EP0859128B1 - Disque de turbine avec canaux refroidissement - Google Patents

Disque de turbine avec canaux refroidissement Download PDF

Info

Publication number
EP0859128B1
EP0859128B1 EP98101046A EP98101046A EP0859128B1 EP 0859128 B1 EP0859128 B1 EP 0859128B1 EP 98101046 A EP98101046 A EP 98101046A EP 98101046 A EP98101046 A EP 98101046A EP 0859128 B1 EP0859128 B1 EP 0859128B1
Authority
EP
European Patent Office
Prior art keywords
cooling air
disc
disk
turbine
groove
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.)
Expired - Lifetime
Application number
EP98101046A
Other languages
German (de)
English (en)
Other versions
EP0859128A1 (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

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
    • 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 with cooling air channels extending from the disk end face, which open into the disk grooves in which air-cooled turbine blades are inserted.
  • reference is made, for example, to DE 29 47 521 A1 and DE 34 44 586 A1.
  • cooling air can also be supplied to a second turbine impeller disk, which is arranged downstream of a first impeller disk, in that part of the cooling air flow entering the disk grooves of the first impeller disk is discharged via these disk grooves virtually backwards into the space between the first and second impeller disks becomes.
  • appropriate passage openings can be provided in the so-called closing plates, which secure the blades inserted into the disk grooves.
  • a cooling air duct opening into the groove bottom of the disk groove cannot be made arbitrarily large with regard to its cross-sectional area, since the spatial fields of the individual stress concentrations for the circumferential stresses overlap in this opening area and can cause greatly increased stress amplitudes locally, which is undesirable with regard to the operational fatigue strength is.
  • the object of the present invention is to provide a remedial measure for the problems described.
  • the solution to this problem is characterized in that in each disk groove two cooling air ducts each emanating from the same disk face end, which are arranged essentially mirror-inverted to and inclined relative to a plane of symmetry leading in the radial direction from the disk axis to the center of the disk groove.
  • cooling air ducts instead of a single cooling air duct, two such cooling air ducts are now provided for each disk groove, through which a larger cooling air flow can of course then be guided.
  • a single duct with the same total flow cross-section instead of these two cooling air ducts, but then inadmissibly high voltage peaks would occur in the region of its mouth opening in the bottom of the disc groove, as will be explained in more detail later.
  • the impeller disk is only as small as possible Dimensions weakened.
  • the cooling air ducts causing a material weakening are in the best possible way and are evenly distributed over the entire pane structure.
  • 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, by the dimension P from each other are spaced.
  • the reference numeral 1 denotes an impeller disk, in particular a gas turbine, which, as usual, has on its outer circumference a plurality of disk grooves 2 each having a fir tree profile, in each of which a turbine blade 3 is inserted. Every turbine blade 3 is air-cooled, ie cooling turbine ducts (not shown) are provided in each turbine blade 3, into which cooling air flow can enter from the disk groove 2.
  • this cooling air flow passes through at least two cooling air channels 4, which start from the face of the disk 1a - the corresponding opening is designated by reference number 7b - and are guided inside the disk to the respective disk groove 2, where they open into the groove base 2a (mouth opening 7a).
  • at least two cooling air ducts 4, which start from the same front face 1a and each have a certain cross-sectional area Q, can be used to bring about a larger amount of cooling air flow than a single cooling air duct 4 with the same cross-sectional area Q, as 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 direction of stress along the row of holes 11 is shown by the arrow 12. 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.
  • cooling air duct arrangement which is favorable with regard to the size of the achievable cooling air flow and with regard to the weakening of the impeller disk 1 by the cooling air ducts 4, if the orifice openings 7a of the two cooling air ducts 4 are essentially in one in each disc groove 2 common cutting plane perpendicular to the disc axis lie next to each other. It is advantageous if, as the partial view of the front face 1a of FIG. 2 shows, the two cooling air ducts 4 for each disk groove 2 are essentially mirror images and inclined relative to one in the radial direction from the disk axis (not shown) to the center of the disk groove 2 leading plane of symmetry 5 are provided.
  • the longitudinal axes of all cooling air ducts 4 can be linear or bent in any way, and the cross section of these cooling air ducts can be circular, elliptical or otherwise suitably shaped.
  • part of the cooling air flow introduced into the disc grooves 2 of this impeller disc can be used to supply cooling air to a second impeller disc (not shown) connected downstream of this first impeller disc 1.
  • Corresponding passage openings 9 can be provided in the area of the disk grooves 2 for a partial cooling air flow in the closing plates 6 which fix the turbine blades 3 in the impeller disk 1, each of which has a channel 9 ′ provided in the foot of the turbine blade and having a channel which adjoins the cooling air channel 4, provided in the blade root cooling air duct 4 '.
  • the doubling or multiplication of the cooling air ducts 4 opening into a disk groove 2 shown here means that a significantly larger cooling air flow can be conducted to the foot of each turbine blade 3 compared to the known prior art.
  • the plurality of orifices 7a of the plurality of cooling air channels 4 lead to significantly lower mechanical loads on the impeller disk 1 than would a single cooling air channel with a correspondingly large cross-sectional area and thus a correspondingly enlarged orifice opening 7a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

  1. Disque de rotor de turbine comportant des canaux d'air de refroidissement (4) partant de la face frontale (la) du disque et débouchant dans les rainures de disque (2) recevant les aubes de turbine (3) refroidies par de l'air,
    caractérisé en ce que
    dans chaque rainure (2) du disque débouchent chaque fois deux canaux d'air de refroidissement (4) partant de la même face frontale (la) du disque, ces canaux étant inclinés de manière essentiellement symétrique par rapport à un plan de symétrie (5) partant dans la direction radiale de l'axe de disque (8) au milieu de la rainure (2).
  2. Disque de rotor de turbine selon la revendication 1,
    caractérisé en ce que
    les embouchures (7a) des deux canaux d'air de refroidissement (4) se situent dans chaque rainure (2) essentiellement de manière juxtaposée dans un plan de coupe commun essentiellement perpendiculaire à l'axe (8) du disque.
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
DE19705442A DE19705442A1 (de) 1997-02-13 1997-02-13 Turbinen-Laufradscheibe mit Kühlluftkanälen
DE19705442 1997-02-13

Publications (2)

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

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DE19854908A1 (de) 1998-11-27 2000-05-31 Rolls Royce Deutschland Schaufel und Laufscheibe einer Strömungsmaschine
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
GB201000982D0 (en) 2010-01-22 2010-03-10 Rolls Royce Plc A rotor disc
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
FR2987864B1 (fr) * 2012-03-12 2017-06-16 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.
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
US10415403B2 (en) 2017-01-13 2019-09-17 Rolls-Royce North American Technologies Inc. Cooled blisk for gas turbine engine
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
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

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Also Published As

Publication number Publication date
US6022190A (en) 2000-02-08
DE59800115D1 (de) 2000-05-11
DE19705442A1 (de) 1998-08-20
EP0859128A1 (fr) 1998-08-19

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