EP0859128A1 - Disque de turbine avec canaux refroidissement - Google Patents

Disque de turbine avec canaux refroidissement Download PDF

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Publication number
EP0859128A1
EP0859128A1 EP98101046A EP98101046A EP0859128A1 EP 0859128 A1 EP0859128 A1 EP 0859128A1 EP 98101046 A EP98101046 A EP 98101046A EP 98101046 A EP98101046 A EP 98101046A EP 0859128 A1 EP0859128 A1 EP 0859128A1
Authority
EP
European Patent Office
Prior art keywords
cooling air
disk
disc
groove
turbine impeller
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
EP98101046A
Other languages
German (de)
English (en)
Other versions
EP0859128B1 (fr
Inventor
Thomas Schillinger
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
BMW Rolls Royce 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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0859128A1 publication Critical patent/EP0859128A1/fr
Application granted granted Critical
Publication of EP0859128B1 publication Critical patent/EP0859128B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages 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
    • 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 a turbine impeller disk from the disk end face outgoing cooling air channels, which in the disc grooves, in which air-cooled turbine blades are used.
  • the environment is referred to DE 29 47 521 A1 and DE 34 44 586 A1.
  • the cooling air supply has channels in the turbine impeller discs basically proven.
  • a second turbine impeller disk which is arranged after a first impeller, cooling air can be fed by part of the in the disc grooves of the first Impeller disk incoming cooling air flow through these disk grooves quasi backwards into the space between the first and second Impeller disc is discharged.
  • locking plates which secure the blades inserted into the disk grooves, corresponding Through openings may be provided.
  • cooling air duct can namely with regard to its cross-sectional area not be designed to be of any size, because this is the area of the mouth the spatial fields of the individual stress concentrations for the Superimposed circumferential tensions and locally excessive stress amplitudes can cause what in terms of operational fatigue strength is undesirable.
  • FIG. 1 a partial longitudinal section being shown in FIG. 1 and a partial view of a preferred exemplary embodiment of a turbine impeller disk according to the invention in FIG. 2.
  • FIG. 3 is used to explain the physical relationships and shows in a diagram the stress concentration (plotted on the ordinate) as a function of the dimensionless hole spacing P / D plotted on the abscissa for a row arrangement of holes with the diameter D, the dimension P from each other are spaced.
  • a plurality of disk grooves 2 each having a fir tree profile has, in each of which a turbine blade 3 is inserted. Every turbine blade 3 is air cooled, i.e. H. are not in each turbine blade 3 Cooling air channels shown are provided, in which from the disc groove 2nd a cooling air flow can enter.
  • This cooling air flow passes into each disk groove 2 via at least two Cooling air channels 4, which start from the front face 1a - the corresponding one Mouth opening is designated by the reference number 7b - and in Are guided inside the disc to the respective disc groove 2, where they are in Groove bottom 2a open (mouth opening 7a).
  • a larger amount of cooling air flow can be brought in than over a single cooling air duct 4 with the same cross-sectional area Q, as this is known and common in the prior art.
  • FIG. 3 First of all, the view of a component 10 is shown, in which a row of holes 11, each having a diameter D, is provided. The individual holes 11 are spaced apart by a dimension P. The main stress direction along the row of holes 11 is shown by the arrow 12. In the diagram according to FIG. 3, the stress concentration factor is now plotted on the ordinate and on the abscissa the dimensionless hole spacing P / D.
  • the stress concentration factor also decreases as the dimensionless hole spacing P / D decreases.
  • the parameter P / D according to FIG. 3 is reduced to 0.707 times its original value, so that the stress concentration factor also decreases accordingly.
  • the absolute peak stress resulting from the (potential theoretical) superposition of the individual stress fields around the bore and groove can be reduced to a considerable extent, which is desirable in view of the fatigue strength of a turbine disk.
  • Impeller disk introduced cooling air flow can be used a second impeller disc connected downstream of this first impeller disc 1 to supply cooling air (not shown).
  • the turbine blades 3 in the impeller disk 1 locking plates 6 can in the range Disc grooves 2 corresponding through openings 9 for a partial cooling air flow be provided, each via one in the foot of the turbine blade provided channel 9 'with a connecting to the cooling air channel 4, provided in the blade root cooling air duct 4 ' are.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98101046A 1997-02-13 1998-01-22 Disque de turbine avec canaux refroidissement Expired - Lifetime EP0859128B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19705442 1997-02-13
DE19705442A DE19705442A1 (de) 1997-02-13 1997-02-13 Turbinen-Laufradscheibe mit Kühlluftkanälen

