EP1013879A1 - Arbre de turbomachine à refroidssement par liquide - Google Patents

Arbre de turbomachine à refroidssement par liquide Download PDF

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Publication number
EP1013879A1
EP1013879A1 EP98811267A EP98811267A EP1013879A1 EP 1013879 A1 EP1013879 A1 EP 1013879A1 EP 98811267 A EP98811267 A EP 98811267A EP 98811267 A EP98811267 A EP 98811267A EP 1013879 A1 EP1013879 A1 EP 1013879A1
Authority
EP
European Patent Office
Prior art keywords
shaft
cooling medium
heat engine
cavity
engine according
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Withdrawn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
EP98811267A
Other languages
German (de)
English (en)
Inventor
Pierre Meylan
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.)
ABB Asea Brown Boveri Ltd
ABB AB
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 EP98811267A priority Critical patent/EP1013879A1/fr
Publication of EP1013879A1 publication Critical patent/EP1013879A1/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Withdrawn legal-status Critical Current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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/185—Liquid cooling
    • 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
    • F01D5/088—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in a closed cavity

Definitions

  • FIG. 1 schematically shows the shaft 20 of a gas turbine. Elements that are not are necessary for a direct understanding of the invention, such as for example the bearing of the shaft are omitted.
  • On her outside The circumference is essentially with compressor rotor blades 50 and Turbine blades 60 provided which the compressor section 5 and define the turbine section 7.
  • the shaft includes a cavity 40 and means 22 for supplying a fresh cooling medium 41 into the cavity and Means 21 for removing a heated cooling medium 42 from the cavity. in the The shaft is operated in particular in the turbine part 7 and between the A hot gas flows around the turbine part 7 and the compressor part 5, whose temperature is higher than the permissible material temperature of the shaft 20 is.
  • the cavity 40 is filled with a liquid during operation.
  • the radial position of the inlet or return openings 21, 22 is not primary here essential to the invention; however, it will be expedient if, as in FIG. 1, the inlets are arranged closer to the axis of rotation 10 of the shaft than the Returns 42. This is because the liquid within the Cavity rotates with the shaft 20 about the axis of rotation 10.
  • the cooling liquid 41 which through the inlets 22 in flows into the cavity 40, is conveyed radially outwards, and flows, after absorbing heat from the shaft, through the returns 21 from.
  • the shaft thus conveys the coolant itself.
  • the rotation of the shaft builds up in the cavity 40 a pressure field such that the liquid in the cavity 40 is in shape a solid body vortex with the shaft 20 rotates about the axis of rotation 10, and thus the pressure in the liquid increases from the center to the outside.
  • a coolant return 21 flows thus heated coolant due to the hydrostatic pressure distribution towards lower pressure, i.e. towards the center of the shaft, and is replaced by cool medium, which continues to be a good one Heat transfer between the material of the shaft 20 and the coolant contributes.
  • the hydrostatic pressure distribution within the cavity 40 enables also the cooling of exposed segments of the shaft through blind holes, which is shown in Fig. 2.
  • the figure shows the turbine section of a shaft 20, which with radial guide grooves for receiving blades 60th is provided.
  • protruding brackets 25 are provided.
  • the brackets 25 are on your surface of the Hot gas flow immediately exposed and consequently thermally particularly heavily loaded.
  • the brackets are also mechanical heavily stressed because they hold the centrifugal blades 60 and their circumferential force must be transferred to the shaft.
  • Coolant which is heated in the blind holes 405, or even evaporates, flows through a due to the pressure distribution described natural convection flow back into the cavity 40 and is by fresh coolant replaced.
  • the cooled gas turbine shaft described can be in a variety of Circuit variants for cooling thermally highly stressed components and to increase the output of gas turbines, as they are integrated for example from EP 0 597 305 B1, DE 44 09 567 A1, US 5 689 948, or EP 0 808 994 A2 are known.
  • a Liquid-cooled shaft according to the invention also as a preheating stage in one Combi system can be used. Liquid heated in the wave -to Example water - can be used anywhere to increase performance or be introduced into a gas turbine cycle to reduce nitrogen oxide, or serve to generate process steam.
  • FIG. 6 An example of a possible process control is shown in FIG. 6.
  • a Gas turbine consists essentially of a rotor 20 and a stator or Housing 72. An amount of air 81 is sucked in from the environment, and in Compressor 5 compresses. The compressed air becomes a in the combustion chamber 6 Amount of fuel 82 supplied and burned. The resulting hot gas is then relaxed in the turbine 7, applying torque to the rotor is transmitted. The extracted hot gas in the turbine Power serves to drive the compressor 5 and a payload, for example a generator 73. A hot gas flows from the turbine 83, from which heat is further removed in a waste heat steam generator 75 becomes. A pump 77 delivers a quantity of liquid 45, for example Water, at an elevated pressure.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP98811267A 1998-12-24 1998-12-24 Arbre de turbomachine à refroidssement par liquide Withdrawn EP1013879A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP98811267A EP1013879A1 (fr) 1998-12-24 1998-12-24 Arbre de turbomachine à refroidssement par liquide

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811267A EP1013879A1 (fr) 1998-12-24 1998-12-24 Arbre de turbomachine à refroidssement par liquide

Publications (1)

