EP1452688A1 - Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor - Google Patents

Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor Download PDF

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Publication number
EP1452688A1
EP1452688A1 EP20030002472 EP03002472A EP1452688A1 EP 1452688 A1 EP1452688 A1 EP 1452688A1 EP 20030002472 EP20030002472 EP 20030002472 EP 03002472 A EP03002472 A EP 03002472A EP 1452688 A1 EP1452688 A1 EP 1452688A1
Authority
EP
European Patent Office
Prior art keywords
steam turbine
turbine rotor
cooling
blade
rotor
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.)
Withdrawn
Application number
EP20030002472
Other languages
German (de)
English (en)
Inventor
Detlef Dr. Haje
Dietmar Dr. Röttger
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 EP20030002472 priority Critical patent/EP1452688A1/fr
Priority to JP2004027602A priority patent/JP4540357B2/ja
Priority to CNB2004100036673A priority patent/CN100462524C/zh
Priority to US10/773,038 priority patent/US7101144B2/en
Publication of EP1452688A1 publication Critical patent/EP1452688A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/081—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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam
    • 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
    • F05D2260/85—Starting

Definitions

  • a single guide vane ring is known from WO 97/49901 selectively through one of a central cavity fed to cool separate radial channel in the rotor.
  • To cooling medium is mixed into the working medium via the duct and the guide vane ring to be cooled selectively by cooling medium incident flow.
  • the cooling effect on the rotor is included improvement.
  • the hole causes disadvantageously a significant increase in the voltage of the rotor compared to the design without a hole.
  • the article mentioned is for improvement the cooling of a steam turbine rotor a cooling steam supply and passing the cooling steam through the first guide vane stage and possibly also through the second guide vane stage proposed.
  • This is an active cooling provided only for the steam turbine housing. moreover is cooling on the main flow area of the working medium limited and in need of improvement.
  • the invention is based on the consideration that to provide sufficient cooling of a steam turbine rotor one over the inflow area of the working medium and one via the only separate cooling of the first blade stage active cooling beyond that within a steam turbine rotor should be provided.
  • the knowledge of the invention is that this is with a consistent in the rotor integrated implementation can be achieved, at least goes beyond a blade stage.
  • the part at least goes beyond the inflow area and at least goes beyond a blade level.
  • Advantageously extends the part extends over at least two blade levels, conveniently over several stages of barrel blading. In order to the possibility is created of using a cooling fluid of a coherent feed-through system integrated in the rotor to run consistently.
  • Such an implementation system is advantageously close to the surface arranged to the outside of the steam turbine rotor.
  • near-surface means in particular that the implementation system, especially the at least one Implementation, in a range of radial expansion Steam turbine rotor is arranged, which through the outside of the rotor on the one hand and the internal radial expansion a blade groove on the other hand is limited.
  • the at least one implementation and / or any other Implementation of the implementation system can be done as needed advantageously as a channel or as any Kind of cavity inside the rotor, preferably in its near-surface area.
  • the proposed cooling concept within of the steam turbine rotor mentioned is thus more effective as one near a central cavity on the inside the rotor wall adjacent to the axis for the Cooling attacking rotor.
  • the cooling according to the proposed concept is reinforced also the benefits of thermal insulation layers on the rotor and shovels. Such layers have a comparative low thermal conductivity and can under provided that there is an adequate heat sink is to build up a high temperature difference.
  • blade feet and sometimes also blades are kept at a much lower temperature than without an insulation layer.
  • an insulation layer or in combination with such can Use of the proposed cooling concept, the application of less well conductive blade materials makes sense his. A preferred example of this are, for example austenitic materials.
  • a coherent implementation system expediently points one along a circumferential extension of the rotor at least partially circumferential channel. Together with the allows at least one axially extending implementation this is an overall cooling of the steam turbine rotor, preferably near its outside.
