EP0894941B1 - Rotor einer Strömungsmaschine - Google Patents

Rotor einer Strömungsmaschine Download PDF

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Publication number
EP0894941B1
EP0894941B1 EP19970810536 EP97810536A EP0894941B1 EP 0894941 B1 EP0894941 B1 EP 0894941B1 EP 19970810536 EP19970810536 EP 19970810536 EP 97810536 A EP97810536 A EP 97810536A EP 0894941 B1 EP0894941 B1 EP 0894941B1
Authority
EP
European Patent Office
Prior art keywords
rotor
shaft
feed
rotor according
root
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
EP19970810536
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0894941A1 (de
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.)
Alstom SA
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to DE59709507T priority Critical patent/DE59709507D1/de
Priority to EP19970810536 priority patent/EP0894941B1/de
Priority to JP10210997A priority patent/JPH1193602A/ja
Publication of EP0894941A1 publication Critical patent/EP0894941A1/de
Application granted granted Critical
Publication of EP0894941B1 publication Critical patent/EP0894941B1/de
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, has a recess in the rotor shaft projecting shaft part the recess is spaced radially from the surface of the rotor shaft,
  • a cooling system for a turbine is known from GB-A-2 224 082. Connect cooling channels a rotor disk with an associated turbine blade. To avoid leaks there are seals in the gap.
  • the Invention as characterized in the claims, the task, the rotor with simple means 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 idea underlying the invention is based on the consideration that the heat acting on the surface of the rotor shaft together with rotor 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.
  • recesses are provided in the peripheral peripheral edge of the rotor shaft have and thus overhanging shaft parts, so-called outstanding Provide sections with radial and / or oblique feed-through channels provided so that the peripheral peripheral edge heated by the hot gases along with Blades from the underside of the overhanging shaft part or protruding Section can be cooled.
  • 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 represents the upper section 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 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. The The arrow shown above the blade breaks represents the flow direction of the Hot gas through the turbines.
  • 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 Wave 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 Blades can cool directly.
  • FIG. 1 The cross-sectional view shown in Fig. 1, which is only a section shows the rotor cross-section corresponds to the end of a designed according to the invention Rotors, with the aid of the representation according to FIG. 2 in place It is to be thought that corresponds to the circle delimited by E in FIG. 2.
  • the circle includes preferably all those blade roots which are provided with the "perforation" according to the invention can be recorded.
  • 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 circumferential 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.
  • 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 through 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 cooling air is supplied there in 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 of the to Shovel 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 is able to 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.
  • cooling flows can also be specifically initiated in the cooling system. Since the openings 12 of the lead-through channels facing the rotor shaft are due to the rotational movement of the rotor relative to that in the recess 5 Rotating the cooling medium can be done by specifically designing the opening geometry the flow direction within each channel for each duct be specified.
  • 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 for 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 feedthrough 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.
  • 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 einer Strömungsmaschine Expired - Lifetime EP0894941B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE59709507T DE59709507D1 (de) 1997-07-28 1997-07-28 Rotor einer Strömungsmaschine
EP19970810536 EP0894941B1 (de) 1997-07-28 1997-07-28 Rotor einer Strömungsmaschine
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 (de) 1997-07-28 1997-07-28 Rotor einer Strömungsmaschine

Publications (2)

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

Family

ID=8230324

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19970810536 Expired - Lifetime EP0894941B1 (de) 1997-07-28 1997-07-28 Rotor einer Strömungsmaschine

Country Status (3)

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

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1041246A1 (de) * 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
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
WO2019008656A1 (ja) * 2017-07-04 2019-01-10 東芝エネルギーシステムズ株式会社 タービン翼及びタービン

Family Cites Families (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
US4344738A (en) * 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
FR2614654B1 (fr) * 1987-04-29 1992-02-21 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
US5318404A (en) * 1992-12-30 1994-06-07 General Electric Company Steam transfer arrangement for turbine bucket cooling
DE4428207A1 (de) * 1994-08-09 1996-02-15 Bmw Rolls Royce Gmbh Turbinen-Laufradscheibe mit gekrümmtem Kühlluftkanal sowie Herstellverfahren hierfür

Also Published As

Publication number Publication date
DE59709507D1 (de) 2003-04-17
JPH1193602A (ja) 1999-04-06
EP0894941A1 (de) 1999-02-03

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