RU2005101887A - GAS-TURBINE ENGINE TURBINE VENTILATION CIRCUITS - Google Patents

GAS-TURBINE ENGINE TURBINE VENTILATION CIRCUITS Download PDF

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Publication number
RU2005101887A
RU2005101887A RU2005101887/06A RU2005101887A RU2005101887A RU 2005101887 A RU2005101887 A RU 2005101887A RU 2005101887/06 A RU2005101887/06 A RU 2005101887/06A RU 2005101887 A RU2005101887 A RU 2005101887A RU 2005101887 A RU2005101887 A RU 2005101887A
Authority
RU
Russia
Prior art keywords
flange
turbine engine
gas turbine
labyrinth
labyrinths
Prior art date
Application number
RU2005101887/06A
Other languages
Russian (ru)
Inventor
Сильви КУЛОН (FR)
Сильви КУЛОН
Жан-Филипп МАФФР (FR)
Жан-Филипп МАФФР
Жан-Клод ТАЙЯН (FR)
Жан-Клод ТАЙЯН
Original Assignee
Снекма Мотер (Fr)
Снекма Мотер
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 Снекма Мотер (Fr), Снекма Мотер filed Critical Снекма Мотер (Fr)
Publication of RU2005101887A publication Critical patent/RU2005101887A/en

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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
    • 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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F02C7/28—Arrangement of seals
    • 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

Claims (5)

1. Газотурбинный двигатель, содержащий уплотнительное устройство между ротором (1) турбины и внутренним картером камеры сгорания, при этом ротор турбины содержит, с одной стороны, диск (3) турбины, содержащий передний поводок для его крепления на заднем конусе компрессора, и, с другой стороны, фланец (5), установленный перед упомянутым диском и отделенный от последнего полостью (12), при этом упомянутый фланец содержит внутреннее отверстие, через которое проходит передний поводок упомянутого диска и передний поводок для его крепления на упомянутом заднем конусе, первый воздушный контур, жестко соединенный с упомянутым внутренним картером, для подачи первого охлаждающего воздушного потока в упомянутую полость (12) через главные форсунки и отверстия, выполненные в упомянутом фланце, при этом упомянутое уплотнительное устройство содержит разгрузочный лабиринт между задним конусом и упомянутым внутренним картером, подфорсуночный лабиринт, расположенный между фланцем и внутренней стенкой первого воздушного контура, и, по меньшей мере, один надфорсуночный лабиринт, расположенный между фланцем и кольцевой конструкцией (27), выполненной между наружной стенкой первого воздушного контура и упомянутым внутренним картером, при этом второй охлаждающий воздушный поток циркулирует во втором контуре, формируемом закрытыми пространствами, ограниченными упомянутым внутренним картером и упомянутым ротором, через упомянутые лабиринты и частично удаляется в переднюю выпускную полость упомянутого диска, отличающийся тем, что уплотнительное устройство содержит на выходе главных форсунок по направлению циркуляции второго охлаждающего воздушного потока, по меньшей мере, три лабиринта (31, 32, 33), радиально отстоящие друг от друга и расположенные между фланцем (5) и кольцевой конструкцией (27).1. A gas turbine engine containing a sealing device between the rotor (1) of the turbine and the internal crankcase of the combustion chamber, while the turbine rotor contains, on the one hand, a turbine disk (3) containing a front leash for mounting it on the rear cone of the compressor, and, c on the other hand, a flange (5) mounted in front of said disk and separated from the latter by a cavity (12), said flange comprising an inner hole through which a front leash of said disk and a front leash for attaching it to said that rear cone, a first air circuit rigidly connected to said inner crankcase for supplying a first cooling air stream to said cavity (12) through main nozzles and openings made in said flange, wherein said sealing device comprises an unloading labyrinth between the rear cone and said inner crankcase, a sub-nozzle labyrinth located between the flange and the inner wall of the first air circuit, and at least one super-nozzle labyrinth located between the flange and the annular structure (27), made between the outer wall of the first air circuit and said inner crankcase, while the second cooling air stream circulates in the second circuit, formed by closed spaces defined by said inner crankcase and said rotor, through the labyrinths and partially removed in the front exhaust cavity of the aforementioned disk, characterized in that the sealing device contains at the output of the main nozzles in the direction of circulation of the second lazhdayuschego airflow, at least three of the labyrinth (31, 32, 33), radially spaced from each other and disposed between the flange (5) and an annular structure (27). 2. Газотурбинный двигатель по п.1, отличающийся тем, что каждый из упомянутых трех лабиринтов содержит только одну перемычку.2. The gas turbine engine according to claim 1, characterized in that each of the three labyrinths contains only one jumper. 3. Газотурбинный двигатель по одному из п.1 или 2, отличающийся тем, что в одну из кольцевых полостей (35), заключенных между двумя смежными лабиринтами (32, 33) из упомянутых трех лабиринтов, подают охлаждающий воздух, отбираемый во втором контуре на входе подфорсуночного лабиринта.3. A gas turbine engine according to one of claims 1 or 2, characterized in that in one of the annular cavities (35) enclosed between two adjacent labyrinths (32, 33) of the three labyrinths, cooling air is drawn, taken in the second circuit to the entrance of the sub-maze labyrinth. 4. Газотурбинный двигатель по п.3, отличающийся тем, что охлаждающий воздушный поток выходит из вспомогательных форсунок, которые приводят его во вращение в направлении вращения ротора.4. The gas turbine engine according to claim 3, characterized in that the cooling air stream leaves the auxiliary nozzles, which cause it to rotate in the direction of rotation of the rotor. 5. Газотурбинный двигатель по п.4, отличающийся тем, что вспомогательные форсунки выполнены в виде сквозных наклонных отверстий (38) в кольцевой конструкции (27).5. A gas turbine engine according to claim 4, characterized in that the auxiliary nozzles are made in the form of through inclined holes (38) in an annular structure (27).
RU2005101887/06A 2002-06-27 2003-06-25 GAS-TURBINE ENGINE TURBINE VENTILATION CIRCUITS RU2005101887A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0207979A FR2841591B1 (en) 2002-06-27 2002-06-27 VENTILATION CIRCUITS OF THE TURBINE OF A TURBOMACHINE
FR0207979 2002-06-27

