EP1367221A1 - Système à double injecteurs fond de chambre pour le refroidissement du flasque amont d'une turbine à haute pression - Google Patents
Système à double injecteurs fond de chambre pour le refroidissement du flasque amont d'une turbine à haute pression Download PDFInfo
- Publication number
- EP1367221A1 EP1367221A1 EP03291258A EP03291258A EP1367221A1 EP 1367221 A1 EP1367221 A1 EP 1367221A1 EP 03291258 A EP03291258 A EP 03291258A EP 03291258 A EP03291258 A EP 03291258A EP 1367221 A1 EP1367221 A1 EP 1367221A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flange
- labyrinth
- upstream
- air flow
- injectors
- 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.)
- Granted
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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
Definitions
- the invention relates to the field of ventilation of rotors of high-pressure turbine of turbojets.
- a ventilation device of a high-pressure turbine rotor of a turbomachine this turbine being disposed downstream of the combustion chamber and comprising, on the one hand, a turbine disk having an inner bore and an upstream flange for fixing it on the downstream cone of a compressor, at high pressure, and on the other hand, a flange disposed upstream of said disc and separated from it last by a cavity, said flange having a portion radially massive interior also having an inner bore, through which extends the upstream flange of said disk, and an upstream flange for its attachment on said downstream cone, said device comprising a first circuit for the blade cooling fed by a first flow of air taken from chamber bottom and delivering this first air flow into said cavity via main injectors arranged upstream of said flange and the holes of provided in said flange, and a second circuit for the cooling of the flange, fed by a second air flow at through a labyrinth of discharge located downstream of the high-pressure compressor pressure, at
- FIG. 1 shows such a high-pressure turbine rotor 1, disposed downstream of a combustion chamber 2, and which comprises a turbine disc 3 equipped with blades 4, and a flange 5 disposed upstream 3.
- the disc 3 and the flange 5 each comprise a flange upstream, referenced 3a for the disc 3 and 5a for the flange 5, for their fixing at the downstream end 6 of the downstream cone 7 of the high-pressure compressor pressure driven by the rotor 1.
- the disc 3 has an inner bore 8 traversed by the shaft 9 of a low pressure turbine, and the flange 5 has a bore 10 surrounding the flange 3a of the disk 3, and ventilation holes 11 by which a first cooling air flow C1 taken from chamber bottom is delivered into the cavity 12 separating the downstream face of the flange 5 of the upstream face of the disc 3.
- This air flow C1 of cooling circulates radially outwards and enters the 4a cells containing the feet of the blades 4 to cool them.
- This air flow is taken from the chamber floor, circulates in a duct 13 disposed in the chamber 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 into the cavity 12.
- a second cooling air flow C2 taken from the bottom of chamber circulates downstream in the chamber 16 separating the downstream cone 7 of the high pressure compressor of the inner casing 17 of the chamber of 12.
- This C2 airflow flows through a labyrinth of discharge 18 and enters the enclosure 14 from which a C2a part flows to through orifices 19 formed in the upstream flange 5a of the flange 5, passes through the bore 10 of the flange 5 to cool the part radially inner of the latter and rejoins the cooling air flow C1 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 bleed cavity 20 of the turbine rotor 1.
- a third part C2c of the third airflow C2 serves to ventilate the upstream upper 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 downstream of the second labyrinth 22, between the flange 5 and the injectors 15, and is evacuated into the cavity of upstream purge 20 of the turbine rotor 1 through a third labyrinth 24 located above the injectors 15, or mixes with the first flow C1.
- 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.
- the temperature of the upstream face of the flange downstream of second labyrinth is therefore quite high and poorly controlled. This requires to use special materials for the realization of the flange and a appropriate sizing.
- the object of the invention is to lower the temperature of the face upstream of the flange to facilitate its dimensioning in overspeed, to increase its life and to be able to use a material economic.
