WO2004003347A1 - Gas turbine ventilation circuitry - Google Patents
Gas turbine ventilation circuitry Download PDFInfo
- Publication number
- WO2004003347A1 WO2004003347A1 PCT/FR2003/001958 FR0301958W WO2004003347A1 WO 2004003347 A1 WO2004003347 A1 WO 2004003347A1 FR 0301958 W FR0301958 W FR 0301958W WO 2004003347 A1 WO2004003347 A1 WO 2004003347A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- flange
- upstream
- labyrinth
- injectors
- labyrinths
- Prior art date
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
-
- 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
Definitions
- the invention relates to the field of ventilation of the high pressure turbine of an aviation turbomachine. More specifically, it relates to a turbomachine comprising a sealing device between the turbine rotor and the interior casing of the combustion chamber, said turbine rotor comprising, on the one hand, a turbine disc having an upstream flange for fixing to the downstream cone of a compressor and, on the other hand, a flange disposed upstream of said disc and separated from the latter by a cavity, said flange having an internal bore traversed by the upstream flange of said disc and an upstream flange for fixing it on said downstream cone, a first air circuit secured to said casing for delivering a first flow of cooling air into said cavity via main injectors and holes made in said flange, said sealing device comprising a discharge labyrinth between the downstream cone and said inner casing, a labyrinth of main sub-injectors disposed between the flange and the inner wall of the first circuit air and at least one labyrinth
- FIG. 1 shows such a high pressure turbine rotor 1, arranged downstream of a combustion chamber 2, and which comprises a turbine disc 3 equipped with blades 4, and a flange 5 arranged upstream of the disc 3.
- the disc 3 and the flange 5 each have an upstream flange, referenced 3a for the disc 3 and 5a for the flange 5, for their attachment to the downstream end 6 of the downstream cone 7 of the high pressure compressor driven by the rotor 1.
- the disc 3 has an internal bore 8 through which the shaft 9 of a low pressure turbine passes, and the flange 5 has an internal bore 10 surrounding the flange 3a of the disc 3, and ventilation holes 11 through which a first flow cooling air Cl taken from the bottom of the chamber is delivered into the cavity 12 separating the downstream face of the flange 5 of the upstream face of the disc 3.
- This cooling air flow C1 circulates radially outward and enters the cells 4a containing the feet of the blades 4 in order to cool the latter.
- This air flow is taken from the chamber bottom, circulates in a duct 13 disposed in the enclosure 14 separating the flange 5 from the chamber bottom and is rotated by injectors 15 in order to lower the temperature of the air delivered to the cavity 12.
- a second cooling air flow C2 taken from the chamber bottom circulates downstream in the enclosure 16 separating the downstream cone 7 of the high pressure compressor from the inner casing 17 of the combustion chamber 2.
- This air flow C2 flows through a discharge labyrinth 18 and enters the enclosure 14 from which part C2a flows through orifices 19 formed in the upstream flange 5a of the flange 5, passes through the bore 10 of the flange 5 in order to cool the radially inner part of the latter and rejoins the air flow C1 for cooling the blades 4.
- Another part C2b of the second air flow C2 cools the upstream face of the flange 5, bypasses the injectors 15 and is discharged into the upstream purge cavity 20 of the turbine rotor 1.
- a third part C2c of the third air flow C2 serves to ventilate the upper upstream face 21 of the flange 5 through a second labyrinth 22 located under the injectors 15.
- This third part C2c enters the enclosure 23 located at downstream of the second labyrinth 22, between the flange 5 and the injectors 15, and is discharged into the upstream purge cavity 20 of the turbine rotor 1 through a third labyrinth 24 located above the injectors 15, or comes to mix with the first air flow Cl.
- the second air flow C2 serves to cool the downstream cone 7, the barrel connecting the high pressure compressor to the high pressure turbine, and the flange 5.
- This second air flow circulating axially in an annular space delimited by fixed walls integral with the chamber and movable walls in rotation integral with the rotor, undergoes heating due to the powers dissipated between the rotor and the stator.
- the air flow C2c used to cool the flange downstream of the second labyrinth 22 located under the injectors 15, is difficult to control because it undergoes the changes in the games of the discharge labyrinth 18, the second labyrinth 22 and the third labyrinth 24 located above the injectors 15, during operation and during the life of the engine.
- the latter comprises three successive wipers formed on a bent portion 25 of the flange 5, which cooperate with sealing elements 26 integral with an annular structure 27 interposed between the outer wall 28 of the duct 13 and the upstream part 29 of the inner casing 27.
- This type of labyrinth with three wipers has an appreciable mass, and due to centrifugal forces requires the flange 5 to be attached to the upstream face of the disc turbine 3 by means of a dog clutch 30.
- the first object of the invention is to modify the sealing device upstream of the main injectors, in order to allow a reduction in the upstream flange.
- a second object of the invention is to allow a reduction in the purge flow upstream of the rotor and thereby a specific consumption gain.
