EP0926311A1 - Rotor pour une turbomachine - Google Patents

Rotor pour une turbomachine Download PDF

Info

Publication number
EP0926311A1
EP0926311A1 EP97811025A EP97811025A EP0926311A1 EP 0926311 A1 EP0926311 A1 EP 0926311A1 EP 97811025 A EP97811025 A EP 97811025A EP 97811025 A EP97811025 A EP 97811025A EP 0926311 A1 EP0926311 A1 EP 0926311A1
Authority
EP
European Patent Office
Prior art keywords
rotor
cavity
rotor according
rotor shaft
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
EP97811025A
Other languages
German (de)
English (en)
Other versions
EP0926311B1 (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 EP19970811025 priority Critical patent/EP0926311B1/fr
Priority to DE59710425T priority patent/DE59710425D1/de
Priority to JP36321398A priority patent/JP4372250B2/ja
Publication of EP0926311A1 publication Critical patent/EP0926311A1/fr
Application granted granted Critical
Publication of EP0926311B1 publication Critical patent/EP0926311B1/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
    • 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
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum 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
    • F01D5/02—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

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 of which a foot protruding through the surface into 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 rotor blades arranged radially on it as directly as possible, but using a gentle cooling medium, preferably air.
  • a gentle cooling medium preferably air.
  • the rotor of a turbomachine preferably the rotor a gas turbine which has rotor blades in the peripheral peripheral edge of its rotor shaft provides, each having a blade root, which is used to attach the blades 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 has a cavity in the rotor shaft near a blade root, designed in such a way that the rotor shaft is close to at least one area below the surface at least one foot has at least one closed cavity that the cavity via at least one feed-through channel with the rotor shaft side facing end of a foot is connected for cooling purposes, and that a cooling system is provided, through which the cavity can be supplied with a cooling medium.
  • the idea on which the invention is based 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 dissipated directly by a suitable supply of cooling air to the Deflect the temperature of the rotor material and that of the rotor feet.
  • the rotors that are located just below their peripheral peripheral edge Have rotor shaft cavities with radial and / or oblique through channels provided so that the peripheral peripheral edge heated by the hot gases along with blades from the side of the cavity, which in turn has a cooling system with a cooling medium, preferably cooling air, is cooled can.
  • a cooling medium preferably cooling air
  • FIG. 2 A rotor shaft contour known per se, which is used to carry out the inventive Measures are suitable, is shown in Fig. 2 as a representation of the prior art.
  • 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 are rotor blades radial to the rotor shaft axis 2 arranged. Between the blades are only for completeness the guide blades 3 are shown, which are fixedly attached to the stator and in the spaces protrude between two successive blades 2. The over The arrow shown in the blade breaks represents the direction of flow of the hot gas through the turbines.
  • Section E is placed near a blade root of a guide vane provides a cavity at the peripheral peripheral edge of the rotor shaft.
  • the concept of the invention basically provides for the area of the rotor shaft to be above to perforate the cavity so that air exchange between the top of the Rotor shaft and the cooling air located in the cavity can take place. Especially the area of the rotor shaft must be provided with such a perforation so that the cooling air in the cavity directly touches the blade root area of the blades can cool.
  • FIG. 1 The cross-sectional view shown in Fig. 1, which is only a section shows the rotor cross-section corresponds to a central section of one according to the invention stepped rotor, with the help of the representation according to FIG. 2 the point is to be thought of which corresponds to the circle delimited by E in FIG. 2.
  • the Circle preferably includes all those blade roots that with the invention "Perforation" can be detected.
  • the constant heat flow Q acts through the Hot gases flowing around the rotor.
  • the Schaufeffuß 7 of a moving blade which in a Circulation groove 8 is fixed within the rotor shaft 1, with the aid of a feed-through channel 9 to be charged directly with cooling air.
  • a cavity 5 is close to the Blade provided within the rotor shaft 1 and with a passage channel 9 connected such that the feed-through channel 9 is largely radial to Shaft axis A extends from the cavity 5 to the blade root 7.
  • the cavity 5 is connected to a cooling system 4, via which a cooling medium in the Cavity 5 can be fed.
  • the supply 4a of the cooling medium into the cavity 5 is advantageously such that a swirl occurs in cavity 5 relative to the rotor.
  • the return 4b of the heated Cooling medium from the cavity 5 is advantageously carried out on the inner surface of the cavity because the heated cooling medium collects there.