- said device further comprises a shunt between the first circuit and the enclosure located downstream of the second labyrinth, said bypass delivering a third air flow for the cooling of the upper face upstream of the radially inner portion of said flange, this third flow of air being pre-rotated by means of additional injectors.
- This third flow of air pre-driven and injected downstream of the labyrinth under main injectors thus reduces the relative total temperature of the air coming to cool the upstream face of the flask downstream of the second labyrinth.
- This third airflow is mixture at the leakage rate of the labyrinth under injectors and is evacuated downstream of the main turbine injectors, into the feed circuit of the high pressure turbine wheels.
- Air injected into the turbine wheel supply circuit is thus colder than that of the air injected according to the state of the art.
- the additional injectors are made under boring tangentially in the direction of rotation of the rotor.
- said bores remove air from the main injectors, and deliver it immediately downstream of the second labyrinth.
- FIG. 2 shows a turbine rotor 1 which differs from that shown in FIG. 1 by the fact that the enclosure 23 situated downstream of second labyrinth 22 is supplied with air, on the one hand, by an air leak C2c coming from the enclosure 14 via the second labyrinth 22 and, on the other hand, on the other hand, by an air flow C1a delivered by a bypass arranged between the conduit 13 delivering the first air flow C1 and the enclosure 23.
- the bypass consists of a plurality of holes 30 opening, on the one hand, to the inlet of the main injectors 15 and, on the other hand, in the enclosure 23 immediately downstream of the second labyrinth 22.
- the holes 30 are cylindrical and inclined tangentially in the direction of rotation of the rotor turbine 1.
- the part radially inner 31 of the flange 5 has a massive shape, and extends axially towards the front of the engine to the radial flange 5a which serves to fix it to the downstream end 6 of the downstream cone 7 of the compressor.
- the labyrinth 22, located under the injectors 15 is disposed at the periphery of the radial flange 5a.
- the holes 30 are substantially radial and directed towards the face upper 32 of the radially inner portion of the flange 5.
- the air flow C1a delivered by the bores 30 is at a reduced relative total temperature relative to the air of cooling of the same regions in the state of the art.
- Air flow C1a is mixed with the C2c leakage rate of the labyrinth under injectors 22 and is discharged downstream of the main injectors 15, in the circuit feeding the turbine wheel.
- the radial flange 5a has no holes to feed the annular chamber 33 located between the radially inner portion 31 of the flange 5 and the downstream flange 3a of the turbine disc 3, because the third air flow C1a is sufficient to ensure by itself the cooling of the entire flange 5.
- Air injected into the turbine wheel supply circuit for the cooling of the blades thus pre-driven is colder, than air cooling blades in a conventional ventilation.
- Gain temperature can be estimated at 15 °, which equates to a gain of specific consumption of about 0.06%.
- the cold air flow C1a delivered by the holes 30 is not influenced by variations of labyrinth games surrounding, because this flow is calibrated by the holes 30.
- Figure 3 shows in dotted line the evolution of the temperature of the bore 31 of the flange 5 in a conventional ventilation rotor of turbine, and in full lines, the evolution of the temperature at the same place with the ventilation device according to the invention according to the game of labyrinth discharge 18 expressed in mm.
- Figure 4 shows the evolution of the temperature of the bore 31 flange 5 depending on the game of the second labyrinth 22 located under the main injectors 15, with conventional ventilation (curve in dotted) and with a ventilation device according to the invention.
- the temperature in this zone with the device according to the invention is substantially constant and less than that obtained with a classical ventilation.
- Figure 5 shows the evolution of temperature at the same place of the flange, depending on the game of the third labyrinth 24, for conventional ventilation (dashed curve) and for ventilation with the device according to the invention.
- the temperature in this region is substantially constant with a ventilation device according to the invention.