  • the at least one implementation can be done as needed To run. So it turns out to be convenient if the implementation through a shovel, in particular through a shovel foot, is led. There could be a groove on a blade root be part of the implementation. If need be, too a bore through a single blade root or, alternatively or in addition, by two adjacent blade feet part the implementation. It also proves to be cheap to provide a channel in an airfoil that matches the Implementation is connected. In this way is an advantageous cooling of the blade area z. B. possible via film cooling.
  • the object is achieved by the invention with a method for active cooling of a steam turbine rotor solved the type mentioned in the invention is provided along a fluid cooling medium the axial extent at least between one before the first Positioned first area and one behind the first area arranged second area consistently to lead.
  • the cooling medium is advantageously at a temperature and / or supplied in an amount that is dependent is adapted to a temperature of the main flow. This can advantageous due to security requirements sufficient valve to regulate the quick-closing and control processes of the turbine valves.
  • the temperature of the cooling medium is according to safety-related Determine requirements advantageously and technically to monitor. If necessary, a disproportionate amount of cooling medium in the feedthrough system be introduced so that the temperature of the main flow after the cooled blading area by reinforced Admixture of cooling medium kept sufficiently low becomes.
  • the rotor is in a particularly advantageous embodiment and / or the turbine blades with a heat insulation coating Mistake.
  • Such heat insulation layers have usually a comparatively low coefficient of thermal conductivity on and can, provided that locally a suitable heat sink is provided, a high one Build up temperature difference.
  • the function of this heat sink can be taken over by the cooling system provided here so that the rotor designed in this way for the Use of heat insulation layers particularly suitable is. It can rotor, blade feet and possibly also Shovel blades at a much lower temperature are kept as without such insulation layers.
  • alternative to or in combination with the use of insulation layers can also use it comparatively poorly heat-conductive blade materials such as austenitic materials can be provided.
  • the preferred embodiment of the invention is related described with a cooling system that has a pressure-adjusted Cooling steam mass flow provides the rotating Components, i.e. the rotor and the blades, targeted can cool.
  • the preferred one proposed here Embodiment makes a significant contribution to cost-effective, industrial feasibility higher Achieve steam parameters and higher efficiencies.
  • one described here or different and modified embodiment of the invention also used are used to make more cost-effective rotor and blade materials current steam parameters.
  • a steam turbine 1 which is a cooling system limited to cooling in the inflow area having.
  • This has one rotatable on an axis 2 arranged rotor 3, on the tubular shaft a number of Rotor blades 4 is arranged. These are in a stationary Housing 5 arranged with a guide blading 6.
  • the Rotor 3 is on the rotor blades 4 by the in the inflow area 7 inflowing working medium 8 driven. additionally to the working medium 8 flows through a separate entrance area 9 a cooling medium 10 to the working medium 8.
  • cooling steam 10a is passed through a separate branch channel 16a a substantially central Cavity 16b, which runs parallel to the rotor axis, supplied. From there, such cooling steam 10a is also separated radial branch channels 16 led out again.
  • the Cooling steam 10a again becomes the main flow in areas 16c supplied to cool the rotor in one place.
  • the cooling medium 10a essentially flows around the rotor 3 in an inflow region 7 and in a central cavity 16b. This ensures effective cooling of the rotor itself not given, because the cooling medium is guided in the central Cavity 16b takes place away from the rotor surface and thus not in a place of heat input.
  • the separate channels 16a, 16 are as branch channels for cooling a specific one Place the rotor trained and can also not be effective Cooling of the rotor 3 cause radially from one central cavity 16b to an area of the main flow 16c run.
  • the cooling of a rotor shown here according to the prior art is still in need of improvement it does not provide near-surface cooling.
  • the central cavity also occurs comparatively high rotor stress, but also the Processing effort for the attachment of the branch channels increased is.