Publication Number Publication Date
EP1013879A1 true EP1013879A1 (fr) 2000-06-28

Family

ID=8236508

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98811267A Withdrawn EP1013879A1 (fr) 1998-12-24 1998-12-24 Arbre de turbomachine à refroidssement par liquide

Country Status (1)

Country Link
EP (1) EP1013879A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1306521A1 (fr) * 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor
DE10208085A1 (de) * 2002-02-25 2003-09-04 Alstom Switzerland Ltd Rotor für eine thermische Turbomaschine
EP1536102A2 (fr) * 2003-11-28 2005-06-01 ALSTOM Technology Ltd Rotor pour une turbine à vapeur
EP1895094A1 (fr) * 2006-08-25 2008-03-05 Siemens Aktiengesellschaft Rotor avec cordon de soudure refroidi par tourbillon
EP3205817A1 (fr) * 2016-02-09 2017-08-16 Ansaldo Energia Switzerland AG Rotor refroidi par fluide pour une turbine à gaz

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902819A (en) * 1973-06-04 1975-09-02 United Aircraft Corp Method and apparatus for cooling a turbomachinery blade
DE2633829A1 (de) 1976-07-02 1978-01-05 Bbc Brown Boveri & Cie Verfahren zum verbinden von metallteilen mittels lichtbogen- schmelzschweissen
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
DE4409567A1 (de) 1994-03-21 1995-09-28 Abb Management Ag Verfahren zur Kühlung von thermisch belasteten Komponenten einer Gasturbogruppe
US5454220A (en) 1993-04-08 1995-10-03 Abb Management Ag Method of operating gas turbine group with reheat combustor
DE4411616A1 (de) 1994-04-02 1995-10-05 Abb Management Ag Verfahren zum Betreiben einer Strömungsmaschine
EP0597305B1 (fr) 1992-11-07 1996-05-29 Asea Brown Boveri Ag Procédé de functionnement d'une centrale à cycle combiné
EP0761929A1 (fr) 1995-08-25 1997-03-12 Asea Brown Boveri Ag Rotor pour turbomachines thermiques
DE19615549A1 (de) 1996-04-19 1997-10-23 Asea Brown Boveri Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
DE19617539A1 (de) 1996-05-02 1997-11-13 Asea Brown Boveri Rotor für eine thermische Turbomaschine
US5689948A (en) 1995-03-07 1997-11-25 Asea Brown Boveri Ag Method of operating a reheat power plant with steam injection
EP0808994A2 (fr) 1996-04-22 1997-11-26 Asea Brown Boveri Ag Procédé de fonctionnement d'une centrale combinée

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3902819A (en) * 1973-06-04 1975-09-02 United Aircraft Corp Method and apparatus for cooling a turbomachinery blade
DE2633829A1 (de) 1976-07-02 1978-01-05 Bbc Brown Boveri & Cie Verfahren zum verbinden von metallteilen mittels lichtbogen- schmelzschweissen
US4260336A (en) * 1978-12-21 1981-04-07 United Technologies Corporation Coolant flow control apparatus for rotating heat exchangers with supercritical fluids
EP0597305B1 (fr) 1992-11-07 1996-05-29 Asea Brown Boveri Ag Procédé de functionnement d'une centrale à cycle combiné
US5454220A (en) 1993-04-08 1995-10-03 Abb Management Ag Method of operating gas turbine group with reheat combustor
US5577378A (en) 1993-04-08 1996-11-26 Abb Management Ag Gas turbine group with reheat combustor
DE4409567A1 (de) 1994-03-21 1995-09-28 Abb Management Ag Verfahren zur Kühlung von thermisch belasteten Komponenten einer Gasturbogruppe
DE4411616A1 (de) 1994-04-02 1995-10-05 Abb Management Ag Verfahren zum Betreiben einer Strömungsmaschine
US5689948A (en) 1995-03-07 1997-11-25 Asea Brown Boveri Ag Method of operating a reheat power plant with steam injection
EP0761929A1 (fr) 1995-08-25 1997-03-12 Asea Brown Boveri Ag Rotor pour turbomachines thermiques
DE19615549A1 (de) 1996-04-19 1997-10-23 Asea Brown Boveri Vorrichtung zum thermischen Schutz eines Rotors eines Hochdruckverdichters
EP0808994A2 (fr) 1996-04-22 1997-11-26 Asea Brown Boveri Ag Procédé de fonctionnement d'une centrale combinée
DE19617539A1 (de) 1996-05-02 1997-11-13 Asea Brown Boveri Rotor für eine thermische Turbomaschine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1306521A1 (fr) * 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor
DE10208085A1 (de) * 2002-02-25 2003-09-04 Alstom Switzerland Ltd Rotor für eine thermische Turbomaschine
EP1536102A2 (fr) * 2003-11-28 2005-06-01 ALSTOM Technology Ltd Rotor pour une turbine à vapeur
EP1536102A3 (fr) * 2003-11-28 2012-08-22 Alstom Technology Ltd Rotor pour une turbine à vapeur
EP1895094A1 (fr) * 2006-08-25 2008-03-05 Siemens Aktiengesellschaft Rotor avec cordon de soudure refroidi par tourbillon
EP3205817A1 (fr) * 2016-02-09 2017-08-16 Ansaldo Energia Switzerland AG Rotor refroidi par fluide pour une turbine à gaz

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