- the temperature of the flange 5 in the vicinity of third labyrinth 24 is substantially constant with the device of according to the invention, and less than that obtained with a conventional ventilation, the flange 5 is less stressed by constraints thermals, and it can be made of a less expensive material and more easy to work.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims (6)
- Dispositif de ventilation d'un rotor de turbine à haute pression d'une turbomachine, cette turbine étant disposée en aval de la chambre de combustion et comportant, d'une part, un disque de turbine présentant un alésage intérieur et une bride amont pour sa fixation sur le cône aval d'un compresseur, à haute pression, et, d'autre part, un flasque disposé en amont dudit disque et séparé de ce dernier par une cavité, ledit flasque comportant une partie radialement intérieure massive ayant également un alésage intérieur, à travers lequel s'étend la bride amont dudit disque, et une bride amont pour sa fixation sur ledit cône aval, ledit dispositif comportant un premier circuit pour le refroidissement des aubes alimenté par un premier débit d'air prélevé en fond de chambre et délivrant ce premier débit d'air dans ladite cavité via des injecteurs principaux disposés en amont dudit flasque et des trous de ventilation ménagés dans ledit flasque, et un deuxième circuit pour le refroidissement du flasque, alimenté par un deuxième débit d'air au travers d'un labyrinthe de décharge situé en aval du compresseur à haute pression, une partie au moins dudit deuxième débit d'air servant à ventiler la face supérieure amont dudit flasque au travers d'un deuxième labyrinthe situé sous les injecteurs,
caractérisé par le fait que ledit dispositif comporte en outre une dérivation entre le premier circuit (13) et l'enceinte (23) située en aval du deuxième labyrinthe (22), ladite dérivation délivrant un troisième débit d'air (C1a) pour le refroidissement de la face supérieure amont (32) de la partie radialement intérieure (31) dudit flasque (5), ce troisième débit d'air (C1a) étant mis en pré-rotation au moyen d'injecteurs additionnels (30). - Dispositif selon la revendication 1, caractérisé par le fait que les injecteurs additionnels sont réalisés sous forme de perçages (30) inclinés tangentiellement dans le sens de rotation du rotor.
- Dispositif selon la revendication 2, caractérisé par le fait que lesdits perçages (30) prélèvent de l'air dans les injecteurs principaux (15).
- Dispositif selon la revendication 3, caractérisé par le fait que lesdits perçages (30) délivrent de l'air immédiatement en aval du deuxième labyrinthe.
- Dispositif selon l'une quelconque des revendications 2 à 4, caractérisé par le fait que le deuxième labyrinthe (22) est disposé entre les injecteurs principaux (15) et la bride amont (5a) du flasque (5).
- Dispositif selon la revendication 5, caractérisé par le fait que la bride amont (5a) du flasque (5) est radiale.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0206600A FR2840351B1 (fr) | 2002-05-30 | 2002-05-30 | Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre |
FR0206600 | 2002-05-30 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1367221A1 true EP1367221A1 (fr) | 2003-12-03 |
EP1367221B1 EP1367221B1 (fr) | 2006-07-26 |
Family
ID=29415148
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03291258A Expired - Lifetime EP1367221B1 (fr) | 2002-05-30 | 2003-05-27 | Système à double injecteurs fond de chambre pour le refroidissement du flasque amont d'une turbine à haute pression |