  • this concept does not offer a sufficient one Shielding the rotor shaft from the main flow of the Steam.
  • FIG. 2 shows a schematic representation of a steam turbine 20 according to a particularly preferred embodiment.
  • This has a rotor 21 with a number of rotor blades 24 on which is rotatable in a housing 23 with a number of Guide blades 22 is mounted.
  • Turbine 20 with rotor 21 and Housing 23 extend along an axial extent 25.
  • the rotatable rotor blades 24 grip like Fingers in spaces between the stationary guide vanes 22nd
  • the rotor 21 shown here has an outer side 26a.
  • the outside 26a borders on one for receiving a main flow 27 of a fluid working medium provided outside space 27a.
  • the rotor has a number of locations on the outside 26a, in each of which one row of blades 24 is held. It extends according to the particularly preferred Embodiment a channel system 28 for guiding a Cooling medium from a first area 28a along the locations for the blades 24 up to a second region 28b continuously.
  • the channel system has along the axial extent 25 a number of openings 29 to the main flow 27. This serve in cooperation with the passage openings of the Channel system for the gradual pressure reduction of the cooling medium parallel to the main flow 27.
  • From stage to stage of Blades 24 can preferably pass through the cooling medium Flow resistances are throttled. For this, for example in each case at a blade stage 24, the Passage of the cooling medium through a hole.
  • the cooling medium has a similar pressure and lower Temperature a higher density than the flow medium in the main flow, which results in better heat transfer behavior results.
  • Steam turbine rotor also a variant not shown here of a cooling system as a closed cooling system be provided.
  • a closed cooling system a Delivery of the cooling medium to the main flow 27 not or only realized at the end of the refrigerated area. So it would the openings 29 of the open system of FIG 2 essentially omitted. Coolant would only come from a first one Area 28a passed to a second area 28b without thereby an immediate pressure adjustment to the main flow would be done. The gradual decrease in pressure could also by throttling. A levy of Cooling medium to the main flow does not take place in any case Blade level 24 instead.
  • the open channel system 28 has a continuous one close to the surface, from which several branches turn towards the openings 29. Furthermore, it acts in the embodiment shown here is also a coherent one Channel system 28 in the sense that if possible separate additional channels that run out of the rotor surface could be avoided. This has the advantage that the cooling steam mass flow can decrease from stage to stage and that the same cooling steam works over several stages can.
  • FIG 3 is a steam turbine rotor 30 according to the preferred Embodiment in the cooled blading area shown in more detail.
  • a corresponding steam turbine 31 also has a housing, not shown, with a guide blading 32 on.
  • the steam turbine rotor 30 sees a first one Site 30a and a second site 30b along the outside 33 before, along the axial extent 34 the second Point 30b is arranged behind the first point 30a.
  • the Outside 33 is adjacent to an outer space 35 which for Recording a main flow 36 of a fluid working medium is provided.
  • the outside is 33 not formed by the actual surface of the rotor shaft, but through a shielding plate that rotates with the rotor 38, which is held by the blade feet 39a, 39b is.
  • the blade feet 39a, 39b are still in blade grooves 40a, 40b anchored.
  • a number of blades 41a will along the circumference of the rotor 30 side by side and each arranged in radial orientation 42 and thus forms a first, also known as a blade stage at location 30a.
  • a number of second Scoops 41b circumferentially at a second location 30b arranged in the groove 40b and forms a second Blade row.
  • shielding plate 38 shown could also be worked on Shielding surface on the blade feet 39a, 39b. This would mean additional material and manufacturing costs may be required, however, a similar one Shielding effect can be achieved as with a shielding plate 38 and be beneficial as needed.
  • the channel system 43 of FIG 3 has at least one between a first area arranged in front of the first location 30a and one behind the first location 30a and in this embodiment also arranged behind the second location 30b second area continuously extending passage 44th on.
  • the bushing 44 extends in this embodiment practically along the entire blading area of the rotor (length as required).
  • Implementation 44 is on the one hand by the wall 37 of the rotor 30 and on the other formed by the shield plate 38.
