WO1991015667A1 - Procede et ensemble d'augmentation de la puissance de turbines a gaz - Google Patents

Procede et ensemble d'augmentation de la puissance de turbines a gaz Download PDF

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Publication number
WO1991015667A1
WO1991015667A1 PCT/AT1991/000050 AT9100050W WO9115667A1 WO 1991015667 A1 WO1991015667 A1 WO 1991015667A1 AT 9100050 W AT9100050 W AT 9100050W WO 9115667 A1 WO9115667 A1 WO 9115667A1
Authority
WO
WIPO (PCT)
Prior art keywords
air
cooler
bar
gas turbine
cooled
Prior art date
Application number
PCT/AT1991/000050
Other languages
German (de)
English (en)
Inventor
Herbert Jericha
Ferdinand HÖLLER
Original Assignee
Elin Energieversorgung Gesellschaft M.B.H.
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 Elin Energieversorgung Gesellschaft M.B.H. filed Critical Elin Energieversorgung Gesellschaft M.B.H.
Publication of WO1991015667A1 publication Critical patent/WO1991015667A1/fr

Links

Classifications

    • 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
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants

Definitions

  • the invention relates to a method for increasing the performance of a gas turbine, preferably in hot, in particular in tropical areas, and an aggregate for performing the method.
  • a gas turbine in its simplest form is an aggregate that consists of a compressor, combustion chamber and the actual turbine.
  • the compressor draws air from the environment and pushes it into the combustion chamber.
  • Gaseous or liquid fuel is burned in the combustion chamber so that hot propellant gases are produced.
  • These hot gases are expanded in the turbine, which both drives the compressor and delivers power.
  • the power generation of gas turbines is therefore based on the principle that less work is required to compress a certain amount of cool combustion air than work is done when the corresponding amount of hot gas is expanded.
  • the object of the invention is therefore to increase the efficiency of gas turbines when they are used in locations with high ambient temperatures.
  • the object is achieved by the invention.
  • This is characterized in that an outside air drawn in with 1 bar, based on sea level and about 30 ° C, preferably 40 ° C, is compressed to about 1.9 bar, that it heats up to about 100 ° C by compression Air is cooled to just above the ambient temperature, preferably about 50 ° C., then this air is released to about 1.04 bar with power recovery and thereby cooled to about 5 ° C., and that this air is fed to a gas turbine as intake air .
  • the invention succeeds in reducing the air humidity before the air enters the gas tube, which leads to a reduction in the compression work to be done. In this way it is possible to significantly increase the efficiency of a gas turbine. Due to the condensation removal, more oxygen gets into the compressor and subsequently into the combustion chamber, which leads to a further increase in performance.
  • an aggregate which consists of an air compressor with two rows of rotor blades rotating in opposite directions with a leading and a secondary guide wheel, a cooler being connected to this air compressor and an air expansion turbine connected downstream of this cooler.
  • this unit ensures that the high increase in performance according to the invention is achieved.
  • the better use of primary energy with the aggregate also makes a valuable contribution against the greenhouse effect and thus for environmental protection.
  • an assembly which consists of an air compressor with two There are rotating rows of blades with leading and trailing impeller, with a cooler downstream of this air compressor and an air expansion turbine downstream of this cooler.
  • An embodiment of the invention provides that the air compressor is driven by an electric motor.
  • the cooler can be operated with feed water.
  • the cooler can be cooled with ambient air.
  • This variant is to be used advantageously if difficulties should arise due to local conditions in the procurement of cooling water.
  • FIG. 1 shows the cross section of a schematic overall arrangement of the unit according to the invention.
  • Air is sucked in via an air intake duct 1, as indicated by an arrow 13, compressed in an air compressor 10 and, as indicated by an arrow 14, via a discharge duct 9 to a cooler and an air expansion turbine connected downstream of the cooler.
  • a cooled air flow re-enters the unit in the direction indicated by an arrow 15 through a supply duct 11 and is fed in the conditioned state in the direction indicated by an arrow 16 through a supply duct 12 to a gas turbine as combustion air.
  • the ** 3 cooling unit consists of an electric motor 6 and two rotating rows of blades 2, 3 with a stator 4 and a stator 5.
  • the compressed air is preferably cooled in feed water or in ambient air. Before this, the air is compressed to a pressure of 1.9 bar; in the cooler, the air is cooled to 50 ° C and then fed to the air expansion turbine. In the air relaxation turbine, the expansion follows a pressure of 1.04 bar and a change to the temperature desired for entry into the gas turbine. To combat nitrogen oxides, more steam can be introduced into the combustion chamber, which results in a further increase in performance.
  • the electric motor 6 drives the rotor blade row 2 via a motor shaft 7.
  • a connecting shaft 8 connects the rotor blade row 3 to a turbine impeller 17; this connecting shaft 8 rotates at the same speed as the electric motor 6, depending on the design of the unit, in the opposite or the same direction as its motor shaft 7.
  • the air ducts of the unit can be welded from sheet metal, since they only have to withstand a pressure of a maximum of 1.9 bar.

