FR3116557B1 - COMPRESSOR ROTOR INCLUDING A SECONDARY AIR SYSTEM SUPPLY SLOT - Google Patents

COMPRESSOR ROTOR INCLUDING A SECONDARY AIR SYSTEM SUPPLY SLOT Download PDF

Info

Publication number
FR3116557B1
FR3116557B1 FR2011996A FR2011996A FR3116557B1 FR 3116557 B1 FR3116557 B1 FR 3116557B1 FR 2011996 A FR2011996 A FR 2011996A FR 2011996 A FR2011996 A FR 2011996A FR 3116557 B1 FR3116557 B1 FR 3116557B1
Authority
FR
France
Prior art keywords
rotor
secondary air
compressor rotor
air system
end section
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
FR2011996A
Other languages
French (fr)
Other versions
FR3116557A1 (en
Inventor
Alexandre Auduberteau
Christophe Michel Georges Marcel Brillet
Pierre Chabanne
Adrien Baptiste Maxime Pique
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 FR2011996A priority Critical patent/FR3116557B1/en
Publication of FR3116557A1 publication Critical patent/FR3116557A1/en
Application granted granted Critical
Publication of FR3116557B1 publication Critical patent/FR3116557B1/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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/046—Heating, heat insulation 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
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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

Abstract

L’invention concerne un rotor (38) de compresseur comportant au moins un aubage externe (46) destiné à comprimer un gaz comburant et un système de prélèvement (36) dudit gaz comburant, aménagé dans ledit rotor (38), alimentant un système d’air secondaire de ladite turbomachine, ledit système de prélèvement comportant un canal (40) d’alimentation interne audit rotor (38), et au moins un orifice (42) communicant qui débouche sur une surface externe (44) dudit rotor (38), caractérisé en ce que le rotor (38) comporte un corps principal (50) porteur de l’aubage (46), qui comporte un tronçon d’extrémité tubulaire (52) en amont dudit aubage (46), et un manchon tubulaire (54) qui est fixé au tronçon d’extrémité tubulaire (52), et qui délimite avec ledit tronçon d’extrémité tubulaire (52) au moins une fente formant ledit au moins un orifice (42). Figure pour l'abrégé : Figure 4The invention relates to a compressor rotor (38) comprising at least one outer blading (46) intended to compress an oxidizing gas and a sampling system (36) of said oxidizing gas, arranged in said rotor (38), supplying a system of secondary air from said turbomachine, said sampling system comprising a supply channel (40) internal to said rotor (38), and at least one communicating orifice (42) which opens onto an external surface (44) of said rotor (38) , characterized in that the rotor (38) comprises a main body (50) carrying the vane (46), which comprises a tubular end section (52) upstream of the said vane (46), and a tubular sleeve ( 54) which is fixed to the tubular end section (52), and which delimits with said tubular end section (52) at least one slot forming said at least one orifice (42). Figure for abstract: Figure 4

FR2011996A 2020-11-23 2020-11-23 COMPRESSOR ROTOR INCLUDING A SECONDARY AIR SYSTEM SUPPLY SLOT Active FR3116557B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2011996A FR3116557B1 (en) 2020-11-23 2020-11-23 COMPRESSOR ROTOR INCLUDING A SECONDARY AIR SYSTEM SUPPLY SLOT

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011996A FR3116557B1 (en) 2020-11-23 2020-11-23 COMPRESSOR ROTOR INCLUDING A SECONDARY AIR SYSTEM SUPPLY SLOT
FR2011996 2020-11-23

Publications (2)

Publication Number Publication Date
FR3116557A1 FR3116557A1 (en) 2022-05-27
FR3116557B1 true FR3116557B1 (en) 2023-04-28

Family

ID=74668985

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011996A Active FR3116557B1 (en) 2020-11-23 2020-11-23 COMPRESSOR ROTOR INCLUDING A SECONDARY AIR SYSTEM SUPPLY SLOT

Country Status (1)

Country Link
FR (1) FR3116557B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS63198U (en) * 1986-06-17 1988-01-05
FR2952138B1 (en) * 2009-10-30 2012-04-20 Turbomeca METHOD FOR PROTECTING THE AIR PASSAGE INTO A COUPLING OF DRIVING PARTS IN AN UNSECURED ENVIRONMENT, AN IMPLEMENTATION COUPLING AND A ROTOR LINE EQUIPPED WITH SUCH COUPLINGS
FR3000145B1 (en) * 2012-12-21 2015-01-16 Turbomeca SEAL ASSEMBLY FOR TURBOMACHINE

Also Published As

Publication number Publication date
FR3116557A1 (en) 2022-05-27

Similar Documents

Publication Publication Date Title
CA2380779A1 (en) Discharge system for simplified control turbojet or turboprop engine
EP1568868A3 (en) High by-pass ratio turbofan
FR3116557B1 (en) COMPRESSOR ROTOR INCLUDING A SECONDARY AIR SYSTEM SUPPLY SLOT
FR2868131B1 (en) PRIME TUBE WITH CHEVRONS FOR A DOUBLE FLOW AIRCRAFT AIRCRAFT AND AIRCRAFT COMPRISING SUCH TUYERE
BE1012810A3 (en) FORCED VENTILATION GAS BURNER FOR BOILER.
FR2856729A1 (en) COOLED BLADES OF A GAS TURBINE ENGINE.
DE60308671D1 (en) CROWN BURNER TUBE
FR3086924B1 (en) TURBOMACHINE WITH SUSPENSION MEANS
FR3091332B1 (en) Turbomachine injector nose comprising a secondary fuel spiral with progressive section
FR3051844B1 (en) CHAMBER BETWEEN AN ENTRY TIP AND A SHUTTER FOR A TURBOMACHINE INJECTOR
CA2456705A1 (en) Annular platform for distributor of low-pressure turbine of jet engine
EP1508670A3 (en) Cooled vane of a gas turbine
FR3115828B1 (en) Fixing an ejection cone in a turbomachine turbine
FR3115835B1 (en) Turbomachine turbine assembly
FR2932227B1 (en) TURBOJET DOUBLE FLOW
FR3100845B1 (en) Outer nozzle member for turbomachine
EP3392569A1 (en) Fuel nozzle assembly with a flow guide assembly and a gas turbine
FR3080649B1 (en) DISCHARGE VEIN INTEGRATED IN A DAWN
FR3075866B1 (en) DEGASSING TUBE FOR A REDUCING AIRCRAFT TURBOMACHINE
RU150723U1 (en) COMBUSTION CAMERA OF A GAS TURBINE ENGINE
FR3124822B1 (en) TURBOMACHINE BLADE EQUIPPED WITH A COOLING CIRCUIT AND LOST WAX MANUFACTURING METHOD OF SUCH A BLADE
FR3049652B1 (en) AIRCRAFT TURBOMACHINE WITH DISCHARGE DEVICE
FR3089561B1 (en) IMPROVED AIR TIGHTNESS DEVICE INTENDED TO BE INTERPOSED BETWEEN A DOUBLE-FLOW AIRCRAFT TURBOMACHINE CASING ELEMENT, AND A NACELLE ELEMENT
FR3096761B1 (en) Pre-vaporization rod, combustion assembly fitted therewith and turbomachine fitted therewith
RU2670858C9 (en) Gas turbine engine annular combustion chamber

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20220527

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4