  • a variety of such Feedthroughs 44 are circumferential in the axial direction 34 arranged along the outside 33 of the rotor 30.
  • the channel system 43 also has a number of circumferential Grooves 45 along that in this embodiment the axial extent 34 each at the level of a guide vane 32 are arranged.
  • the guide vane 32 has one Cover plate 32a.
  • the duct system 43 can by milling in the surface 37 of the rotor shaft be applied and by flat components of the Shielding plate 38 are covered.
  • the channel system refers 43 also blade grooves (FIG 9, FIG 10) and / or bores 46a, 46b (FIG 5, FIG 6, FIG 9, FIG 10) in blade roots 39a, 39b into the flow.
  • Shielding by a shielding plate 38 in the blading area can also shield the inflow area of the cooling medium by means of another shielding plate which is not shown here, and others Advantages with regard to the oxidation of the turbine rotor material brings with it.
  • a Implementation system 43 or an implementation 44, 45 also in Form of holes or other suitable means within of the rotor 30 near the surface.
  • FIG. 4 shows the view of section A-A of FIG. 3.
  • the circumferential groove 45 of FIG 3 is in dashed lines Line executed. Accordingly, the axial groove 44 is as Indentation in the surface 37 of the rotor shaft of the Steam turbine rotor indicated schematically.
  • FIG. 5 shows a possibility of making a bore 46a in a blade root 39a.
  • FIG. 6 An alternative embodiment of the bores 46a, 46a 'in FIG. 3 is shown in FIG. 6 as bore 46a ".
  • a bore 46a" is attached in two adjacent blade roots 39a ".
  • FIG. 7 shows a possibility 70 for the transmission of a cooling medium 71 from an area 72 in front of a first row of guide vanes 78 in a further area 73 of the blade attachment along the axial extent 74 behind the first Guide vane series 78.
  • An inner housing is shown here 76 a, which in an outer casing 76 of a steam turbine 77 is appropriate.
  • the cooling medium can be supplied via a feed 70 in a near-surface channel system 79 is introduced into the rotor 75 be and along the axial extent 74 in the area of Run blading 75a are performed. In parallel, it can Coolant flow through the sealing area (cooling, Reduction of enthalpy losses).
  • the flow 69 of the cooling medium 71 in the outer housing 76 is used Cooling the outer case.
  • the inflow of the cooling medium will valves that meet safety requirements regulated.
  • FIG. 7 shows another advantageous Possibility of introducing cooling medium 80 at a preferred embodiment, which in a turbine 1 1 according to the prior art is now close to the surface Provides cooling.
  • the corresponding ones Parts of the turbine 1 according to the prior art and Turbine 81 according to the particularly preferred embodiment are provided with the same reference numerals.
  • the cooling medium 80 is on the one hand via an entrance area 9, as already in 1 shows an inflow region of the working medium 8 fed.
  • the cooling medium 80 is covered by a shield 12 passed through and in a room 82 behind the Shielding plate 12, the cooling medium 80 along the axial Expansion 85 within the rotor wall near the surface, d. H. in the area 84 of the attachment of the rotor blades 15 guided.
  • the cooling medium 80 is along the axial Extension 85 at least between one before the first Blade ring 15 arranged first area 82 and a arranged behind the first rotor blade ring 15 second Area 88 managed throughout.
  • the turbine 81, the first region 82 is used to Cooling medium 80 the near-surface axial bushing system to feed the rotor 83.
  • the cooling medium 80 can also practically along the entire run blading area of the rotor 83 (actual design (length) according to technical Requirements).
  • Measures to train the active cooling system can be provided in the turbine 81.
  • the cooling system as an open Cooling system designed.
  • the cooling medium escapes at the end of the duct system into the Main flow is not only the cooling medium of the main flow in pressure, but also in the temperature of the main flow largely adapted. This is due to the absorption of heat of the cooling medium in the cooled blading area. The cooling medium then takes part in further expansion in the mainstream Part. This is a particular advantage of an open one Cooling system, which thus enthalpy transport from the cooled Blading area in the non-cooled area.
  • the safety-related monitoring of the cooling medium has the embodiment shown here, especially the temperature of the cooling medium. It should be noted that a premature condensation / droplet formation in the flow and is excluded in the duct system even with partial loads. Of Furthermore, the essential components should overheat like rotor, blades or blade attachments for all relevant Load cases must be excluded. According to technical requirements there may be a mismatch between turbine valves and Coolant valves are provided.