Publications (2)

Publication Number Publication Date
EP0859128A1 true EP0859128A1 (fr) 1998-08-19
EP0859128B1 EP0859128B1 (fr) 2000-04-05

Family

ID=7820090

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98101046A Expired - Lifetime EP0859128B1 (fr) 1997-02-13 1998-01-22 Disque de turbine avec canaux refroidissement

Country Status (3)

Country Link
US (1) US6022190A (fr)
EP (1) EP0859128B1 (fr)
DE (2) DE19705442A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1004748A3 (fr) * 1998-11-27 2001-10-17 Rolls-Royce Deutschland Ltd & Co KG Rotor pour une turbomachine
FR2987864A1 (fr) * 2012-03-12 2013-09-13 Snecma Turbomachine a disques de rotor et moyen de guidage radial d'air, et compresseur et/ou turbine avec de tels disques et moyen de guidage.
US8708657B2 (en) 2010-01-22 2014-04-29 Rolls-Royce Plc Rotor Disc

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6428270B1 (en) * 2000-09-15 2002-08-06 General Electric Company Stage 3 bucket shank bypass holes and related method
US7465149B2 (en) * 2006-03-14 2008-12-16 Rolls-Royce Plc Turbine engine cooling
EP1892375A1 (fr) * 2006-08-23 2008-02-27 Siemens Aktiengesellschaft Disque de rotor d'un moteur à turbine avec passage de refroidissement
US20090110561A1 (en) * 2007-10-29 2009-04-30 Honeywell International, Inc. Turbine engine components, turbine engine assemblies, and methods of manufacturing turbine engine components
JP4939461B2 (ja) * 2008-02-27 2012-05-23 三菱重工業株式会社 タービンディスク及びガスタービン
JP4981709B2 (ja) * 2008-02-28 2012-07-25 三菱重工業株式会社 ガスタービン及びディスク並びにディスクの径方向通路形成方法
DE102009007468A1 (de) * 2009-02-04 2010-08-19 Mtu Aero Engines Gmbh Integral beschaufelte Rotorscheibe für eine Turbine
US8087871B2 (en) * 2009-05-28 2012-01-03 General Electric Company Turbomachine compressor wheel member
US8591180B2 (en) * 2010-10-12 2013-11-26 General Electric Company Steam turbine nozzle assembly having flush apertures
FR2969209B1 (fr) * 2010-12-21 2019-06-21 Safran Aircraft Engines Etage de turbine pour turbomachine d'aeronef, presentant une etancheite amelioree entre le flasque aval et les aubes de la turbine
US10683756B2 (en) 2016-02-03 2020-06-16 Dresser-Rand Company System and method for cooling a fluidized catalytic cracking expander
US10519857B2 (en) 2016-10-24 2019-12-31 Rolls-Royce Corporation Disk with lattice features adapted for use in gas turbine engines
US10458242B2 (en) * 2016-10-25 2019-10-29 Pratt & Whitney Canada Corp. Rotor disc with passages
DE102016124806A1 (de) * 2016-12-19 2018-06-21 Rolls-Royce Deutschland Ltd & Co Kg Turbinen-Laufschaufelanordnung für eine Gasturbine und Verfahren zum Bereitstellen von Dichtluft in einer Turbinen-Laufschaufelanordnung
US10247015B2 (en) 2017-01-13 2019-04-02 Rolls-Royce Corporation Cooled blisk with dual wall blades for gas turbine engine
US10934865B2 (en) 2017-01-13 2021-03-02 Rolls-Royce Corporation Cooled single walled blisk for gas turbine engine
US10415403B2 (en) 2017-01-13 2019-09-17 Rolls-Royce North American Technologies Inc. Cooled blisk for gas turbine engine
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
CA3000376A1 (fr) * 2017-05-23 2018-11-23 Rolls-Royce Corporation Assemblage de carenage de turbine comportant des segments de piste en composite a matrice ceramique dotes de fonctionnalites de fixation metallique
KR102028804B1 (ko) * 2017-10-19 2019-10-04 두산중공업 주식회사 가스 터빈 디스크
US10718218B2 (en) 2018-03-05 2020-07-21 Rolls-Royce North American Technologies Inc. Turbine blisk with airfoil and rim cooling
CN109236378A (zh) * 2018-09-11 2019-01-18 上海发电设备成套设计研究院有限责任公司 一种内部蒸汽冷却的高参数汽轮机的单流高温转子
KR102141626B1 (ko) * 2018-10-01 2020-08-05 두산중공업 주식회사 터빈장치
JP7328794B2 (ja) * 2019-05-24 2023-08-17 三菱重工業株式会社 ロータディスク、ロータ軸、タービンロータ、及びガスタービン
US11506060B1 (en) 2021-07-15 2022-11-22 Honeywell International Inc. Radial turbine rotor for gas turbine engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2065788A (en) * 1979-12-17 1981-07-01 United Technologies Corp Rotor disc cooling air duct
DE3444586A1 (de) 1983-12-22 1985-07-04 United Technologies Corp., Hartford, Conn. Laufradanordnung in einer gasturbine
DE2947521A1 (de) 1978-11-27 1986-06-26 Snecma Turbinenscheibe mit kanaelen zum durchtritt eines kuehlfluids
DE4428207A1 (de) * 1994-08-09 1996-02-15 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe mit gekrümmtem Kühlluftkanal sowie Herstellverfahren hierfür

