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RU2008135804A - Газотурбинная система и способ ее эксплуатации - Google Patents

Газотурбинная система и способ ее эксплуатации Download PDF

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Publication number
RU2008135804A
RU2008135804A RU2008135804/06A RU2008135804A RU2008135804A RU 2008135804 A RU2008135804 A RU 2008135804A RU 2008135804/06 A RU2008135804/06 A RU 2008135804/06A RU 2008135804 A RU2008135804 A RU 2008135804A RU 2008135804 A RU2008135804 A RU 2008135804A
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RU
Russia
Prior art keywords
air
compressor
combustion chamber
turbine
exhaust
Prior art date
Application number
RU2008135804/06A
Other languages
English (en)
Inventor
Джозеф КИРЗНЕР (US)
Джозеф КИРЗНЕР
Original Assignee
Дженерал Электрик Компани (US)
Дженерал Электрик Компани
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 Дженерал Электрик Компани (US), Дженерал Электрик Компани filed Critical Дженерал Электрик Компани (US)
Publication of RU2008135804A publication Critical patent/RU2008135804A/ru

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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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/05—Purpose of the control system to affect the output of the engine
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Turbines (AREA)

Abstract

1. Способ эксплуатации газотурбинной системы (100), имеющей компрессор (110), камеру (120) сгорания и турбину (130), при частичной нагрузке, при котором: ! уменьшают поток топлива в камеру (120) сгорания; ! отводят воздух из компрессора (110) для уменьшения потока воздуха в камеру (120) сгорания; и ! возвращают отведенный воздух в турбину (130) или компонент газотурбинной системы (100), отличный от камеры (120) сгорания. ! 2. Способ по п.1, при котором при отводе воздуха из компрессора (110) отводят воздух из выходного патрубка (175) компрессора (110). ! 3. Способ по п.1, при котором при отводе воздуха из компрессора (110) для уменьшения потока воздуха в камеру (120) сгорания повышают температуру горения в камере (120) сгорания. ! 4. Способ по п.3, при котором при повышении температуры сгорания в камере (120) сгорания поддерживают выхлоп продуктов сгорания из камеры (120) сгорания ниже заданного уровня. ! 5. Способ по п.1, при котором при возврате отведенного воздуха в турбину (130) охлаждают турбину (130). ! 6. Способ по п.1, при котором при возврате отведенного воздуха в компонент газотурбинной системы (100), отличный от камеры сгорания (120), направляют отведенный воздух в теплообменник (180). ! 7. Способ по п.1, при котором при отводе воздуха из компрессора (110) его отводят из одной или нескольких ступеней компрессора и дополнительно направляют один или несколько потоков (160) воздуха, отводимых из ступеней компрессора, в турбину (130) во время работы при частичных нагрузках. ! 8. Способ по п.1, при котором объем отведенного воздуха изменяется при изменении нагрузки на газотурбинную систему (100), температуры выхлопа турбины (130) или температуры внутри турбины (130). ! 9. Газотурбинная система (100), со

Claims (9)

1. Способ эксплуатации газотурбинной системы (100), имеющей компрессор (110), камеру (120) сгорания и турбину (130), при частичной нагрузке, при котором:
уменьшают поток топлива в камеру (120) сгорания;
отводят воздух из компрессора (110) для уменьшения потока воздуха в камеру (120) сгорания; и
возвращают отведенный воздух в турбину (130) или компонент газотурбинной системы (100), отличный от камеры (120) сгорания.
2. Способ по п.1, при котором при отводе воздуха из компрессора (110) отводят воздух из выходного патрубка (175) компрессора (110).
3. Способ по п.1, при котором при отводе воздуха из компрессора (110) для уменьшения потока воздуха в камеру (120) сгорания повышают температуру горения в камере (120) сгорания.
4. Способ по п.3, при котором при повышении температуры сгорания в камере (120) сгорания поддерживают выхлоп продуктов сгорания из камеры (120) сгорания ниже заданного уровня.
5. Способ по п.1, при котором при возврате отведенного воздуха в турбину (130) охлаждают турбину (130).
6. Способ по п.1, при котором при возврате отведенного воздуха в компонент газотурбинной системы (100), отличный от камеры сгорания (120), направляют отведенный воздух в теплообменник (180).
7. Способ по п.1, при котором при отводе воздуха из компрессора (110) его отводят из одной или нескольких ступеней компрессора и дополнительно направляют один или несколько потоков (160) воздуха, отводимых из ступеней компрессора, в турбину (130) во время работы при частичных нагрузках.
8. Способ по п.1, при котором объем отведенного воздуха изменяется при изменении нагрузки на газотурбинную систему (100), температуры выхлопа турбины (130) или температуры внутри турбины (130).
9. Газотурбинная система (100), содержащая:
компрессор (110);
камеру (120) сгорания, сообщающуюся с компрессором (110);
при этом компрессор (110) содержит выпускной клапан (200) компрессора так, что воздух из компрессора (110) может быть отведен во время работы при частичных нагрузках.
RU2008135804/06A 2007-09-04 2008-09-03 Газотурбинная система и способ ее эксплуатации RU2008135804A (ru)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/849,383 US20090056342A1 (en) 2007-09-04 2007-09-04 Methods and Systems for Gas Turbine Part-Load Operating Conditions
US11/849,383 2007-09-04

Publications (1)

Publication Number Publication Date
RU2008135804A true RU2008135804A (ru) 2010-03-10

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
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Country Link
US (1) US20090056342A1 (ru)
JP (1) JP2009062981A (ru)
DE (1) DE102008044476A1 (ru)
FR (1) FR2920477A1 (ru)
RU (1) RU2008135804A (ru)

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DE102008044476A1 (de) 2009-03-05
FR2920477A1 (fr) 2009-03-06
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