EP0894941A1 - Rotor d'une turbomachine - Google Patents

Rotor d'une turbomachine Download PDF

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Publication number
EP0894941A1
EP0894941A1 EP97810536A EP97810536A EP0894941A1 EP 0894941 A1 EP0894941 A1 EP 0894941A1 EP 97810536 A EP97810536 A EP 97810536A EP 97810536 A EP97810536 A EP 97810536A EP 0894941 A1 EP0894941 A1 EP 0894941A1
Authority
EP
European Patent Office
Prior art keywords
rotor
rotor shaft
shaft
rotor according
channel
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
EP97810536A
Other languages
German (de)
English (en)
Other versions
EP0894941B1 (fr
Inventor
Wilhelm Dr. Endres
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.)
General Electric Switzerland GmbH
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to DE59709507T priority Critical patent/DE59709507D1/de
Priority to EP19970810536 priority patent/EP0894941B1/fr
Priority to JP10210997A priority patent/JPH1193602A/ja
Publication of EP0894941A1 publication Critical patent/EP0894941A1/fr
Application granted granted Critical
Publication of EP0894941B1 publication Critical patent/EP0894941B1/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
    • F01D5/085—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
    • F01D5/02—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

Definitions

  • the invention relates to a rotor of a turbomachine, which on a Surface of its rotor shaft in one or more rows of blades and / or other parts, for example.
  • Heat shields or heat accumulation segments each protrude into the rotor shaft through a surface for attachment, the rotor shaft on at least a portion of its surface near a foot a, a recess in the rotor shaft projecting shaft part, the the recess is spaced radially from the surface of the rotor shaft,
  • the Invention based on the object, the rotor as simple as possible and in particular the surface areas of the rotor shaft of a turbomachine and the blades arranged radially on it as directly as possible, but using a gentle cooling medium, preferably air.
  • a gentle cooling medium preferably air.
  • the measures according to the invention should also be retrofitted to turbomachines that are already in use can be.
  • the rotor of a turbomachine preferably the rotor a gas turbine
  • the blades in the peripheral peripheral edge of its rotor shaft provides, each having a blade root, which is used to attach the blade protrudes into the rotor shaft on the rotor shaft via the peripheral peripheral edge and its rotor shaft in at least one area on the peripheral peripheral edge near a blade root, a recess in the rotor shaft protruding portion, the recess radially to the top of the peripheral Spaced peripheral edge, designed such that the protruding portion is penetrated with at least one feed-through channel such that the Feed-through channel the recess with the rotor shaft end facing of a blade root connects or at least partially penetrates the projecting section.
  • the idea underlying the invention is based on the consideration that the heat of the surface acting on the rotor shaft together with the blades hot gases flowing around the rotor, as close as possible to the peripheral peripheral edge the rotor shaft is to be discharged directly by a suitable supply of cooling air lower the temperature of the rotor material and that of the rotor blades.
  • FIG. 2 A rotor shaft contour known per se, which is used to carry out the inventive Measures is suitable in FIG. 2 as a representation of the prior art shown.
  • the highly schematic cross-sectional drawing according to FIG. 2 represents the Upper portion of a rotor shaft 1, which rotates about the rotor shaft axis A. At the peripheral peripheral edge of the rotor shaft 1 are radial to the rotor shaft axis A blades 2 arranged. Between the blades 2 are only the completeness for the sake of the guide vanes 3, which are fixedly attached to the stator and in the spaces protrude between two successive blades. Of the The arrow shown above the blade breaks represents the flow direction of the Hot gas through the turbines.
  • overhanging shaft part 4 shown in FIG. 2 which is provided in the vicinity of a blade root of a guide blade 2 on the peripheral circumferential edge of the rotor shaft 1.
  • Perforation is suitable, only cooler air is located at the end of the turbomachine on the flow output side, or the supply of cooling air can take place unhindered in this area.
  • the idea of the invention basically provides for the overhanging shaft parts to be closed perforate so that there is an exchange of air between the top of the overhanging Shaft part 4 and the underlying air volume 5 can take place.
  • the overhanging shaft part must be provided with such a perforation, so that the cooling air present in area 5 is the blade root area of the Blades can cool directly.
  • FIG. 1 which only shows a section of the rotor cross-section, corresponds to the end of a rotor designed according to the invention, which, with the aid of the representation according to FIG. 2, is to be thought of at the position that in FIG limited circle corresponds.
  • the circle preferably encompasses all those blade roots that are in accordance with the invention Perforation "can be detected.
  • the constant heat flow Q through the hot gases flowing around the rotor acts on the surface 6 of the rotor shaft 1.
  • an additional heat flow Q S penetrates into the rotor shaft 1 via the blade root 7 of a rotor blade (not shown in FIG. 1), which otherwise rises radially above the surface 6 of the rotor shaft 1.
