Water-Cooled Gas Turbine Nozzle Technology Demonstration at Ultra-High Firing Temperature

Geiling, D.W.; Klompas, N.; Zeman, Klaus

doi:10.1115/83-gt-15

Cited by 3 publications

(2 citation statements)

References 7 publications

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“…As for the moving rotor blades, closed-circuit internal steam cooling was chosen to avoid the expectable problems such as water leakage and difficulty in recovering water through the turbine rotor. The idea of water cooling was tried and tested for both nozzle and rotor blades featuring a composite material construction under high temperature turbine technology (HTTT) program (Geiling, et al, 1983), though water cooled gas turbines have not been in practical use until now. This paper will firstly discuss the studied effect of the cooling system on a plant performance based on the Hz/OZ Fired High Temperature Steam Cycle (HTSC) (Jericha, et al, 1991).…”

Section: Introductionmentioning

confidence: 99%

Conceptual Design of the Cooling System for 1700°C-Class Hydrogen-Fueled Combustion Gas Turbines

Kizuka

Sagae

Anzai

et al. 1998

Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations

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The effects of three types of cooling systems on the calculated operating performances of a hydrogen-fueled thermal power plant with a 1,700°C-class gas turbine were studied with the goal of attaining a thermal efficiency of greater than 60%. The combination of a closed-circuit water cooling system for the nozzle blades and a steam cooling system for the rotor blades was found to be the most efficient, since it eliminated the penalties of a conventional open-circuit cooling system which ejects coolant into the main hot gas stream. Based on the results, the water cooled first-stage nozzle blade and the steam cooled first-stage rotor blade were designed. The former features array of circular cooling holes close to the surface and uses a copper alloy taking advantage of recent coating technologies such as thermal barrier coatings (TBCs) and metal coatings to decrease the temperature and protect the blade core material. The later has cooling by serpentine cooling passages with V-shaped staggered turbulence promoter ribs which intensify the internal cooling.

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Section: Introductionmentioning

confidence: 99%

Conceptual Design of the Cooling System for 1700°C-Class Hydrogen-Fueled Combustion Gas Turbines

Kizuka

Sagae

Anzai

et al. 1998

Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations

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“…A detailed description of the nozzle design and fabrication has been discussed in a previous paper (2). Successful testing in a hot-gas cascade is described in a companion paper (3). This paper describes the post-test metallurgical evaluation of the two nozzle segments tested.…”

Section: Introductionmentioning

confidence: 99%

Post-Test Evaluation of a Prototype Composite Water-Cooled Gas Turbine Nozzle

Muth

Beltran

1983

Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations

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Water-cooled high temperature gas turbine technology has been under investigation by the Gas Turbine Division of the General Electric Company for the past 15 years. The transition from testing small scale laboratory-size hardware to full-scale gas turbine components was initiated in 1975 by General Electric and extended further under the U.S. Department of Energy’s High Temperature Turbine Technology (HTTT) Program. A key element in this transition was the identification of a composite (hybrid) design for the first-stage nozzles. This design permits efficient heat transfer to the water-cooling passage-ways, thus lowering effective strains and increasing part life. The results of GE’s extensive efforts over many years to develop a composite water-cooled first-stage nozzle were further confirmed through the successful fabrication and testing of full-scale hardware under the DOE/HTTT Program. This paper describes the post test metallurgical evaluation of two segments of the nozzle tested under the DOE/HTTT program. A brief description of the actual hot-gas path testing of the part is given. The bulk of the paper deals with a microstructural evaluation of the segments including microprobe traces and hardness surveys. Pre- and post-test non-destructive evaluations are also reviewed.

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Conceptual Design of the Cooling System for 1700°C-Class, Hydrogen-Fueled Combustion Gas Turbines

Kizuka

Sagae

Anzai

et al. 1999

Journal of Engineering for Gas Turbines and Power

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The effects of three types of cooling systems on the calculated operating performances of a hydrogen-fueled thermal power plant with a 1,700°C-class gas turbine were studied with the goal of attaining a thermal efficiency of greater than 60 percent. The combination of a closed-circuit water cooling system for the nozzle blades and a steam cooling system for the rotor blades was found to be the most efficient, since it eliminated the penalties of a conventional open-circuit cooling system which ejects coolant into the main hot gas stream. Based on the results, the water cooled, first-stage nozzle blade and the steam cooled first-stage rotor blade were designed. The former features array of circular cooling holes close to the surface and uses a copper alloy taking advantage of recent coating technologies such as thermal barrier coatings (TBCs) and metal coatings to decrease the temperature and protect the blade core material. The later has cooling by serpentine cooling passages with V-shaped staggered turbulence promoter ribs which intensify the internal cooling.

show abstract

Water-Cooled Gas Turbine Nozzle Technology Demonstration at Ultra-High Firing Temperature

Cited by 3 publications

References 7 publications

Conceptual Design of the Cooling System for 1700°C-Class Hydrogen-Fueled Combustion Gas Turbines

Conceptual Design of the Cooling System for 1700°C-Class Hydrogen-Fueled Combustion Gas Turbines

Post-Test Evaluation of a Prototype Composite Water-Cooled Gas Turbine Nozzle

Conceptual Design of the Cooling System for 1700°C-Class, Hydrogen-Fueled Combustion Gas Turbines

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