EP2148977A2 - Turbine à gaz - Google Patents

Turbine à gaz

Info

Publication number
EP2148977A2
EP2148977A2 EP08758019A EP08758019A EP2148977A2 EP 2148977 A2 EP2148977 A2 EP 2148977A2 EP 08758019 A EP08758019 A EP 08758019A EP 08758019 A EP08758019 A EP 08758019A EP 2148977 A2 EP2148977 A2 EP 2148977A2
Authority
EP
European Patent Office
Prior art keywords
rotor
shaft
gas turbine
cone
interior
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
Application number
EP08758019A
Other languages
German (de)
English (en)
Other versions
EP2148977B1 (fr
Inventor
Wilfried Weidmann
Moritz Wirth
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2148977A2 publication Critical patent/EP2148977A2/fr
Application granted granted Critical
Publication of EP2148977B1 publication Critical patent/EP2148977B1/fr
Not-in-force 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
    • 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
    • F01D25/125—Cooling of bearings
    • 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
    • F01D5/025—Fixing blade carrying members on shafts

Definitions

  • the invention relates to a gas turbine having a rotor, which comprises a turbine rotor, a shaft and a compressor rotor and in the case of a multi-shaft gas turbine is part of the low-pressure system, wherein the turbine rotor has at least one bladed rotor disk and a rotor cone leading from the shaft or a rotor shaft, and wherein the downstream end of the shaft is rotatably supported in a bearing with bearing chamber, according to the preamble of claim 1.
  • Future engine concepts require high-speed low-pressure turbines with high AN 2 , high turbine inlet temperatures and compact, short design to meet the required specifications.
  • CAVITY cavity between the last turbine stage and the turbine exhaust housing (TEC).
  • TEC turbine exhaust housing
  • the cone of the rotor connection is acted upon on both sides with air at different temperatures.
  • the temperature of the blade cooling air prevails, and behind the shaft connection at the turbine outlet housing (TEC), the temperature of the bearing blockage air. This results in temperature differences with high thermal stresses in the rotor cone and the associated rotor disk.
  • the object of the invention is to propose a gas turbine with a rotor comprising a turbine rotor, a shaft and a compressor rotor and in the case of a multi-shaft gas turbine part of the low pressure system, wherein a thermally balanced design in the region of the turbine rotor and its shaft connection high life is achieved.
  • the shaft in the region of the connection of the rotor cone, has an expansion with an enlarged inner and outer diameter, openings for the entry of cooling air into the widened interior of the shaft at its upstream end, and openings for the exit of the shaft at its downstream end Cooling air in the space between the storage chamber and rotor cone are present.
  • the extended interior of the shaft is sealed against the continuous interior of the shaft with a wall for separating cooling and sealing air. This ensures that the rotor cone and the associated running disk are subjected to cooling air at about the same temperature on both sides in the sense of a thermal compensation. A possibly exiting from the bearing chamber, the cooling air blended small amount of purging air at a lower temperature plays no significant role.
  • FIG. 1 is a partial longitudinal section through a turbine rotor with shaft connection and storage with conventional air flow
  • Fig. 2 is a partial longitudinal section through a turbine rotor with shaft connection, storage and air duct according to the present invention.
  • the turbine rotor 2 in FIG. 1 comprises three bladed running disks 6, 7 and 8. From the middle running disk 7, a rotor cone 10 leads to the associated shaft 12 and is flanged thereto.
  • the shaft 12 is rotatably supported at its downstream end in a bearing 14.
  • the bearing 14 is arranged in a bearing chamber 16, which in turn is part of a turbine outlet housing 18.
  • the bearing chamber 16 is non-hermetically sealed by means of two axially spaced seals 41, 42.
  • cooling air 22 flows.
  • sealing air 20 is guided with a relation to the cooling air 22 significantly lower temperature.
  • the sealing air 20 is guided out of the shaft 12 between the seals 41, 42 and flows partly into the bearing chamber 16, partly into the space between the turbine rotor 2 and the turbine outlet housing 18.
  • upstream of the rotor cone 10 and downstream therefrom are different Air temperatures, which leads to thermal stresses and a shortened life of the rotor connection.
  • the solution according to the invention according to FIG. 2 is characterized by design changes, which lead to a change in the air temperature distribution.
  • three running wheels 3, 4 and 5 can be seen.
  • With the rearmost disk 5 a leading to the associated shaft 11 rotor cone 9 is integrally connected.
  • the Ro- Torkonus 9 is detachably connected to the shaft 11.
  • the connection 33 (see arrow) is accomplished in the case shown via a toothing 34, two press fits 35, 36, an axial stop 37 and a screw 38.
  • the shaft 11 has in the region of the connection 33 an expansion 27 with an enlarged inner and outer diameter.
  • In the space 23 upstream or outside of the rotor cone 9 and radially outside the shaft 11 is cooling air 21 with elevated temperature.
  • sealing air 19 flows at a lower temperature.
  • cooling air 21 can enter the shaft interior.
  • openings 29 at the downstream end of the widening 27 the same cooling air 21 can again emerge from the shaft interior and enter the space 24 downstream of the rotor cone 9.
  • a separating wall 31, here in the form of a socket is installed.
  • annular interior 26 is only with the spaces 23 and 24 in direct communication.
  • the flow of sealing air 19 is concentrated in the illustrated case by means of a central tube 32 on the outer circumference of the inner space 25, which is not absolutely necessary.
  • the sealing air 19 is known manner via openings 30 out of the shaft between two axially spaced seals 39, 40, here in the form of brush seals, passed. From there, a portion of the sealing air 19 enters the interior of the storage chamber 15 of the bearing 13. The other part of the sealing air 19 enters via the non-hermetic seal 39 in the space 24 and mixes there with cooling air 21. Since the from the openings 29 exiting cooling air flow is considerably greater than the exiting from the seal 39 blocking air flow, deviates the resulting mixing temperature in the space 24 only slightly from the starting temperature of the cooling air 21. This ensures that both sides of the rotor cone 9, the connection 33 and the running disk 5 is about the same temperature.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Separation By Low-Temperature Treatments (AREA)
EP08758019A 2007-05-18 2008-05-02 Turbine à gaz Not-in-force EP2148977B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007023380A DE102007023380A1 (de) 2007-05-18 2007-05-18 Gasturbine
PCT/DE2008/000758 WO2008141609A2 (fr) 2007-05-18 2008-05-02 Turbine à gaz