  • the blade root 7 of a moving blade which in a circulation groove 8 is fixed within the rotor shaft 1, with the help of a feed-through channel 9 to be charged directly with cooling air.
  • This will be the blade load-bearing, overhanging shaft part 4 with a through channel 9 such enforces that the feed-through channel 9 is largely radial to the shaft axis A extends from the recess 5 to the blade root 7.
  • the circumferential groove 8, in which the blade root 7 is attached also has a cavity 10 in which the Cooling air present in the recess 5 pass through the duct 9 can.
  • the circumferential groove 8 runs completely angularly around the rotor shaft 1, in which one A large number of blades are arranged one behind the other.
  • the individual cavities 10 under each blade root of a moving blade together form a circumferential channel 10 'through which the cooling air introduced via the duct 9 can circulate. In this way, the blade feet are cooling, integral Cooling system can be implemented within the rotor shaft.
  • feed-through channels 9 ' are also provided, which overhang the Push shaft part 4 through completely. In this way, the one on the peripheral Circumferential edge 6 acting heat flow Q directly through the through channels 9 'in the direction of the recess 5, in which cooling air is provided.
  • the perforation according to the invention of an overhanging shaft part of a rotor shaft 1, as stated above, is preferably carried out at the end of a rotor, especially since there targeted cooling air is fed into the area of the recess 5 can.
  • Perforation achieve that a desired rotor temperature even with warmer cooling air is achievable, which is already cheaper from a thermodynamic point of view is.
  • Fig. 1 which preferably for Cooling of the blades is provided at the rotor end, can be different Be designed so that the cooling air for removal to the Bucket feet serve existing heat.
  • the cooling air located near the blade root in the cavity 10 is heated due to the large heat input Q S and experiences so much lift in the presence of the centrifugal field generated by the rotation of the rotor that the warmer air climbs radially inward through the duct and in this way the flowing cold air makes room so that it can cool the hot blade feet.
  • This convection flow, which forms in the centrifugal field, arises automatically due to the temperature gradient.
  • the feed-through channels must be of a correspondingly large size so that a countercurrent system of the above-mentioned type can form within a channel.
  • the direction of flow can be specifically designed for each lead-through channel by designing the opening geometry can be specified within the channel.
  • Fig. 1b is the sectional view according to the section A entered in Fig. 1a - A is shown.
  • the cross-sectional view shown in the angular direction to the axis of rotation 1b shows two adjacent feed-through channels 9, which each have openings 11, 11 'facing the rotor shaft and are different have large inlet curvatures R and r.
  • R and r By the of the direction of rotation specified by the rotation of the rotor (see the large arrow direction) cause smaller or sharper opening radii r to create and guide a radially outward cooling flow into the cooling system. Make it up in this way lead-through channels through which the cooling air flows.
  • the cooling flow then passes through the immediately adjacent feed-through channels off again, especially since the individual feed-through channels via the circulation groove 10 ', which is composed of the totality of all cavities 10, are connected.
  • each with differently dimensioned opening radii R, r have, which alternate between adjacent through-channels it is also possible to design the opening area of a through channel in such a way that an opening has two different radii R and r. So it is for the above described flow direction specification necessary, the opening areas two adjacent passageways, which are closest to each other form the same radii of curvature. (see Figure 1c)
  • the direct cooling of the blade feet of the moving blades by a targeted below the cooling medium introduced, preferably cooling air, is also the blade roots for reasons of possible contamination by dust particles within the Cooling system an advantage.
  • dust particles get through the feed-through channels in the circumferential grooves of the mounting rails, so these can in principle also to blockages of the circumferential grooves and thus to a considerable one Reduce the cooling effect.
  • you can counteract such contamination Provide so-called dust holes, such as those in cooled blades are used, on the other hand, it is easy for maintenance work Effort possible by removing the blades from the mounting rail to easily remove contaminants deposited in the circumferential grooves.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)
EP19970810536 1997-07-28 1997-07-28 Rotor d'une turbomachine Expired - Lifetime EP0894941B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE59709507T DE59709507D1 (de) 1997-07-28 1997-07-28 Rotor einer Strömungsmaschine
EP19970810536 EP0894941B1 (fr) 1997-07-28 1997-07-28 Rotor d'une turbomachine
JP10210997A JPH1193602A (ja) 1997-07-28 1998-07-27 流体機械用のロータ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19970810536 EP0894941B1 (fr) 1997-07-28 1997-07-28 Rotor d'une turbomachine

