinquel
Bruno Frelon
Gilles Maton
Bertrand Guillaume Robin Pellaton
Nicolas Christophe Perra
Florent Louis Henri Rey
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter 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 Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to FR2107503A priority Critical patent/FR3125082B1/en
Publication of FR3125082A1 publication Critical patent/FR3125082A1/en
Application granted granted Critical
Publication of FR3125082B1 publication Critical patent/FR3125082B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • 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
    • F01D25/18—Lubricating arrangements
    • 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
    • F02C7/24—Heat or noise insulation
    • F02C7/25—Fire protection or prevention
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling

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)

Abstract

L’invention concerne un système anti-incendie (30) pour une turbomachine en particulier d'aéronef, la turbomachine comprenant au moins une turbine et une cavité annulaire qui est agencée en amont d’un premier étage de la turbine et qui est alimentée en air de refroidissement via des moyens d’injection (17). Selon l’invention, le système anti-incendie comprend un diffuseur (52) annulaire destiné à être disposé dans la cavité (16) et à coopérer avec les moyens d’injection, le diffuseur s’étendant entre un bord amont (54) et un bord aval (55) suivant un axe D et étant pourvu de canaux (26) qui sont formés dans l’épaisseur d’une paroi annulaire (23) du diffuseur et qui ont un profil évolutif, les canaux débouchant chacun, d’une part dans le bord amont (54) à travers une pluralité de lumières (58), et d’autre part dans le bord aval dans une ouverture (59) annulaire, les lumières étant disposées autour de l’axe D. Figure 2The invention relates to a fire-fighting system (30) for a turbomachine in particular of an aircraft, the turbomachine comprising at least one turbine and an annular cavity which is arranged upstream of a first stage of the turbine and which is supplied with cooling air via injection means (17). According to the invention, the fire-fighting system comprises an annular diffuser (52) intended to be placed in the cavity (16) and to cooperate with the injection means, the diffuser extending between an upstream edge (54) and a downstream edge (55) along an axis D and being provided with channels (26) which are formed in the thickness of an annular wall (23) of the diffuser and which have an evolving profile, the channels each opening out, from a on the one hand in the upstream edge (54) through a plurality of slots (58), and on the other hand in the downstream edge in an annular opening (59), the slots being arranged around the axis D. Figure 2

FR2107503A 2021-07-09 2021-07-09 FIRE-FIGHTING SYSTEM FOR A TURBOMACHINE INCLUDING A COOLING AIR DIFFUSER AND CORRESPONDING TURBOMACHINE Active FR3125082B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2107503A FR3125082B1 (en) 2021-07-09 2021-07-09 FIRE-FIGHTING SYSTEM FOR A TURBOMACHINE INCLUDING A COOLING AIR DIFFUSER AND CORRESPONDING TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2107503 2021-07-09
FR2107503A FR3125082B1 (en) 2021-07-09 2021-07-09 FIRE-FIGHTING SYSTEM FOR A TURBOMACHINE INCLUDING A COOLING AIR DIFFUSER AND CORRESPONDING TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3125082A1 FR3125082A1 (en) 2023-01-13
FR3125082B1 true FR3125082B1 (en) 2024-06-07

Family

ID=78536292

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2107503A Active FR3125082B1 (en) 2021-07-09 2021-07-09 FIRE-FIGHTING SYSTEM FOR A TURBOMACHINE INCLUDING A COOLING AIR DIFFUSER AND CORRESPONDING TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3125082B1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1350471A (en) * 1971-05-06 1974-04-18 Secr Defence Gas turbine engine
US4236869A (en) * 1977-12-27 1980-12-02 United Technologies Corporation Gas turbine engine having bleed apparatus with dynamic pressure recovery
GB2118629B (en) * 1982-04-21 1985-07-17 Rolls Royce Device for passing a fluid flow eg. cooling air through a barrier eg. bolted joint
US8172506B2 (en) * 2008-11-26 2012-05-08 General Electric Company Method and system for cooling engine components
DE102015117773A1 (en) * 2015-10-19 2017-04-20 Rolls-Royce Deutschland Ltd & Co Kg Jet engine with several chambers and a bearing chamber carrier
RU2615391C1 (en) * 2016-03-11 2017-04-04 Публичное акционерное общество "Уфимское моторостроительное производственное объединение" ПАО "УМПО" Gas turbine engine cooled turbine

Also Published As

Publication number Publication date
FR3125082A1 (en) 2023-01-13

Similar Documents

Publication Publication Date Title
CA2772054C (en) Turbine engine compressor having air injectors
EP1134360A2 (en) Device for adjusting the diameter of the stator of a gas turbine engine
EP1275819A3 (en) Gas turbine stationary blade
JP2010038166A (en) Transition duct aft end frame cooling and related method
US7708525B2 (en) Industrial gas turbine blade assembly
FR2916244A1 (en) METHOD AND DEVICE FOR FACILITATING COOLING OF TURBINE ENGINES
FR2590320A1 (en) TURBOREACTOR WITH TWO FLOWS AND SEVERAL COOLING TREES THROUGH THE SECONDARY CHANNEL EXTENDING PRACTICALLY OVER THE LENGTH OF THE MACHINE
EP1907281A1 (en) Propulsion unit for aircraft and aircraft comprising at least one such propulsion unit
KR20160013019A (en) Stator vane, gas turbine provided with the same, manufacturing method of stator vane, and method for modification
US20160146016A1 (en) Rotor rim impingement cooling
FR2905166A1 (en) Annular combustion chamber for e.g. turboreactor, has cooling channel made between inner and outer fixation edges of chamber base and upstream fixation edges of inner and outer walls, where channel opens inside chamber
EP0924384A2 (en) Airfoil with leading edge cooling
US6554566B1 (en) Turbine shroud cooling hole diffusers and related method
FR3043653A1 (en) PROPELLER ASSEMBLY OF AN AIRCRAFT COMPRISING A GAS GENERATOR AND TWO BLOWERS DEPORTEES
WO2014167259A1 (en) Device for deicing an aeronautical turbomachine separator
EP1378651A3 (en) Cooled variable geometry exhaust nozzle
IL157989A (en) Integral swirl knife edge injection assembly
FR3125082B1 (en) FIRE-FIGHTING SYSTEM FOR A TURBOMACHINE INCLUDING A COOLING AIR DIFFUSER AND CORRESPONDING TURBOMACHINE
CA2436638A1 (en) Variable-geometry turbine stator blade, particularly for aircraft engines
FR2951436A1 (en) AIRCRAFT TURBOHOMOTOR HANGING MACHINE WITH CONCENTRIC HOT AIR PIPING
FR3095476B1 (en) SET FOR A TURBOMACHINE EJECTION TUBE
FR2807501A1 (en) AIR SUPPLY SYSTEM IN A ROOM OF A BUILDING
FR3101613A1 (en) PROTECTION DEVICE FOR AN ELEMENT OF AN AIR CONDITIONING SYSTEM AGAINST CONTACT WITH AN ADVERSE OBJECT
FR3129985B1 (en) AIRCRAFT TURBOMACHINE EJECTION CONE ASSEMBLY
FR3082551A1 (en) AIRCRAFT PROPULSION SYSTEM COMPRISING A FIXED INTERIOR STRUCTURE HAVING A VENTING SLOT

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20230113

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4