Publications (2)

Publication Number Publication Date
EP2148977A2 true EP2148977A2 (fr) 2010-02-03
EP2148977B1 EP2148977B1 (fr) 2010-08-18

Family

ID=39868847

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08758019A Not-in-force EP2148977B1 (fr) 2007-05-18 2008-05-02 Turbine à gaz

Country Status (7)

Country Link
US (1) US8388303B2 (fr)
EP (1) EP2148977B1 (fr)
JP (1) JP5197736B2 (fr)
AT (1) ATE478236T1 (fr)
DE (2) DE102007023380A1 (fr)
ES (1) ES2347303T3 (fr)
WO (1) WO2008141609A2 (fr)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20120103517A (ko) * 2011-03-10 2012-09-19 한국전자통신연구원 인트라 예측 방법 및 그 장치
FR2983908B1 (fr) * 2011-12-08 2015-02-20 Snecma Systeme pour assurer l’etancheite entre une enceinte d’huile et un volume exterieur attenant et turbomachine equipee d’un tel systeme d’etancheite.
US9371737B2 (en) * 2012-02-23 2016-06-21 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
WO2014060860A1 (fr) * 2012-10-16 2014-04-24 Tusas Motor Sanayi Anonim Sirketi Système d'étanchéité à rideau d'air pour palier
WO2014163678A2 (fr) * 2013-03-12 2014-10-09 Dierksmeier Douglas D Turbine à gaz et système de compensation actif
FR3023588B1 (fr) * 2014-07-08 2016-07-15 Turbomeca Ensemble pour turbine destine a  proteger un disque de turbine contre des gradients thermiques
EP3124742B1 (fr) 2015-07-28 2018-11-07 MTU Aero Engines GmbH Turbine a gaz
US9874239B2 (en) * 2015-10-14 2018-01-23 Hamilton Sundstrand Corporation Turbine thrust shaft for air bearing cooling
JP6584687B2 (ja) * 2016-03-01 2019-10-02 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ ガスタービンエンジン内の圧縮機組立体の下流側のミッドフレームトルクディスク用の圧縮機ブリード冷却システム
GB201710314D0 (en) * 2017-06-28 2017-08-09 Rolls Royce Plc Cooling bearing chambers in a gas turbine engine
US10760494B2 (en) * 2018-03-18 2020-09-01 Raytheon Technologies Corporation Telescoping bore basket for gas turbine engine
US10968760B2 (en) * 2018-04-12 2021-04-06 Raytheon Technologies Corporation Gas turbine engine component for acoustic attenuation
IT201800006394A1 (it) * 2018-06-18 2019-12-18 Sistema di spurgo per cassa cuscino
US11118705B2 (en) 2018-08-07 2021-09-14 General Electric Company Quick connect firewall seal for firewall
DE102023108251A1 (de) * 2023-03-30 2024-10-02 MTU Aero Engines AG Rotoranordnung für eine Niederdruckturbine einer Strömungsmaschine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2680001A (en) * 1950-11-13 1954-06-01 United Aircraft Corp Arrangement for cooling turbine bearings
US3844110A (en) * 1973-02-26 1974-10-29 Gen Electric Gas turbine engine internal lubricant sump venting and pressurization system
US4296599A (en) * 1979-03-30 1981-10-27 General Electric Company Turbine cooling air modulation apparatus
US5472313A (en) * 1991-10-30 1995-12-05 General Electric Company Turbine disk cooling system
US5433584A (en) * 1994-05-05 1995-07-18 Pratt & Whitney Canada, Inc. Bearing support housing
JP4091874B2 (ja) * 2003-05-21 2008-05-28 本田技研工業株式会社 ガスタービンエンジンの二次エア供給装置
FR2858649B1 (fr) 2003-08-05 2005-09-23 Snecma Moteurs Turbine basse-pression de turbomachine
US6976679B2 (en) * 2003-11-07 2005-12-20 The Boeing Company Inter-fluid seal assembly and method therefor
FR2892454B1 (fr) * 2005-10-21 2008-01-25 Snecma Sa Dispositif de ventilation de disques de turbine dans un moteur a turbine a gaz
US7574854B2 (en) * 2006-01-06 2009-08-18 General Electric Company Gas turbine engine assembly and methods of assembling same
US7828513B2 (en) * 2006-10-05 2010-11-09 Pratt & Whitney Canada Corp. Air seal arrangement for a gas turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008141609A2 *

Also Published As

Publication number Publication date
DE102007023380A1 (de) 2008-11-20
JP2010527421A (ja) 2010-08-12
DE502008001171D1 (de) 2010-09-30
US20100104418A1 (en) 2010-04-29
EP2148977B1 (fr) 2010-08-18
WO2008141609A2 (fr) 2008-11-27
ES2347303T3 (es) 2010-10-27
US8388303B2 (en) 2013-03-05
JP5197736B2 (ja) 2013-05-15
ATE478236T1 (de) 2010-09-15
WO2008141609A3 (fr) 2009-06-11

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