A review of jet-impingement heat transfer in gas turbine systems is presented. Characteristics of the different flow regions for submerged jets--free jet, stagnation flow, and wall jet--are reviewed. Heat transfer characteristics of both single and multiple jets are discussed with consideration of the effects of important parameters relevant to gas turbine systems including curvature of surfaces, crossflow, angle of impact, and rotation.

Jet-impingement heat transfer in gas turbine systems.

Heat transfer characteristics in steam-cooled rectangular channels with two opposite rib-roughened walls

Heat transfer analysis for a multistage gas turbine using different blade-cooling schemes

Comparative performance of combined gas turbine systems under three different blade cooling schemes

A constrained optimization of locations and discrete radii of a large number of small circular cross-section straight-through coolant flow passages in internally cooled gas turbine vane was developed. The objective of the optimization was minimization of the integrated surface heat flux penetrating the airfoil thus indirectly minimizing the amount of coolant needed for the removal of this heat. Constraints were that the maximum temperature of any point in the vane is less than the maximum specified value and that the distances between any two holes or between any hole and the airfoil surface are greater than the minimum specified value. A configuration with maximum of 30 passages was considered. The presence of external hot gas and internal coolant was approximated by using convection boundary conditions for the heat conduction analysis. A parallel three-dimensional thermoelasticity finite element analysis (FEA) code from the ADVENTURE project at University of Tokyo was used to perform automatic thermal analysis of different vane configurations. A robust semi-stochastic constrained optimizer and a parallel genetic algorithm (PGA) were used to solve this problem using an inexpensive distributed memory parallel computer. 1 Research scientist. ASME member.

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Optimization of a Large Number of Coolant Passages Located Close to the Surface of a Turbine Blade

It is very essential to raise the thermal efficiency of combined cycle plants from the viewpoint of energy saving and environmental protection. Tohoku Electric Power Co., Inc., and Toshiba Corporation in Japan have jointly studied the next generation of combined cycle systems using 1500°C class gas turbine. A promising cooling technology for the vanes using steam was developed. The blades are cooled by air, adopting the impingement cooling, film cooling, and so on. The cooling effectiveness was confirmed both for the vanes and the blades using a hot wind tunnel. This paper describes the design features of the vanes and the blades, and the results of the verification tests using the hot wind tunnel.

The Advanced Cooling Technology for the 1500°C Class Gas Turbines: Steam-Cooled Vanes and Air-Cooled Blades

There is a strong demand for efficient and clean power-generating systems to meet recent energy-saving requirements and environmental regulations. A combined cycle power plant is one of the best solutions to the above. Tohoku Electric Power Co., Inc., and Mitsubishi Heavy Industries, ltd., have jointly developed three key technologies for a next-generation 1,500 C class gas turbine. The three key technologies consist of: (1) high-temperature low-NO{sub x} combustion system, (2) row 1 turbine vane and blade with advanced cooling schemes, and (3) advanced heat-resistant materials; (2) and (3) were verified by HTDU (High Temperature Demonstration Unit). This paper describes the results of the above-mentioned six-year joint development.

Final Report of the Key Technology Development Program for a Next-Generation High-Temperature Gas Turbine

There is a strong demand for efficient and clean power generating systems to meet recent energy saving requirements and environmental regulations. A combined cycle power plant is one of the best solutions to the above.Tohoku Electric Power Co., Inc. and Mitsubishi Heavy Industries, Ltd. have jointly developed three key technologies for a next generation 1,500°C class gas turbine. The three key technologies consist of (1) high temperature low NOx combustion system, (2) row I turbine vane and blade with advanced cooling schemes, and (3) advanced heat resistant materials, verified by HTDU (High Temperature Demonstration Unit).This paper describes the results of the above mentioned 6 year joint development.Copyright © 1995 by ASME

Final Report of the Key Technology Development Program for a Next Generation High Temperature Gas Turbine

Tohoku Electric Power Co., Inc. and Mitsubishi Heavy Industries, Ltd. have begun a joint development program on key technologies for a next generation gas turbine which aims for a combined cycle efficiency over 55%. Under the program, advanced cooling technologies, better heat resistant materials and thy low NOx (DLN) combustion technologies are being developed. For verifying high temperature technologies, turbine testing is going to be performed using the HTDU (High Temperature Demonstration Unit) at Takasago Machinery Works, Mitsubishi Heavy Industries, Ltd.This paper describes the general description of the HTDU facility and plans for testing a turbine at a firing temperature of 1500°C.© 1994 ASME

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High Temperature Demonstration Unit for a 1500°C Class Gas Turbine

There is a strong demand for efficient and clean power generation systems which can cope with the energy shortage and the global environmental problems.As one of the measures to meet this demand, Tohoku Electric Power Company, in cooperation with the three domestic gas turbine manufacturers, has been developing since 1989 the key technologies for the next generation high efficiency gas turbine of a 1,500°C class of firing temperature.The aim is to achieve over 55% (LHV) thermal efficiency in a LNG comhined cycle power plant.In this research, Tohoku Electric Power Company have developed: (1) advanced cooling schemes for 1st stage vanes and blades, (2) heat resistant materials for 1st stage vanes and blades and (3) high temperature low NOx combustor, which are the key technologies required for realizing a 1,500 °C class high efficiency gas turbine with a potential for practical use.Copyright © 1996 by ASME

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M. Sato

Papers

The Advanced Cooling Technology for the 1500°C Class Gas Turbines: Steam-Cooled Vanes and Air-Cooled Blades

Final Report of the Key Technology Development Program for a Next-Generation High-Temperature Gas Turbine

Final Report of the Key Technology Development Program for a Next Generation High Temperature Gas Turbine

High Temperature Demonstration Unit for a 1500°C Class Gas Turbine

Development of Advanced Gas Turbine