- a third object of the invention is to increase the pressure levels in the cooling air supply circuit of the turbine wheel, which is favorable for the cooling of the blades.
- the first object of the invention is achieved by the fact that the sealing device comprises downstream of the main injectors in the direction of circulation of the second cooling air flow, at least three radially spaced labyrinths arranged between the flange and the annular structure.
- said three labyrinths each have a single wiper.
- Each of these labyrinths has a light structure, which allows the elimination of dog clutching.
- the second and third objects of the invention are achieved by the fact that one of the annular cavities between two consecutive labyrinths among said three labyrinths is supplied by cooling air taken from the second circuit upstream of the labyrinth of sub-injectors. This third flow rate is advantageously rotated in the direction of rotation of the rotor by secondary injectors.
- these secondary injectors are produced in the form of inclined bores, formed in the annular structure.
- FIG. 1 is an axial half-section of a high-pressure turbine rotor of a turbojet engine, which shows the cooling air circuits and the various sealing labyrinths according to the prior art, and
- FIG. 2 is an axial half-section of a turbojet turbine rotor which shows the arrangement of the flange and labyrinths, according to the invention, upstream of the main injectors.
- FIG 2 there is shown by reference 1 a high pressure turbine rotor disposed downstream of a combustion chamber 2, which comprises a turbine disc 3 equipped at its periphery with blades 4, and a flange 5 disposed upstream of the disc 3.
- the disc 3 and the flange 5 delimit between them a cavity 12 supplied with cooling air via main injectors 15 and holes 11 formed in the flange 5 in view of the main injectors 15.
- the main injectors 15 are inclined relative to the axis of rotation of the turbine in order to direct the air supplied in the direction of rotation of the turbine rotor 1.
- the main injectors 15 are supplied with air taken from the bottom of the combustion chamber by means of an annular duct 13 which has a radially inner wall 13a and a radially outer wall 28.
- a second labyrinth is arranged under the main injectors, between the radially inner wall 13a and the flange 5.
- An annular structure 27 is interposed between the radially outer wall 28 of the duct 13 and the upstream part 29 of the inside casing of the combustion chamber 2.
- These three labyrinths 31, 32 and 33 each have a single wiper, and define between the enclosure 23, in which the main injectors 15 and the upstream purge cavity 2 emerge, two intermediate cavities 34 and 35.
- the labyrinths 31, 32 and 33 could be replaced by other rotor / stator sealing systems, such as brush seals and one could also have a mixture of labyrinths and brush seals without departing from the scope of the invention. .
- Bypass 36 formed through the annular conduit 13 connect the chamber 14 chamber bottom disposed downstream of the second labyrinth located under the main injectors with the chamber 37 located radially outside the annular conduit 13.
- Holes inclined 38 relative to the axis of rotation of the turbine rotor 1 are formed in the annular structure 27 between the enclosure 36 and the cavity 35 located immediately upstream of the purge cavity 20.
- the holes 38 are inclined in the direction of rotation of the turbine rotor 1 in order to decrease the temperature of the cooling air of the radially outer wall of the flange 5. Because the air entering the cavity 35 through the holes 38 is taken upstream of the sub-injector labyrinth, the pressure in the cavity 35 is increased and the leakage rate through the labyrinths 31 and 32 is reduced. This results in an increase in the pressure in the cavities 23 and 12, which is favorable for the cooling of the blades 4.
- the holes 38 are calibrated so as to reduce the leakage rate in the purge cavity 20, which makes it possible to reduce the specific consumption by about 0.1%.
- the holes 38 constitute a system of secondary injectors allowing most of the air in the chamber cavity to be used, via the branches 36 for cooling the top of the upstream flange. This air flow crosses the cooling air of the blades, which is why it is commonly called shunt.
- the inclined holes 38 can be replaced by injectors with vanes or inclined tubes, mounted in the wall of the annular structure 27 without departing from the scope of the invention.