Publications (1)

Publication Number Publication Date
RU2005101887A true RU2005101887A (en) 2005-06-27

Family

ID=29724922

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2005101887/06A RU2005101887A (en) 2002-06-27 2003-06-25 GAS-TURBINE ENGINE TURBINE VENTILATION CIRCUITS

Country Status (9)

Country Link
US (1) US20050201859A1 (en)
EP (1) EP1552111A1 (en)
JP (1) JP2005530956A (en)
AU (1) AU2003253082A1 (en)
CA (1) CA2490619A1 (en)
FR (1) FR2841591B1 (en)
MA (1) MA27255A1 (en)
RU (1) RU2005101887A (en)
WO (1) WO2004003347A1 (en)

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FR2869094B1 (en) * 2004-04-15 2006-07-21 Snecma Moteurs Sa ANNULAR COMBUSTION CHAMBER OF INTERNAL FLANGE TURBOMACHINE WITH IMPROVED FASTENING
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US20090238683A1 (en) * 2008-03-24 2009-09-24 United Technologies Corporation Vane with integral inner air seal
EP2963377A3 (en) 2014-06-30 2016-04-13 Marc Hartmann Apparatus for releasing fluid to the atmosphere
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JP6209199B2 (en) * 2015-12-09 2017-10-04 三菱日立パワーシステムズ株式会社 Seal fin, seal structure, turbomachine and method of manufacturing seal fin
US10408077B2 (en) * 2017-01-26 2019-09-10 United Tehnologies Corporation Gas turbine seal
CN107131009B (en) * 2017-05-16 2019-02-15 中国科学院工程热物理研究所 A kind of self-locking seal structure of turbomachine and the engine with it
CN108716423B (en) * 2018-05-08 2020-06-02 中国科学院工程热物理研究所 Sealing structure for fish mouth between turbine rotor and stator of gas turbine
FR3101670B1 (en) 2019-10-08 2021-10-08 Safran Aircraft Engines Injector for a high pressure turbine
US11421597B2 (en) 2019-10-18 2022-08-23 Pratt & Whitney Canada Corp. Tangential on-board injector (TOBI) assembly
US11415016B2 (en) * 2019-11-11 2022-08-16 Rolls-Royce Plc Turbine section assembly with ceramic matrix composite components and interstage sealing features
FR3115562A1 (en) 2020-10-26 2022-04-29 Safran Aircraft Engines Turbomachinery Turbine Cooling Air Injector
FR3118891B1 (en) 2021-01-15 2023-03-24 Safran Aircraft Engines Manufacture of a turbine injector by laser fusion on a powder bed
US11598265B2 (en) * 2021-02-03 2023-03-07 Pratt & Whitney Canada Corp. Tangential on-board injector
FR3126140B1 (en) 2021-08-11 2024-04-26 Safran Aircraft Engines Sealing flange for turbomachine turbine
FR3127521B1 (en) 2021-09-24 2023-12-15 Safran Aircraft Engines COOLING AIR INJECTION HOUSING FOR TURBOMACHINE TURBINE
FR3127518A1 (en) 2021-09-28 2023-03-31 Safran Helicopter Engines TURBOMACHINE STAGE INCLUDING AT LEAST ONE SEAL RING
FR3127979A1 (en) * 2021-10-11 2023-04-14 Safran Aircraft Engines Axial wiper seal for turbomachine
FR3129426A1 (en) 2021-11-19 2023-05-26 Safran Aircraft Engines Turbomachine with passive regulation of the ventilation flow of the turbine injectors
CN116537895B (en) * 2023-07-04 2023-09-15 中国航发四川燃气涡轮研究院 Pre-rotation air supply system with comb gap control

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Also Published As

Publication number Publication date
FR2841591A1 (en) 2004-01-02
AU2003253082A1 (en) 2004-01-19
CA2490619A1 (en) 2004-01-08
FR2841591B1 (en) 2006-01-13
MA27255A1 (en) 2005-03-01
US20050201859A1 (en) 2005-09-15
JP2005530956A (en) 2005-10-13
EP1552111A1 (en) 2005-07-13
WO2004003347A1 (en) 2004-01-08

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FA92 Acknowledgement of application withdrawn (lack of supplementary materials submitted)

Effective date: 20070925