EP1895094B1 - Rotor avec cordon de soudure refroidi par tourbillon - Google Patents

Rotor avec cordon de soudure refroidi par tourbillon Download PDF

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Publication number
EP1895094B1
EP1895094B1 EP06017817A EP06017817A EP1895094B1 EP 1895094 B1 EP1895094 B1 EP 1895094B1 EP 06017817 A EP06017817 A EP 06017817A EP 06017817 A EP06017817 A EP 06017817A EP 1895094 B1 EP1895094 B1 EP 1895094B1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
rotor
flow
swirl
shroud
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.)
Not-in-force
Application number
EP06017817A
Other languages
German (de)
English (en)
Other versions
EP1895094A1 (fr
Inventor
Jan Walkenhorst
Armin De Lazzer
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to DE502006007968T priority Critical patent/DE502006007968D1/de
Priority to EP06017817A priority patent/EP1895094B1/fr
Priority to AT06017817T priority patent/ATE483096T1/de
Publication of EP1895094A1 publication Critical patent/EP1895094A1/fr
Application granted granted Critical
Publication of EP1895094B1 publication Critical patent/EP1895094B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth 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
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/063—Welded rotors
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer

Definitions

  • the invention relates to a turbomachine comprising a housing and a rotatably mounted within the housing rotor, wherein the rotor is formed of two part rotors and the two part rotors are welded together, whereby a welding area is formed.
  • a steam turbine is understood to mean any turbine or sub-turbine through which a working medium in the form of steam flows.
  • gas turbines are traversed with gas and / or air as a working medium, but that is subject to completely different temperature and pressure conditions than the steam in a steam turbine.
  • Steam turbines for example, the working medium having the highest temperature, which flows to a partial turbine, at the same time has the highest pressure.
  • An open cooling system, as in gas turbines, is therefore not feasible without external supply.
  • a steam turbine typically includes a vaned rotatably mounted rotor disposed within a casing shell.
  • the rotor When flowing through the flow space formed by the housing jacket with heated and pressurized steam, the rotor is set in rotation by the steam via the blades.
  • the rotor-mounted blades are also referred to as blades.
  • usually stationary guide vanes are mounted on the housing jacket, which engage in the intermediate spaces of the moving blades.
  • a vane is typically held at a first location along an interior of the steam turbine casing. In this case, it is usually part of a vane ring, which comprises a number of vanes, which are arranged along an inner circumference on the inside of the steam turbine housing. Each vane has its blade radially inward.
  • a vane ring at a location along the axial extent is also referred to as a vane row.
  • a plurality of vane rows are arranged one behind the other.
  • the rotatably mounted in the steam turbine steam turbine rotors are subjected to thermal stress during operation.
  • the development and production of a steam turbine rotor is both expensive and time consuming.
  • the steam turbine rotors are considered to be the most highly stressed and expensive components of a steam turbine.
  • a feature of the steam turbine rotor is that it has no significant heat sink. Therefore, the cooling of the blades arranged on the steam turbine rotor is difficult.
  • EP 1 536 102 discloses a rotor for a steam turbine, wherein the rotor consists of at least two rotor parts. The two rotor parts are welded together, wherein cooling means are provided for cooling the weld area.
  • the CH 353 218 discloses a runner composed of individual disks designed as a blade carrier of an axial turbine.
  • the EP 1 013 879 also discloses a shaft of a heat engine with a cavity.
  • Piston area is to be understood as the area of a thrust balance piston.
  • the thrust balance piston acts in a steam turbine such that a force caused by the working medium force is formed on the rotor in one direction counter-force in the opposite direction.