  • the opening of the feed channel 4a into the cavity 5 must e.g. with large radii or bevels or guide vanes in such a way that the cooling medium flows in well can. If the latter is too warm for the rotor, the discharge duct 4b can always be used still isolate, e.g. through a lining pipe or a thermal insulation layer.
  • the circumferential groove 8 in which the blade root 7 is fastened also has a hollow channel 10 on, in which the cooling air present in the cavity 5 via the duct 9 can reach.
  • the circumferential groove 8 runs completely angularly around the rotor shaft 1, in which a plurality are arranged one behind the other.
  • the individual hollow channels 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 circulates can. In this way, an integral cooling system that cools the blade feet is inside the rotor shaft can be realized.
  • feed-through channels 9 ' are also provided which cover the peripheral area the rotor shaft completely or only partially. That way the heat flow Q acting on the peripheral peripheral edge 6 directly through the feed-through channels 9 'in the direction of the cavity 5 are provided in the cooling air is derived.
  • the cooling arrangement according to the invention shown in Fig. 1, preferably for Cooling the rotor blades in the middle of the rotor can be done in different ways Be designed so that the cooling air for removal of the the existing blade heat is used.
  • the cooling air located near the blade root in the hollow duct 1 0 warms due to the large heat input and experiences in the presence of the by the rotation of the rotor generated centrifugal field so much lift that the warmer air, directed radially inward, climbs up and through the duct this gives way to the incoming colder air, so that it is called hot Shovel feet can cool.
  • This convection flow that forms in the centrifugal field arises automatically due to the temperature gradient.
  • the Feed-through channels must, however, be made correspondingly large, so that countercurrent system within a channel as described above can train.
  • the openings of the feed-through channels, which end in the cavity 5, should open a smaller radius, measured from the axis of rotation of the rotor, than the areas of the rotor shaft where the heat is applied,
  • the design of the cavity can be designed as desired. So it is not mandatory required that the upper contour of the cavity from which the feed-through channels 9 go out, runs obliquely to the rotor shaft axis A. They can also Feed-through channels 9 also depart from cavity wall sections that are perpendicular or run vertically relative to the rotor shaft axis A. Essential with the arrangement of the feed-through channels, however, is that the openings of the feed-through channels lie on a smaller radius relative to the rotor shaft axis than that Areas of the feed-through channels to which the heat is supplied, so that the Principle of the so-called thermosiphon is applicable. In this case, the Rotor shaft the difference between the pumping power for the cold cooling air and the Apply the turbine power to the warm cooling air.
  • the openings 11, 11 ' largely on the same radius lie relative to the rotor shaft axis A; if this is not the case, the radial influences Pressure difference, i.e. the swirl in the cavity caused by the pressure difference Cooling effect.
  • FIG. 1 b is the sectional view according to the section A entered in Fig. 1a - A is shown.
  • the cross-sectional representation shown perpendicular to the axis of rotation in 1 b shows two adjacent feed-through channels 9, each on the rotor shaft side have facing openings 11, 11 'and of different sizes Inlet curves R and r have.
  • the cooling medium in the cavity 5 flows relative to the rotor in the direction indicated by the large arrow.
  • This Cross flow over the openings 11, 11 'is in the holes 11 with the larger ones Opening radii R generate a higher pressure than in the holes 11 'with smaller ones Opening radii r.
  • This Flow continues through the circumferential groove 10 'and returns in the adjacent channels 9 with the smaller opening radii r back into the cavity 5.
  • 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.
  • opening contours shown can create real scooping edges at the respective points of the openings of the through channels be provided. However, this is with an additional constructive Effort associated with the operation of the above "Thermosyphons" is not absolutely necessary.
  • 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, they 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)
EP19970811025 1997-12-24 1997-12-24 Rotor pour une turbomachine Expired - Lifetime EP0926311B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP19970811025 EP0926311B1 (fr) 1997-12-24 1997-12-24 Rotor pour une turbomachine
DE59710425T DE59710425D1 (de) 1997-12-24 1997-12-24 Rotor einer Strömungsmaschine
JP36321398A JP4372250B2 (ja) 1997-12-24 1998-12-21 流体機械のロータ

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19970811025 EP0926311B1 (fr) 1997-12-24 1997-12-24 Rotor pour une turbomachine

Publications (2)

Publication Number Publication Date
EP0926311A1 true EP0926311A1 (fr) 1999-06-30
EP0926311B1 EP0926311B1 (fr) 2003-07-09

Family

ID=8230550

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970811025 Expired - Lifetime EP0926311B1 (fr) 1997-12-24 1997-12-24 Rotor pour une turbomachine

Country Status (3)