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)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA002490619A CA2490619A1 (en) | 2002-06-27 | 2003-06-25 | Gas turbine ventilation circuitry |
US10/517,613 US20050201859A1 (en) | 2002-06-27 | 2003-06-25 | Gas turbine ventilation circuitry |
JP2004516864A JP2005530956A (en) | 2002-06-27 | 2003-06-25 | Gas turbine ventilation circuit |
AU2003253082A AU2003253082A1 (en) | 2002-06-27 | 2003-06-25 | Gas turbine ventilation circuitry |
EP03761639A EP1552111A1 (en) | 2002-06-27 | 2003-06-25 | Gas turbine ventilation circuitry |
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 |
FR02/07979 | 2002-06-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004003347A1 true WO2004003347A1 (en) | 2004-01-08 |
Family
ID=29724922
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2003/001958 WO2004003347A1 (en) | 2002-06-27 | 2003-06-25 | Gas turbine ventilation circuitry |
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) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2963377A2 (en) | 2014-06-30 | 2016-01-06 | Marc Hartmann | Apparatus for releasing fluid to the atmosphere |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1508672A1 (en) | 2003-08-21 | 2005-02-23 | Siemens Aktiengesellschaft | Segmented fastening ring for a turbine |
FR2861129A1 (en) * | 2003-10-21 | 2005-04-22 | Snecma Moteurs | Labyrinth seal device for gas turbine device, has ventilation orifices provided at proximity of fixation unit, and compressor with last stage from which upward air is collected immediately |
FR2869094B1 (en) * | 2004-04-15 | 2006-07-21 | Snecma Moteurs Sa | ANNULAR COMBUSTION CHAMBER OF INTERNAL FLANGE TURBOMACHINE WITH IMPROVED FASTENING |
GB0412476D0 (en) | 2004-06-04 | 2004-07-07 | Rolls Royce Plc | Seal system |
US20090238683A1 (en) * | 2008-03-24 | 2009-09-24 | United Technologies Corporation | Vane with integral inner air seal |
EP3124742B1 (en) * | 2015-07-28 | 2018-11-07 | MTU Aero Engines GmbH | Gas turbine |
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 |
FR3127979B1 (en) * | 2021-10-11 | 2024-05-31 | Safran Aircraft Engines | Axial lip seal for turbomachine |
FR3129426B1 (en) | 2021-11-19 | 2024-08-30 | 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 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2541371A1 (en) * | 1983-02-22 | 1984-08-24 | Gen Electric | COOLING CIRCUIT FOR GAS TURBINE ENGINE |
EP0501066A1 (en) * | 1991-02-28 | 1992-09-02 | General Electric Company | Turbine rotor disk with integral blade cooling air slots and pumping vanes |
US5402636A (en) * | 1993-12-06 | 1995-04-04 | United Technologies Corporation | Anti-contamination thrust balancing system for gas turbine engines |
FR2744761A1 (en) * | 1996-02-08 | 1997-08-14 | Snecma | LABYRINTH DISK WITH INCORPORATED STIFFENER FOR TURBOMACHINE ROTOR |
EP1211381A1 (en) * | 2000-11-30 | 2002-06-05 | Snecma Moteurs | Cover plate for a bladed rotor disk |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5984630A (en) * | 1997-12-24 | 1999-11-16 | General Electric Company | Reduced windage high pressure turbine forward outer seal |
FR2831918B1 (en) * | 2001-11-08 | 2004-05-28 | Snecma Moteurs | STATOR FOR TURBOMACHINE |
-
2002
- 2002-06-27 FR FR0207979A patent/FR2841591B1/en not_active Expired - Lifetime
-
2003
- 2003-06-25 AU AU2003253082A patent/AU2003253082A1/en not_active Abandoned
- 2003-06-25 EP EP03761639A patent/EP1552111A1/en not_active Withdrawn
- 2003-06-25 WO PCT/FR2003/001958 patent/WO2004003347A1/en not_active Application Discontinuation
- 2003-06-25 RU RU2005101887/06A patent/RU2005101887A/en not_active Application Discontinuation
- 2003-06-25 CA CA002490619A patent/CA2490619A1/en not_active Abandoned
- 2003-06-25 US US10/517,613 patent/US20050201859A1/en not_active Abandoned
- 2003-06-25 JP JP2004516864A patent/JP2005530956A/en not_active Withdrawn
-
2004
- 2004-12-16 MA MA28009A patent/MA27255A1/en unknown
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2541371A1 (en) * | 1983-02-22 | 1984-08-24 | Gen Electric | COOLING CIRCUIT FOR GAS TURBINE ENGINE |
EP0501066A1 (en) * | 1991-02-28 | 1992-09-02 | General Electric Company | Turbine rotor disk with integral blade cooling air slots and pumping vanes |
US5402636A (en) * | 1993-12-06 | 1995-04-04 | United Technologies Corporation | Anti-contamination thrust balancing system for gas turbine engines |
FR2744761A1 (en) * | 1996-02-08 | 1997-08-14 | Snecma | LABYRINTH DISK WITH INCORPORATED STIFFENER FOR TURBOMACHINE ROTOR |
EP1211381A1 (en) * | 2000-11-30 | 2002-06-05 | Snecma Moteurs | Cover plate for a bladed rotor disk |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2963377A2 (en) | 2014-06-30 | 2016-01-06 | Marc Hartmann | Apparatus for releasing fluid to the atmosphere |
Also Published As
Publication number | Publication date |
---|---|
FR2841591B1 (en) | 2006-01-13 |
RU2005101887A (en) | 2005-06-27 |
JP2005530956A (en) | 2005-10-13 |
US20050201859A1 (en) | 2005-09-15 |
EP1552111A1 (en) | 2005-07-13 |
CA2490619A1 (en) | 2004-01-08 |
FR2841591A1 (en) | 2004-01-02 |
MA27255A1 (en) | 2005-03-01 |
AU2003253082A1 (en) | 2004-01-19 |
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