EP1784557B1 - Injection de fluide dans une turbine lors d'une période de refroidissement - Google Patents

Injection de fluide dans une turbine lors d'une période de refroidissement Download PDF

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Publication number
EP1784557B1
EP1784557B1 EP05777877A EP05777877A EP1784557B1 EP 1784557 B1 EP1784557 B1 EP 1784557B1 EP 05777877 A EP05777877 A EP 05777877A EP 05777877 A EP05777877 A EP 05777877A EP 1784557 B1 EP1784557 B1 EP 1784557B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
compressor
liquid
turbine
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.)
Not-in-force
Application number
EP05777877A
Other languages
German (de)
English (en)
Other versions
EP1784557A1 (fr
Inventor
Hajrudin Ceric
Giuseppe Gaio
Frank GÜNTHER
Gabriel Jungnickel-Marques
Stefan Wanz
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
Huelfenhaus Armin
Huelsemann Gerhard
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 Huelfenhaus Armin, Huelsemann Gerhard, Siemens AG filed Critical Huelfenhaus Armin
Priority to EP05777877A priority Critical patent/EP1784557B1/fr
Priority to ES05777877T priority patent/ES2304709T3/es
Publication of EP1784557A1 publication Critical patent/EP1784557A1/fr
Application granted granted Critical
Publication of EP1784557B1 publication Critical patent/EP1784557B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34—Turning or inching gear
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
    • F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
    • F04D29/705—Adding liquids
    • 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
    • F05D2260/212—Heat transfer, e.g. cooling by water injection

Definitions

  • the invention relates to a method for cooling a gas turbine with a compressor, a turbine unit and with a rotor, which is carried out after the operation of the gas turbine and in which the rotor is at least temporarily driven during a cooling phase at a reduced rated speed.
  • the object of the invention is to provide a method for cooling a gas turbine with a rotor, which causes even faster cooling of the gas turbine to further reduce the service life of the gas turbine.
  • the solution provides that for faster cooling at least temporarily during the cooling phase, a liquid is introduced before the compressor in the air stream, which flows through the flow channel of the compressor and the turbine unit of the gas turbine.
  • the invention is based on the idea that by introducing a liquid into the air stream, the liquid stream enriched with liquid can take up and remove a larger amount of heat per unit of time from the still heated gas turbine. This leads to faster cooling of the gas turbine than in the previously known from the prior art method.
  • the gas turbine can be cooled faster along its entire longitudinal extent along the rotor. Consequently, the compressor, the combustion chamber and the turbine unit are flowed through by the cooled air flow during the implementation of the method.
  • the air flow is cooled only after flowing through the compressor.
  • the faster cooling of the gas turbine allows inspections, inspections and maintenance to be carried out earlier by the installation staff. This reduces the service life of the gas turbine and increases its availability.
  • the embodiment of the method in which the rotational speed of the rotor during the liquid introduction is higher than the rotational speed at which no liquid introduction takes place. Due to the higher speed, more air is pumped through the gas turbine. Thus, the airflow can absorb more liquid without water retention causing cracks or crack growth on the components of the gas turbine.
  • the introduction of the liquid takes place by means of a compressor washing device.
  • Design changes to the gas turbine are not necessary for carrying out the method, so that the retrofitting of existing gas turbines for performing such a method is particularly inexpensive and easy.
  • the compressor washing device can also be used a Eindüsvoriques for a liquid which is provided at the compressor inlet and which injects a liquid in the sucked ambient air during operation of the gas turbine to increase the mass flow.
  • This method which is carried out during operation of the gas turbine, is known by the term "wet compression” or else "wet compression”.
  • FIG. 1 a gas turbine 1 with a rotatably mounted about a rotational axis 3 rotor fifth
  • the gas turbine 1 has an intake chamber 7, a compressor 9, a toroidal annular combustion chamber 11 and a turbine unit 13.
  • Both in the compressor 9 and in the turbine unit 13 guide vanes 15 and blades 17 are each arranged in rings.
  • a blade ring 19 is followed by a blade ring 21.
  • the rotor blades 17 are fastened to the rotor 5 by means of rotor disks 23, whereas the stator blades 15 are fixedly mounted on the housing 25.
  • Wreaths 21 of guide vanes 15 are likewise arranged in the turbine unit 13, which, viewed in the direction of the flow medium, is followed by a ring of rotor blades 17.
  • the respective blade profiles of the guide vanes 15 and of the rotor blades 17 extend in a radial manner in an annular flow channel 27 extending through the compressor 9 and the turbine unit 13.
  • air 29 is sucked through the intake manifold 7 and compressed by the compressor.
  • the compressed air is guided to the burners 33, which are provided on a ring lying on the annular combustion chamber 11.
  • the compressed air 29 is mixed with a fuel 35, which mixture in the annular combustion chamber 11 is burned to a hot gas 37.
  • the hot gas 37 flows through the flow channel 27 of the turbine unit 13 past guide vanes 15 and blades 17.
  • the hot gas 37 relaxes on the blades 17 of the turbine unit 13 to perform work.
  • the rotor 5 of the gas turbine 1 in a rotational movement with its rated speed, for example, 3000 min -1 or 3600 min -1 , which serves to drive the compressor 9 and to drive a working engine or generator, not shown.
  • FIG. 2 shows a cross section through the intake 7 of the gas turbine 1.
  • the air inlet-side end 39 of the compressor 9 with the centrally mounted rotor 5 is shown in cross section.
  • only a few of the guide vanes 15 arranged in the flow channel 27 are shown.
  • a device 41 for introducing, in particular injection of a liquid 43, for example distilled water, is arranged.
  • the device 41 can be, for example, a compressor washing device 45 or a injection circuit for wet compression.
  • the method for cooling the gas turbine 1 is performed.
  • the rotor 5 is driven by a rotating device, not shown, at a reduced speed, for example in the range of 80 min -1 to 160 min -1 , preferably at 120 min -1 , to cool it.
  • the rotor 5 pumps in relation to the operation
  • the gas turbine 1 thus sucks in a comparatively small air mass flow and pumps it through the section of the flow channel 27 arranged in the compressor, through the combustion chamber and through the turbine unit 13 arranged portion of the flow channel 27th
  • the cooling process is further accelerated by additionally called distilled water in front of the compressor 9 in the intake air flow during the rotary operation, also called cooling operation.
  • the evaporation of the water cools the sucked-in air flow, as a result of which, as it flows through the gas turbine 1, it increasingly absorbs and removes the heat stored in the gas turbine 1.
  • the rotational speed of the rotor 5 can be increased, for example to 4% to 10% of the nominal rotational speed.
  • the introduction of the liquid 43 can take place by suitable means both in the annular combustion chamber 11 and in the flow channel 27 of the turbine unit 13.