Country Link
EP (1) EP0926311B1 (fr)
JP (1) JP4372250B2 (fr)
DE (1) DE59710425D1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1785587A1 (fr) 2005-11-11 2007-05-16 Siemens Aktiengesellschaft Rotor de turbomachine à refroidissement interne
EP2837769A1 (fr) * 2013-08-13 2015-02-18 Alstom Technology Ltd Arbre de rotor pour turbomachine
EP3061909A1 (fr) * 2015-02-26 2016-08-31 General Electric Technology GmbH Arbre de rotor avec des entrées à alésages de refroidissement
US10113432B2 (en) 2014-03-19 2018-10-30 Ansaldo Energia Switzerland AG Rotor shaft with cooling bore inlets

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB742242A (en) * 1951-02-15 1955-12-21 Power Jets Res & Dev Ltd Improvements in the cooling of turbine rotors
DE959868C (de) * 1953-07-17 1957-03-14 Schilling Estate Company Laufradanordnung fuer Verpuffungsbrennkraftturbinen hoher Drehzahl
GB810459A (en) * 1955-06-14 1959-03-18 Gen Electric Improved turbomachine rotor with air-cooled blading
GB882480A (en) * 1957-09-18 1961-11-15 Escher Wyss Ag Improvements in or relating to rotors for axial-flow turbines
CH495496A (de) * 1969-02-26 1970-08-31 Bbc Sulzer Turbomaschinen Turbomaschine mit gekühltem Rotor
FR2083846A5 (en) * 1970-03-14 1971-12-17 Motoren Turbinen Union Gas turbine rotors and blades assembled by electron bombardment - welding - with efficient assembly cooling means
EP0037897A1 (fr) * 1980-04-15 1981-10-21 M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft Dispositif de refroidissement interne d'une turbine à gaz
EP0122872A1 (fr) * 1983-03-18 1984-10-24 Kraftwerk Union Aktiengesellschaft Turbine de vapeur de moyenne pression pour une installation de vapeur de haute température avec réchauffage intermédiaire
DE4324034A1 (de) * 1993-07-17 1995-01-19 Abb Management Ag Gasturbine mit gekühltem Rotor
DE19617539A1 (de) * 1996-05-02 1997-11-13 Asea Brown Boveri Rotor für eine thermische Turbomaschine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB742242A (en) * 1951-02-15 1955-12-21 Power Jets Res & Dev Ltd Improvements in the cooling of turbine rotors
DE959868C (de) * 1953-07-17 1957-03-14 Schilling Estate Company Laufradanordnung fuer Verpuffungsbrennkraftturbinen hoher Drehzahl
GB810459A (en) * 1955-06-14 1959-03-18 Gen Electric Improved turbomachine rotor with air-cooled blading
GB882480A (en) * 1957-09-18 1961-11-15 Escher Wyss Ag Improvements in or relating to rotors for axial-flow turbines
CH495496A (de) * 1969-02-26 1970-08-31 Bbc Sulzer Turbomaschinen Turbomaschine mit gekühltem Rotor
FR2083846A5 (en) * 1970-03-14 1971-12-17 Motoren Turbinen Union Gas turbine rotors and blades assembled by electron bombardment - welding - with efficient assembly cooling means
EP0037897A1 (fr) * 1980-04-15 1981-10-21 M.A.N. MASCHINENFABRIK AUGSBURG-NÜRNBERG Aktiengesellschaft Dispositif de refroidissement interne d'une turbine à gaz
EP0122872A1 (fr) * 1983-03-18 1984-10-24 Kraftwerk Union Aktiengesellschaft Turbine de vapeur de moyenne pression pour une installation de vapeur de haute température avec réchauffage intermédiaire
DE4324034A1 (de) * 1993-07-17 1995-01-19 Abb Management Ag Gasturbine mit gekühltem Rotor
DE19617539A1 (de) * 1996-05-02 1997-11-13 Asea Brown Boveri Rotor für eine thermische Turbomaschine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1785587A1 (fr) 2005-11-11 2007-05-16 Siemens Aktiengesellschaft Rotor de turbomachine à refroidissement interne
EP2837769A1 (fr) * 2013-08-13 2015-02-18 Alstom Technology Ltd Arbre de rotor pour turbomachine
US11105205B2 (en) 2013-08-13 2021-08-31 Ansaldo Energia Switzerland AG Rotor shaft for a turbomachine
US10113432B2 (en) 2014-03-19 2018-10-30 Ansaldo Energia Switzerland AG Rotor shaft with cooling bore inlets
EP3061909A1 (fr) * 2015-02-26 2016-08-31 General Electric Technology GmbH Arbre de rotor avec des entrées à alésages de refroidissement

Also Published As

Publication number Publication date
JP4372250B2 (ja) 2009-11-25
EP0926311B1 (fr) 2003-07-09
DE59710425D1 (de) 2003-08-14
JPH11247603A (ja) 1999-09-14

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