Publications (2)

Publication Number Publication Date
EP0894941A1 true EP0894941A1 (fr) 1999-02-03
EP0894941B1 EP0894941B1 (fr) 2003-03-12

Family

ID=8230324

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970810536 Expired - Lifetime EP0894941B1 (fr) 1997-07-28 1997-07-28 Rotor d'une turbomachine

Country Status (3)

Country Link
EP (1) EP0894941B1 (fr)
JP (1) JPH1193602A (fr)
DE (1) DE59709507D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1041246A1 (fr) * 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz
EP2246525A4 (fr) * 2008-02-28 2013-05-01 Mitsubishi Heavy Ind Ltd Turbine à gaz, disque et procédé de formation de passage radial de disque

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019008656A1 (fr) * 2017-07-04 2019-01-10 東芝エネルギーシステムズ株式会社 Aube de turbine et turbine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH495496A (de) * 1969-02-26 1970-08-31 Bbc Sulzer Turbomaschinen Turbomaschine mit gekühltem Rotor
US3904307A (en) * 1974-04-10 1975-09-09 United Technologies Corp Gas generator turbine cooling scheme
US3918835A (en) * 1974-12-19 1975-11-11 United Technologies Corp Centrifugal cooling air filter
GB2065788A (en) * 1979-12-17 1981-07-01 United Technologies Corp Rotor disc cooling air duct
FR2614654A1 (fr) * 1987-04-29 1988-11-04 Snecma Disque de compresseur axial de turbomachine a prelevement d'air centripete
GB2224082A (en) * 1988-10-19 1990-04-25 Rolls Royce Plc Turbine disc having cooling and sealing arrangements
EP0605155A1 (fr) * 1992-12-30 1994-07-06 General Electric Company Dispositif de transfert de vapeur pour aube de turbine refroidie
DE4428207A1 (de) * 1994-08-09 1996-02-15 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe mit gekrümmtem Kühlluftkanal sowie Herstellverfahren hierfür

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH495496A (de) * 1969-02-26 1970-08-31 Bbc Sulzer Turbomaschinen Turbomaschine mit gekühltem Rotor
US3904307A (en) * 1974-04-10 1975-09-09 United Technologies Corp Gas generator turbine cooling scheme
US3918835A (en) * 1974-12-19 1975-11-11 United Technologies Corp Centrifugal cooling air filter
GB2065788A (en) * 1979-12-17 1981-07-01 United Technologies Corp Rotor disc cooling air duct
FR2614654A1 (fr) * 1987-04-29 1988-11-04 Snecma Disque de compresseur axial de turbomachine a prelevement d'air centripete
GB2224082A (en) * 1988-10-19 1990-04-25 Rolls Royce Plc Turbine disc having cooling and sealing arrangements
EP0605155A1 (fr) * 1992-12-30 1994-07-06 General Electric Company Dispositif de transfert de vapeur pour aube de turbine refroidie
DE4428207A1 (de) * 1994-08-09 1996-02-15 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe mit gekrümmtem Kühlluftkanal sowie Herstellverfahren hierfür

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1041246A1 (fr) * 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz
WO2000058606A1 (fr) * 1999-03-29 2000-10-05 Siemens Aktiengesellschaft Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine
US6565318B1 (en) 1999-03-29 2003-05-20 Siemens Aktiengesellschaft Cast gas turbine blade through which coolant flows, together with appliance and method for manufacturing a distribution space of the gas turbine blade
EP2246525A4 (fr) * 2008-02-28 2013-05-01 Mitsubishi Heavy Ind Ltd Turbine à gaz, disque et procédé de formation de passage radial de disque

Also Published As

Publication number Publication date
DE59709507D1 (de) 2003-04-17
EP0894941B1 (fr) 2003-03-12
JPH1193602A (ja) 1999-04-06

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