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)
  • Separation By Low-Temperature Treatments (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Nonmetallic Welding Materials (AREA)
  • Ceramic Products (AREA)

Claims (5)

  1. Procédé de refroidissement d'une turbine (1) à gaz comprenant un compresseur (9), un groupe (13) de turbine et un rotor (5),
    qui s'effectue à la suite du fonctionnement de la turbine (1) à gaz et dans lequel le rotor (5) est entraîné au moins de temps en temps pendant une phase de refroidissement à une vitesse de rotation nominale diminuée,
    caractérisé
    en ce que pour le refroidissement on introduit, au moins de temps en temps, pendant la phase de refroidissement, un liquide (43) en amont du compresseur (9) dans le courant d'air, qui passe dans au moins le canal (27) d'écoulement du compresseur (9) et dans le canal (27) d'écoulement du groupe (13) de la turbine (1) à gaz.
  2. Procédé suivant la revendication 1,
    caractérisé
    en ce que la vitesse de rotation du rotor (5) est pendant l'introduction du liquide, plus grande que la vitesse de rotation alors qu'il n'y a pas d'introduction de liquide.
  3. Procédé suivant la revendication 1 ou 2,
    caractérisé
    en ce qu'on effectue l'injection du liquide (43) au moyen d'un dispositif (45) de lavage du compresseur.
  4. Procédé suivant la revendication 1,2 ou 3,
    caractérisé
    en ce que l'on effectue une introduction supplémentaire de liquide (43) dans une chambre de combustion de la turbine (1) à gaz ou dans le canal (27) d'écoulement du groupe (13) de turbine.
  5. Procédé suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que l'on utilise de l'eau distillée comme liquide (43).
EP05777877A 2004-08-25 2005-08-12 Injection de fluide dans une turbine lors d'une période de refroidissement Not-in-force EP1784557B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP05777877A EP1784557B1 (fr) 2004-08-25 2005-08-12 Injection de fluide dans une turbine lors d'une période de refroidissement
ES05777877T ES2304709T3 (es) 2004-08-25 2005-08-12 Inyeccion de liquido en una turbina de gas durante una fase de refrigeracion.

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04020155A EP1630356A1 (fr) 2004-08-25 2004-08-25 Injection de fluide dans une turbine lors d'une periode de de refroidissement
EP05777877A EP1784557B1 (fr) 2004-08-25 2005-08-12 Injection de fluide dans une turbine lors d'une période de refroidissement
PCT/EP2005/053969 WO2006021520A1 (fr) 2004-08-25 2005-08-12 Injection de fluide dans une turbine a gaz pendant une phase de refroidissement

Publications (2)

Publication Number Publication Date
EP1784557A1 EP1784557A1 (fr) 2007-05-16
EP1784557B1 true EP1784557B1 (fr) 2008-03-19

Family

ID=34926292

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04020155A Withdrawn EP1630356A1 (fr) 2004-08-25 2004-08-25 Injection de fluide dans une turbine lors d'une periode de de refroidissement
EP05777877A Not-in-force EP1784557B1 (fr) 2004-08-25 2005-08-12 Injection de fluide dans une turbine lors d'une période de refroidissement