Country Status (7)
Country | Link |
---|---|
US (1) | US6787947B2 (fr) |
EP (1) | EP1367221B1 (fr) |
JP (1) | JP3940377B2 (fr) |
CA (1) | CA2430143C (fr) |
DE (1) | DE60306990T2 (fr) |
FR (1) | FR2840351B1 (fr) |
RU (1) | RU2318120C2 (fr) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1736635A2 (fr) * | 2005-05-31 | 2006-12-27 | Rolls-Royce Deutschland Ltd & Co KG | Système de transfert d'air entre le compresseur et la turbine d'une turbine à gaz |
RU2443869C2 (ru) * | 2010-02-19 | 2012-02-27 | Вячеслав Евгеньевич Беляев | Устройство для охлаждения ротора газовой турбины |
EP2942483A1 (fr) * | 2014-04-01 | 2015-11-11 | United Technologies Corporation | Injecteur de bord tangentiel ventilé pour un moteur à turbine à gaz |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2861129A1 (fr) * | 2003-10-21 | 2005-04-22 | Snecma Moteurs | Dispositif de joint a labyrinthe pour moteur a turbine a gaz |
GB0412476D0 (en) * | 2004-06-04 | 2004-07-07 | Rolls Royce Plc | Seal system |
GB2426289B (en) * | 2005-04-01 | 2007-07-04 | Rolls Royce Plc | Cooling system for a gas turbine engine |
GB0620430D0 (en) * | 2006-10-14 | 2006-11-22 | Rolls Royce Plc | A flow cavity arrangement |
FR2950656B1 (fr) * | 2009-09-25 | 2011-09-23 | Snecma | Ventilation d'une roue de turbine dans une turbomachine |
US9091173B2 (en) | 2012-05-31 | 2015-07-28 | United Technologies Corporation | Turbine coolant supply system |
US20150241067A1 (en) * | 2012-09-26 | 2015-08-27 | United Technologies Corporation | Fastened joint for a tangential on board injector |
US9388698B2 (en) * | 2013-11-13 | 2016-07-12 | General Electric Company | Rotor cooling |
WO2015160403A2 (fr) | 2014-01-20 | 2015-10-22 | United Technologies Corporation | Tuyau d'ajout conforme haute pression non arrondi, fixé sur cloison |
JP6174655B2 (ja) | 2014-10-21 | 2017-08-02 | ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation | ガスタービンエンジン用のダクテッド熱交換器システム、およびガスタービンエンジン用の熱交換器の製造方法 |
US10450956B2 (en) | 2014-10-21 | 2019-10-22 | United Technologies Corporation | Additive manufactured ducted heat exchanger system with additively manufactured fairing |
JP6484430B2 (ja) * | 2014-11-12 | 2019-03-13 | 三菱重工業株式会社 | タービンの冷却構造及びガスタービン |
EP3130750B1 (fr) * | 2015-08-14 | 2018-03-28 | Ansaldo Energia Switzerland AG | Système de refroidissement de turbines à gaz |
CN106523043B (zh) * | 2016-12-21 | 2018-04-03 | 中国南方航空工业(集团)有限公司 | 燃气轮机用分气路装置及燃气轮机 |
US11021962B2 (en) * | 2018-08-22 | 2021-06-01 | Raytheon Technologies Corporation | Turbulent air reducer for a gas turbine engine |
CN111878178B (zh) * | 2020-07-30 | 2022-10-25 | 中国航发湖南动力机械研究所 | 涡轮转盘及涡轮转子 |
CN112049688B (zh) * | 2020-08-19 | 2021-08-10 | 西北工业大学 | 一种用于等半径预旋供气系统的过预旋叶型接受孔 |
CN112855283B (zh) * | 2021-01-11 | 2022-05-20 | 中国科学院工程热物理研究所 | 一种可提高接收孔流量系数的发动机预旋系统 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2541371A1 (fr) * | 1983-02-22 | 1984-08-24 | Gen Electric | Circuit de refroidissement pour moteur a turbine a gaz |
US4807433A (en) * | 1983-05-05 | 1989-02-28 | General Electric Company | Turbine cooling air modulation |
US4822244A (en) * | 1987-10-15 | 1989-04-18 | United Technologies Corporation | Tobi |
FR2707698A1 (fr) * | 1993-07-15 | 1995-01-20 | Snecma | Turbomachine munie d'un moyen de soufflage d'air sur un élément de rotor. |