  • the invention begins, whose task is to specify a turbomachine, which can be manufactured inexpensively.
  • a turbomachine comprising a housing and a rotatably mounted within the housing rotor, wherein the rotor is formed of two part rotors and the two part rotors are welded together, whereby a welding area is formed, wherein cooling means are provided for cooling the welding area ,
  • the turbomachine comprises at least one row of guide vanes having vanes formed with shrouds, the shroud having swirl bores for guiding a flow medium flowing in operation through the turbomachine to the weld area.
  • the invention therefore provides for a turbomachine with a rotor, which is formed from two part rotors.
  • the two sub-rotors experience different thermal stresses.
  • One of the two sub-rotors can be used in a particularly thermally loaded area, whereas the second sub-rotor is to be used in a comparatively less thermally stressed area.
  • the welding must be done at a suitable place. Care must be taken to ensure that the thermal load on the welding area during operation is not too great. Therefore, efforts are made to move the welding area as possible to a point that is relatively less thermally stressed.
  • it is proposed to arrange the welding area entirely in a region of higher thermal stress.
  • coolant for cooling the weld area is provided according to the invention.
  • the welding area can be arranged in an area on the rotor, which is exposed to higher thermal loads. Due to the cooling according to the invention, the weld can nevertheless be arranged in this thermally loaded area. As a result, the heat-resistant material to be used in the thermally stressed area can be saved, since the weld is arranged as far as possible in the thermally stressed area. In the less thermally loaded area can be a cheaper, less heat-resistant material can be used. Due to the material savings of expensive high-temperature resistant material finally the production of such a turbomachine is cheaper.
  • the invention has an effect if the sub-rotor, the high thermal loads of about 700 ° C is exposed, made of a nickel-based alloy.
  • the material price of these alloys is a factor of three to four higher than that of material X12 (i.e., a 9% chromium steel) used for the part rotor exposed to low thermal stresses.
  • the allowable dimensions of the forgings are limited.
  • the maximum billet weight of a nickel-based alloy forging is currently 6 t, whereas the maximum billet weight of a forged billet of X12 is> 12 t.
  • any reduction of the partial rotor of the nickel-based alloy already by a few centimeters leads to significant cost savings and, moreover, such a part rotor can be procured easily. According to first estimates, such a rotor designed according to the invention could save up to 20% or up to 50 cm of the length of this partial rotor not designed according to the invention.
  • a shroud with swirl holes for guiding a flowing during operation by the flow machine flow medium is carried out on the welding area.
  • the flow medium flows through the swirl bores. Due to the accelerating effect in the swirl bore, the temperature of the flow medium in the swirl hole is reduced. This means that after exiting the swirl hole, the flow medium acts as a cooling medium. With the thus cooled flow medium finally the welding area of the rotor is cooled.
  • the shroud is arranged above the welding area. It has a favorable effect if the shroud is arranged in the immediate vicinity above the welding area.
  • the flowing out of the swirl holes flow medium acts as a cooling medium and should therefore be placed as close to the welding area.
  • the flow conditions of the flow medium in the turbomachine are such that it is favorable that the swirl bore is arranged before the flow medium enters the guide vane row. Thus, it is possible to divert a high volume flow of the flow medium into the swirl bores.
  • the swirl bore is inclined at an angle ⁇ to the flow direction.
  • the angle ⁇ has values between 30 ° and 90 °. This makes it possible, due to the flow conditions in the flow channel, to divert a high yield of volume flow from the flow medium in the flow channel into the swirl bore.