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3849025A (en) * 1973-03-28 1974-11-19 Gen Electric Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
US4275990A (en) * 1977-12-17 1981-06-30 Rolls-Royce Limited Disc channel for cooling rotor blade roots
US4212587A (en) * 1978-05-30 1980-07-15 General Electric Company Cooling system for a gas turbine using V-shaped notch weirs
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
US5816777A (en) * 1991-11-29 1998-10-06 United Technologies Corporation Turbine blade cooling
US5318404A (en) * 1992-12-30 1994-06-07 General Electric Company Steam transfer arrangement for turbine bucket cooling
US5593274A (en) * 1995-03-31 1997-01-14 General Electric Co. Closed or open circuit cooling of turbine rotor components
JP3448145B2 (ja) * 1995-11-24 2003-09-16 三菱重工業株式会社 熱回収式ガスタービンロータ
US5800124A (en) * 1996-04-12 1998-09-01 United Technologies Corporation Cooled rotor assembly for a turbine engine
US5755556A (en) * 1996-05-17 1998-05-26 Westinghouse Electric Corporation Turbomachine rotor with improved cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2947521A1 (de) 1978-11-27 1986-06-26 Snecma Turbinenscheibe mit kanaelen zum durchtritt eines kuehlfluids
GB2065788A (en) * 1979-12-17 1981-07-01 United Technologies Corp Rotor disc cooling air duct
DE3444586A1 (de) 1983-12-22 1985-07-04 United Technologies Corp., Hartford, Conn. Laufradanordnung in einer gasturbine
DE4428207A1 (de) * 1994-08-09 1996-02-15 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe mit gekrümmtem Kühlluftkanal sowie Herstellverfahren hierfür

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1004748A3 (fr) * 1998-11-27 2001-10-17 Rolls-Royce Deutschland Ltd & Co KG Rotor pour une turbomachine
US8708657B2 (en) 2010-01-22 2014-04-29 Rolls-Royce Plc Rotor Disc
FR2987864A1 (fr) * 2012-03-12 2013-09-13 Snecma Turbomachine a disques de rotor et moyen de guidage radial d'air, et compresseur et/ou turbine avec de tels disques et moyen de guidage.

Also Published As

Publication number Publication date
DE59800115D1 (de) 2000-05-11
US6022190A (en) 2000-02-08
DE19705442A1 (de) 1998-08-20
EP0859128B1 (fr) 2000-04-05

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