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04020155A Withdrawn EP1630356A1 (fr) 2004-08-25 2004-08-25 Injection de fluide dans une turbine lors d'une periode de de refroidissement

Country Status (7)

Country Link
US (1) US7752847B2 (fr)
EP (2) EP1630356A1 (fr)
AT (1) ATE389785T1 (fr)
DE (1) DE502005003367D1 (fr)
ES (1) ES2304709T3 (fr)
PT (1) PT1784557E (fr)
WO (1) WO2006021520A1 (fr)

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CH702827A1 (de) * 2010-03-02 2011-09-15 Alstom Technology Ltd Verfahren zum Abkühlen einer Gasturbine.
US8777793B2 (en) 2011-04-27 2014-07-15 United Technologies Corporation Fan drive planetary gear system integrated carrier and torque frame
EP2620604A1 (fr) 2012-01-25 2013-07-31 Siemens Aktiengesellschaft Procédé pour contrôler un processus de refroidissement de composants de turbine
US20130192198A1 (en) 2012-01-31 2013-08-01 Lisa I. Brilliant Compressor flowpath
US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US8863491B2 (en) 2012-01-31 2014-10-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US9038366B2 (en) 2012-01-31 2015-05-26 United Technologies Corporation LPC flowpath shape with gas turbine engine shaft bearing configuration
ITFI20120046A1 (it) * 2012-03-08 2013-09-09 Nuovo Pignone Srl "device and method for gas turbine unlocking"
US10823054B2 (en) * 2012-11-06 2020-11-03 Fuad AL MAHMOOD Reducing the load consumed by gas turbine compressor and maximizing turbine mass flow
WO2015038451A1 (fr) * 2013-09-10 2015-03-19 United Technologies Corporation Injecteur de fluide pour refroidir un composant de moteur à turbine à gaz
EP3023604A1 (fr) 2014-11-18 2016-05-25 Siemens Aktiengesellschaft Procédé et système de refroidissement d'une turbine à gaz
US10082089B2 (en) * 2016-08-25 2018-09-25 General Electric Company Systems and methods to improve shut-down purge flow in a gas turbine system
US10082091B2 (en) * 2016-08-25 2018-09-25 General Electric Company Systems and methods to improve shut-down purge flow in a gas turbine system
US10082087B2 (en) * 2016-08-25 2018-09-25 General Electric Company Systems and methods to improve shut-down purge flow in a gas turbine system
US10082090B2 (en) * 2016-08-25 2018-09-25 General Electric Company Systems and methods to improve shut-down purge flow in a gas turbine system
US10947993B2 (en) 2017-11-27 2021-03-16 General Electric Company Thermal gradient attenuation structure to mitigate rotor bow in turbine engine
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine

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Publication number Priority date Publication date Assignee Title
FR2185753B1 (fr) * 1972-05-26 1976-06-11 Szydlowski Joseph
JPS5477820A (en) * 1977-12-02 1979-06-21 Hitachi Ltd Method of cooling gas turbine blade
US4314442A (en) * 1978-10-26 1982-02-09 Rice Ivan G Steam-cooled blading with steam thermal barrier for reheat gas turbine combined with steam turbine
US4196020A (en) * 1978-11-15 1980-04-01 Avco Corporation Removable wash spray apparatus for gas turbine engine
SE504323C2 (sv) * 1995-06-07 1997-01-13 Gas Turbine Efficiency Ab Förfaringssätt för tvättning av objekt såsom t ex turbinkompressorer
US5867977A (en) * 1996-05-14 1999-02-09 The Dow Chemical Company Method and apparatus for achieving power augmentation in gas turbines via wet compression
DE59808158D1 (de) * 1998-05-28 2003-06-05 Alstom Switzerland Ltd Verfahren zum Betrieb von Gasturbinen und Kombikraftwerken
US6310022B1 (en) * 1999-11-30 2001-10-30 Biogenesis Enterprises, Inc. Chemical cleaning solution for gas turbine blades
US6626637B2 (en) * 2001-08-17 2003-09-30 Alstom (Switzerland) Ltd Cooling method for turbines
US6659715B2 (en) * 2002-01-17 2003-12-09 Siemens Aktiengesellschaft Axial compressor and method of cleaning an axial compressor
EP1418319A1 (fr) * 2002-11-11 2004-05-12 Siemens Aktiengesellschaft Turbine à Gaz
US7065955B2 (en) * 2003-06-18 2006-06-27 General Electric Company Methods and apparatus for injecting cleaning fluids into combustors

Also Published As

Publication number Publication date
EP1630356A1 (fr) 2006-03-01
US20070251210A1 (en) 2007-11-01
US7752847B2 (en) 2010-07-13
ES2304709T3 (es) 2008-10-16
EP1784557A1 (fr) 2007-05-16
DE502005003367D1 (de) 2008-04-30
ATE389785T1 (de) 2008-04-15
WO2006021520A1 (fr) 2006-03-02
PT1784557E (pt) 2008-06-27

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