  • the swirl bore is inclined at an angle ⁇ to the tangents of the Leitschaufeldeckbandober Design.
  • the angle ⁇ has values between 0 ° and 60 °.
  • tangential of the Leitschaufeldeckbandober Design is essentially a straight line to understand that leads perpendicular to a connecting line from the rotor center to the swirl hole and branches off from the swirl hole. This makes it possible to achieve the so-called swirl cooling, which is reinforced by the inventive inclination of the swirl bore.
  • the swirl cooling is caused by the interplay between a moving reference system (rotating rotor) and a stationary reference system (Leitschaufelsch).
  • a rotor seal is arranged in the front region of the shroud.
  • FIG. 1 is a cross-sectional view of a turbomachine 1 is shown.
  • a turbomachine 1 is z.
  • B. a gas turbine or a steam turbine.
  • the turbomachine comprises a housing 2.
  • the housing 2 may be formed as an inner housing or as an outer housing.
  • the turbomachine 1 has a rotatably mounted within the housing 2 rotor 3.
  • the rotor is one in the FIG. 1 not shown in detail rotation axis 24 rotatably mounted.
  • the rotor 3 has a first part rotor 3a and a second part rotor 3b. The rotor 3 is welded together in a welding area.
  • the turbomachine 1 comprises at least one row of guide vanes 5, the row of vanes 5 having vanes 7 formed with shrouds 6.
  • turbomachine has a plurality of vane rows 5 ', 5'',5'' on. Between the guide blade rows 5, 5 ', 5'',5''' blade rows 8 are arranged, which are formed from individual blade 9.
  • a flow medium flows through the turbomachine 1 in a flow direction 10. The flow medium flows through a flow channel 11.
  • the flow medium may be, for example, a live steam having temperatures of up to 700 ° C and a pressure of 350 bar.
  • the turbomachine 1 can be designed as a high-pressure steam turbine.
  • the shroud 6 is formed with swirl bores 12 for guiding a flow medium flowing through the turbomachine 1 during operation onto the welding region 4. This creates the so-called swirl cooling in the area of the welding area 4 and cools it effectively.
  • the shroud 6 is arranged above the welding area 4.
  • FIG. 4 is an enlarged view of a part of FIG. 1 illustrated turbomachine 1.
  • the shroud 6 is shown.
  • the vane 7 comprises a vane profile 13.
  • the guide blade profile 13 can be seen only as a projection on a plane parallel to the flow direction 10.
  • the vane profile 13 is projected at the character level, so to speak.
  • the shroud 6 has a length 14 which is longer than the projection 15 of the guide blade profile 13 on a plane parallel to the flow direction 10.
  • the swirl bore 12 is arranged in a region 16 of the shroud 6, which is seen in the flow direction 10 in front of the guide blade leading edge 17.
  • the swirl bore 12 is inclined at an angle ⁇ to the flow direction 10. Starting from the flow direction 10, the swirl bore 12 is rotated in the mathematically negative sense by the angle ⁇ .
  • the angle ⁇ here takes on values between 30 ° and 90 °.
  • the angle ⁇ may be 90 °.
  • the airfoil causes no restriction.
  • the shroud 6 has a projection 18 which faces towards the rotor surface 19.
  • a seal 20 is arranged in the front region of the shroud 6.
  • the seal 20 may be formed as a labyrinth seal 21 or as a brush seal 22.
  • FIG. 2 is a cross-sectional view (seen in the flow direction 10) of the turbomachine 1 is shown.
  • the rotor 3 rotates in a direction of rotation 23.
  • the direction of rotation 23 points in a clockwise direction.
  • the rotation takes place about a rotation axis 24.
  • the swirl bore 12 is inclined at an angle ⁇ to a tangential 25 of the Leitschaufeldeckbandober Structure 26.
  • the angle ⁇ can have values between 10 ° and 60 °.
  • the swirl hole 12 is designed as a bore. However, other embodiments of the swirl bore 12 can be considered.
  • the swirl hole 12 may also have a curved course.
  • the first part rotor 3a is formed of a high heat resistant 1% chromium material.
  • the second partial rotor 3b may be formed of a less thermally loaded and cheaper material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Heat Treatment Of Articles (AREA)