  • the described channel system of the preferred embodiment can also be used advantageously for preheating purposes by suitable medium is fed in during the start-up process. This can also be done from other parts of the water-steam cycle be removed as the actual cooling medium.
  • the fact that the preheating medium has an advantageous effect is throttled in the duct system and at least here does not contribute to the start-up of a shaft train. Analog can this method can also be used for rapid cooling. For future rotors or rotor materials, the ones described can Approaches an advantage in terms of Offer arrival times and cooling times.
  • FIG. 9 shows a further design of a channel system for Conduction of the cooling medium in the area of a blade root 90, which is anchored in a groove 91 in a turbine rotor 92.
  • the axial feedthrough 93 of the preferred embodiment is in the area of a guide vane 94 deeper inside a Rotors 92 embedded and thus has an example triangular shape in the area of the housing blade 94 on. Any other course is possible.
  • Implementation 93 is open to the main flow via channels 99.
  • a blade groove 95 is also included in the implementation.
  • the implementation is carried out by a blade root 90 by means of a channel 96 which is above the waist 97 of the blade root arranged closer to the blade 98 is. This has the advantage that the strength of the Bucket foot waist 97 is not affected.
  • FIG. 10 shows a further design similar to that in FIG 9 shown.
  • a passage 106 also in the area of an airfoil 108.
  • the airfoil 108 proceed from the implementation 106 channels 110, which cooling medium from a bushing 106 to the airfoil surface 108 to to provide film cooling.
  • cooling medium is also channeled in the area 109 a housing blade 104 to the main flow of the working medium issued. More details 100, 101, 102, 103, 107 correspond to those shown in FIG.
  • FIG 11 shows a favorable arrangement of a first shielding plate 120 and a second shield plate 121 in the area a joint 122 shown.
  • the detailed version shown here can be advantageous with a shield 38 Through openings 123 and 124 in FIG 11 or 47, 48 and 49 be made in FIG 3.
  • Such a shield is advantageously from a suitable, e.g. B. heat resistant material manufactured. In this version it consists of sections 120, 121, which preferred 122 at their joints a cover that is movable for different temperatures 125, 126.
  • the shielding plate is located in the area of the guide vane cover plates and should be appropriate Sealing tips, d. H. have non-contact seals.
  • Sealing tips could be screwed all around, d. H. be made from the solid, or sealing tapes caulked become. What turns out to be advantageous can depending on the strength and manufacturing requirements of the material and the construction in detail.
  • the Loss of efficiency due to the flowing over these seals Leakage mass flow can be reduced.
  • the leakage mass flow exists in this case not from the hot medium of the main flow, but from cooling medium with lower enthalpy. possibly however, this effect is due to a smaller number of sealing tips due to the space required for introduction of the cooling medium is consumed again.
  • a steam turbine rotor is a steam turbine and a method for actively cooling a steam turbine rotor and a suitable use of the cooling is proposed Service.
  • a rotor In previously known steam turbines 1, a rotor is either only passively or only in an inflow area of the working medium actively cooled to a limited extent. With an increasing Stress on the rotor due to increased steam parameters the working medium is sufficient cooling of the steam turbine rotor no longer guaranteed.
  • At least one Implementation 44, 46a, 46b, 93, 96, 103, 106 provided the arranged, close to the surface, at least between one first region 28a, 72 arranged in front of the first point 30a and a second one located behind the second location 30b Area 28b, 73 extends continuously. It will be a procedure and proposed use in which a fluid cooling medium 10 is performed accordingly.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20030002472 2003-02-05 2003-02-05 Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor Withdrawn EP1452688A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP20030002472 EP1452688A1 (fr) 2003-02-05 2003-02-05 Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor
JP2004027602A JP4540357B2 (ja) 2003-02-05 2004-02-04 蒸気タービンロータと蒸気タービンおよび蒸気タービンロータの能動的冷却方法と能動的冷却の使用方法
CNB2004100036673A CN100462524C (zh) 2003-02-05 2004-02-05 汽轮机及其转子和主动冷却该转子的方法及该方法的应用
US10/773,038 US7101144B2 (en) 2003-02-05 2004-02-05 Steam turbine rotor, steam turbine and method for actively cooling a steam turbine rotor and use of active cooling