US5816776A (en) * | 1996-02-08 | 1998-10-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Labyrinth disk with built-in stiffener for turbomachine rotor |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3832090A (en) * | 1972-12-01 | 1974-08-27 | Avco Corp | Air cooling of turbine blades |
GB2108202B (en) * | 1980-10-10 | 1984-05-10 | Rolls Royce | Air cooling systems for gas turbine engines |
US5143512A (en) * | 1991-02-28 | 1992-09-01 | General Electric Company | Turbine rotor disk with integral blade cooling air slots and pumping vanes |
US5310319A (en) * | 1993-01-12 | 1994-05-10 | United Technologies Corporation | Free standing turbine disk sideplate assembly |
US5402636A (en) * | 1993-12-06 | 1995-04-04 | United Technologies Corporation | Anti-contamination thrust balancing system for gas turbine engines |
-
2002
- 2002-05-30 FR FR0206600A patent/FR2840351B1/fr not_active Expired - Fee Related
-
2003
- 2003-05-23 JP JP2003145777A patent/JP3940377B2/ja not_active Expired - Fee Related
- 2003-05-27 US US10/445,354 patent/US6787947B2/en not_active Expired - Lifetime
- 2003-05-27 DE DE60306990T patent/DE60306990T2/de not_active Expired - Lifetime
- 2003-05-27 EP EP03291258A patent/EP1367221B1/fr not_active Expired - Lifetime
- 2003-05-28 CA CA2430143A patent/CA2430143C/fr not_active Expired - Fee Related
- 2003-05-30 RU RU2003116095/06A patent/RU2318120C2/ru not_active IP Right Cessation
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2541371A1 (fr) * | 1983-02-22 | 1984-08-24 | Gen Electric | Circuit de refroidissement pour moteur a turbine a gaz |
US4807433A (en) * | 1983-05-05 | 1989-02-28 | General Electric Company | Turbine cooling air modulation |
US4822244A (en) * | 1987-10-15 | 1989-04-18 | United Technologies Corporation | Tobi |
FR2707698A1 (fr) * | 1993-07-15 | 1995-01-20 | Snecma | Turbomachine munie d'un moyen de soufflage d'air sur un élément de rotor. |
US5816776A (en) * | 1996-02-08 | 1998-10-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Labyrinth disk with built-in stiffener for turbomachine rotor |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1736635A2 (fr) * | 2005-05-31 | 2006-12-27 | Rolls-Royce Deutschland Ltd & Co KG | Système de transfert d'air entre le compresseur et la turbine d'une turbine à gaz |
EP1736635A3 (fr) * | 2005-05-31 | 2009-10-14 | Rolls-Royce Deutschland Ltd & Co KG | Système de transfert d'air entre le compresseur et la turbine d'une turbine à gaz |
RU2443869C2 (ru) * | 2010-02-19 | 2012-02-27 | Вячеслав Евгеньевич Беляев | Устройство для охлаждения ротора газовой турбины |
EP2942483A1 (fr) * | 2014-04-01 | 2015-11-11 | United Technologies Corporation | Injecteur de bord tangentiel ventilé pour un moteur à turbine à gaz |
US10697321B2 (en) | 2014-04-01 | 2020-06-30 | Raytheon Technologies Corporation | Vented tangential on-board injector for a gas turbine engine |
US10920611B2 (en) | 2014-04-01 | 2021-02-16 | Raytheon Technologies Corporation | Vented tangential on-board injector for a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
US6787947B2 (en) | 2004-09-07 |
DE60306990D1 (de) | 2006-09-07 |
FR2840351B1 (fr) | 2005-12-16 |
FR2840351A1 (fr) | 2003-12-05 |
CA2430143A1 (fr) | 2003-11-30 |
US20030223893A1 (en) | 2003-12-04 |
RU2318120C2 (ru) | 2008-02-27 |
JP3940377B2 (ja) | 2007-07-04 |
DE60306990T2 (de) | 2007-03-08 |
JP2004132352A (ja) | 2004-04-30 |
CA2430143C (fr) | 2010-10-05 |
EP1367221B1 (fr) | 2006-07-26 |
RU2003116095A (ru) | 2005-01-27 |
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