Claims (14)

  1. Turbomachine ( 1 ),
    comprenant un carter (2) et un rotor (3) monté tournants à l'intérieur du carter ( 2 ),
    dans laquelle le rotor ( 3 ) est formé de deux sous-rotors ( 3a, 3b ) et
    les deux sous-rotors ( 3a, 3b ) sont soudés l'un à l'autre, ce qui forme une zone (4) de soudure,
    dans laquelle il est prévu des moyens (6, 12) de refroidissement pour refroidir la zone ( 4 ) de soudure, dans laquelle la turbomachine ( 1 ) comprend au moins une rangée ( 5 ) d'aubes directrices et la rangée ( 5 ) d'aubes directrices a des aubes ( 7 ) directrices constituées en ayant des bande ( 6 ) de couverture,
    caractérisé en ce que
    la bande (6) de couverture est réalisée en ayant des trous ( 12 ) de tourbillonnement pour le guidage sur la zone ( 4 ) de soudure d'un fluide en écoulement s'écoulant en fonctionnement dans la turbomachine ( 1 ).
  2. Turbomachine ( 1 ) suivant la revendication 1,
    dans laquelle la bande ( 6 ) de couverture est au-dessus de la zone ( 4 ) de soudure.
  3. Turbomachine ( 1 ) suivant la revendication 1 ou 2,
    dans laquelle la longueur ( 14 ) de la bande ( 6 ) de couverture,
    considérée dans la direction d'écoulement,
    est plus grande que la longueur de la projection ( 15 ) du profil ( 13 ) de l'aube directrice sur un plan parallèle à la direction ( 10 ) de l'écoulement.
  4. Turbomachine ( 1 ) suivant la revendication 3,
    dans laquelle le trou ( 12 ) de tourbillonnement est disposé dans une partie de la bande ( 6 ) de couverture, qui, considérée dans la direction ( 10 ) d'écoulement, est avant le bord ( 17 ) avant de l'aube directrice.
  5. Turbomachine ( 1 ) suivant l'une des revendications 3 ou 4,
    dans laquelle le trou ( 12 ) de tourbillonnement est incliné d'un angle α par rapport à la direction ( 10 ) d'écoulement.
  6. Turbomachine ( 1 ) suivant la revendication 5,
    dans laquelle l'angle α a une valeur comprise entre 30° et 90°.
  7. Turbomachine ( 1 ) suivant l'une des revendications 1 à 6,
    dans laquelle le trou ( 12 ) de tourbillonnement est incliné d'un angle β par rapport à une tangente ( 25 ) à la surface de la bande de couverture de l'aube directrice.
  8. Turbomachine ( 1 ) suivant la revendication 7,
    dans laquelle l'angle β a une valeur comprise entre 10° et 60°.
  9. Turbomachine ( 1 ) suivant l'une des revendications 1 à 8,
    dans laquelle la bande ( 6 ) de couverture a,
    considérée dans la direction ( 10 ) de l'écoulement,
    sur la partie ( 16 ) avant une saillie ( 18 ), qui pointe vers la surface ( 19 ) du rotor.
  10. Turbomachine ( 1 ) suivant la revendication 9,
    dans laquelle la partie ( 16 ) avant comprend une étanchéité ( 20 ) de rotor.
  11. Turbomachine ( 1 ) suivant la revendication 10,
    dans laquelle l'étanchéité ( 20 ) de rotor est constituée en étanchéité en labyrinthe ( 21 ) ou en étanchéité à balai ( 22 ).
  12. Turbomachine ( 1 ) suivant l'une des revendications précédentes,
    dans laquelle le premier sous-rotor ( 3a ) est en un matériau résistant à la chaleur à 1 % de chrome.
  13. Turbomachine ( 1 ) suivant l'une des revendications précédentes,
    constituée en turbine à vapeur.
  14. Turbomachine ( 1 ) suivant l'une des revendications précédentes,
    dans laquelle la turbomachine ( 1 ) est constituée en turbine à vapeur à haute pression.
EP06017817A 2006-08-25 2006-08-25 Rotor avec cordon de soudure refroidi par tourbillon Not-in-force EP1895094B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE502006007968T DE502006007968D1 (de) 2006-08-25 2006-08-25 Drallgekühlte Rotor-Schweissnaht
EP06017817A EP1895094B1 (fr) 2006-08-25 2006-08-25 Rotor avec cordon de soudure refroidi par tourbillon
AT06017817T ATE483096T1 (de) 2006-08-25 2006-08-25 Drallgekühlte rotor-schweissnaht

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06017817A EP1895094B1 (fr) 2006-08-25 2006-08-25 Rotor avec cordon de soudure refroidi par tourbillon

Publications (2)

Publication Number Publication Date
EP1895094A1 EP1895094A1 (fr) 2008-03-05
EP1895094B1 true EP1895094B1 (fr) 2010-09-29

Family

ID=37633615

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06017817A Not-in-force EP1895094B1 (fr) 2006-08-25 2006-08-25 Rotor avec cordon de soudure refroidi par tourbillon

Country Status (3)

Country Link
EP (1) EP1895094B1 (fr)
AT (1) ATE483096T1 (fr)
DE (1) DE502006007968D1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2180149B1 (fr) * 2008-08-11 2016-12-21 Mitsubishi Hitachi Power Systems, Ltd. Ensemble turbine à vapeur

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH353218A (de) * 1957-09-18 1961-03-31 Escher Wyss Ag Aus Scheiben zusammengesetzter Läufer einer Axialturbine
US3291447A (en) * 1965-02-15 1966-12-13 Gen Electric Steam turbine rotor cooling
DE3209506A1 (de) * 1982-03-16 1983-09-22 Kraftwerk Union AG, 4330 Mülheim Axial beaufschlagte dampfturbine, insbesondere in zweiflutiger ausfuehrung
DE19839592A1 (de) * 1998-08-31 2000-03-02 Asea Brown Boveri Strömungsmaschine mit gekühlter Rotorwelle
EP1342882B1 (fr) * 1998-12-10 2006-05-17 ALSTOM Technology Ltd Procédé de fabrication d'un rotor soudé de turbomachine
EP1013879A1 (fr) * 1998-12-24 2000-06-28 Asea Brown Boveri AG Arbre de turbomachine à refroidssement par liquide
DE10355738A1 (de) * 2003-11-28 2005-06-16 Alstom Technology Ltd Rotor für eine Turbine

Also Published As

Publication number Publication date
EP1895094A1 (fr) 2008-03-05
DE502006007968D1 (de) 2010-11-11
ATE483096T1 (de) 2010-10-15

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