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20030002472 EP1452688A1 (fr) 2003-02-05 2003-02-05 Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor

Publications (1)

Publication Number Publication Date
EP1452688A1 true EP1452688A1 (fr) 2004-09-01

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EP20030002472 Withdrawn EP1452688A1 (fr) 2003-02-05 2003-02-05 Rotor pour une turbine à vapeur, procédé et utilisation de refroidissement d'un tel rotor

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US (1) US7101144B2 (fr)
EP (1) EP1452688A1 (fr)
JP (1) JP4540357B2 (fr)
CN (1) CN100462524C (fr)

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EP2031183A1 (fr) * 2007-08-28 2009-03-04 Siemens Aktiengesellschaft Arbre de turbine à vapeur doté d'une couche d'isolation thermique
FR2968707A1 (fr) * 2010-12-13 2012-06-15 Gen Electric Turbine a vapeur et circuit de refroidissement pour rotor tambour
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US8888436B2 (en) 2011-06-23 2014-11-18 General Electric Company Systems and methods for cooling high pressure and intermediate pressure sections of a steam turbine
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EP1788191B1 (fr) * 2005-11-18 2014-04-02 Siemens Aktiengesellschaft Turbine à vapeur et procédé pour le refroidissement d'une turbine à vapeur
EP1911933A1 (fr) * 2006-10-09 2008-04-16 Siemens Aktiengesellschaft Rotor pour une turbomachine
US8257015B2 (en) * 2008-02-14 2012-09-04 General Electric Company Apparatus for cooling rotary components within a steam turbine
US8282349B2 (en) * 2008-03-07 2012-10-09 General Electric Company Steam turbine rotor and method of assembling the same
DE102009021384A1 (de) * 2009-05-14 2010-11-18 Mtu Aero Engines Gmbh Strömungsvorrichtung mit Kavitätenkühlung
JP5193960B2 (ja) 2009-06-30 2013-05-08 株式会社日立製作所 タービンロータ
US8376687B2 (en) * 2009-10-13 2013-02-19 General Electric Company System and method for cooling steam turbine rotors
US8348608B2 (en) * 2009-10-14 2013-01-08 General Electric Company Turbomachine rotor cooling
US20110158819A1 (en) * 2009-12-30 2011-06-30 General Electric Company Internal reaction steam turbine cooling arrangement
US8376689B2 (en) * 2010-04-14 2013-02-19 General Electric Company Turbine engine spacer
EP2386767B1 (fr) * 2010-05-11 2021-01-06 Sulzer Management AG Pompe hélico-axiale et procédé pour supporter un rotor dans une pompe hélico-axiale
JP5495995B2 (ja) * 2010-07-14 2014-05-21 三菱重工業株式会社 コンバインドサイクル発電装置
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EP2520764A1 (fr) * 2011-05-02 2012-11-07 MTU Aero Engines GmbH Aube avec pied refroidi
US9739151B2 (en) 2011-05-02 2017-08-22 Mtu Aero Engines Gmbh Blade, integrally bladed rotor base body and turbomachine
US8888436B2 (en) 2011-06-23 2014-11-18 General Electric Company Systems and methods for cooling high pressure and intermediate pressure sections of a steam turbine
US8899909B2 (en) 2011-06-27 2014-12-02 General Electric Company Systems and methods for steam turbine wheel space cooling
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JP4540357B2 (ja) 2010-09-08
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US20040247433A1 (en) 2004-12-09
CN100462524C (zh) 2009-02-18
CN1526916A (zh) 2004-09-08

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