Abstract

Un procédé et un ensemble permettent d'augmenter la puissance d'une turbine à gaz dans des régions géographiques à température ambiante élevée. L'air ambiant aspiré à 1 bar et à environ 40 °C est comprimé à environ 1,9 bar et refroidi jusqu'à une température légèrement supérieure à la température ambiante. Puis l'air est détendu jusqu'à 1,04 bar environ, avec récupération de la puissance, se refroidissant ainsi jusqu'à 5 °C, et est fourni à une turbine à gaz en tant qu'air d'aspiration. L'humidité de l'air est ainsi réduite avant son entrée dans la turbine à gaz, ce qui diminue l'effort de compression nécessaire et entraîne une augmentation considérable du rendement.
PCT/AT1991/000050 1990-04-03 1991-04-03 Procede et ensemble d'augmentation de la puissance de turbines a gaz WO1991015667A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ATA774/90 1990-04-03
AT77490 1990-04-03

Publications (1)

Publication Number Publication Date
WO1991015667A1 true WO1991015667A1 (fr) 1991-10-17

Family

ID=3499403

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/AT1991/000050 WO1991015667A1 (fr) 1990-04-03 1991-04-03 Procede et ensemble d'augmentation de la puissance de turbines a gaz

Country Status (1)

Country Link
WO (1) WO1991015667A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0622535A1 (fr) * 1993-04-27 1994-11-02 Air Products And Chemicals, Inc. Utilisation de nitrogène d'une installation de séparation d'air pour le refroidissement de l'air fourni au compresseur d'une turbine à gaz pour augmenter le rendement
EP0626510A1 (fr) * 1993-05-28 1994-11-30 Praxair Technology, Inc. Combinaison d'une turbine à gaz avec une installation de séparation d'air
GB2280224A (en) * 1993-07-22 1995-01-25 Ormat Ind Ltd Method of and apparatus for augmenting power produced from gas turbines
US5622044A (en) * 1992-11-09 1997-04-22 Ormat Industries Ltd. Apparatus for augmenting power produced from gas turbines
EP0770771A1 (fr) * 1995-10-26 1997-05-02 Asea Brown Boveri Ag Compresseur avec refroidissement intermédiaire

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1339734A (fr) * 1962-10-25 1963-10-11 Turbine à gaz à performances indépendantes de la température ambiante
DE2102279A1 (de) * 1970-05-08 1971-11-18 Bergmann Borsig Veb Verfahren und Einrichtung zum Betrieb eines Verdichters, insbesondere für Gasturbinenanlagen
WO1988000282A1 (fr) * 1986-07-09 1988-01-14 Engine Technology Limited Dispositif de refroidissement d'air dans un moteur a combustion interne suralimente
EP0378003B1 (fr) * 1989-01-11 1993-06-16 STEWART & STEVENSON SERVICES, INC. Dispositif et méthode pour optimiser la température de l'air d'admission de turbine à gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1339734A (fr) * 1962-10-25 1963-10-11 Turbine à gaz à performances indépendantes de la température ambiante
DE2102279A1 (de) * 1970-05-08 1971-11-18 Bergmann Borsig Veb Verfahren und Einrichtung zum Betrieb eines Verdichters, insbesondere für Gasturbinenanlagen
WO1988000282A1 (fr) * 1986-07-09 1988-01-14 Engine Technology Limited Dispositif de refroidissement d'air dans un moteur a combustion interne suralimente
EP0378003B1 (fr) * 1989-01-11 1993-06-16 STEWART & STEVENSON SERVICES, INC. Dispositif et méthode pour optimiser la température de l'air d'admission de turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5622044A (en) * 1992-11-09 1997-04-22 Ormat Industries Ltd. Apparatus for augmenting power produced from gas turbines
EP0622535A1 (fr) * 1993-04-27 1994-11-02 Air Products And Chemicals, Inc. Utilisation de nitrogène d'une installation de séparation d'air pour le refroidissement de l'air fourni au compresseur d'une turbine à gaz pour augmenter le rendement
EP0626510A1 (fr) * 1993-05-28 1994-11-30 Praxair Technology, Inc. Combinaison d'une turbine à gaz avec une installation de séparation d'air
GB2280224A (en) * 1993-07-22 1995-01-25 Ormat Ind Ltd Method of and apparatus for augmenting power produced from gas turbines
EP0770771A1 (fr) * 1995-10-26 1997-05-02 Asea Brown Boveri Ag Compresseur avec refroidissement intermédiaire

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