Conceptual Design and Cooling Blade Development of 1700°C Class High-Temperature Gas Turbine
Author:
Ito Shoko1, Saeki Hiroshi1, Inomata Asako1, Ootomo Fumio1, Yamashita Katsuya1, Fukuyama Yoshitaka1, Koda Elichi2, Takehashi Toru2, Sato Mikio2, Koyama Miki3, Ninomiya Toru3
Affiliation:
1. Toshiba Corporation, Yokohama, Japan 2. Central Research Institute of Electric Power Industry, Yokosuka, Japan 3. New Energy and Industrial Technology Development Organization, Tokyo, Japan
Abstract
In this paper we describe the conceptual design and cooling blade development of a 1700°C-class high-temperature gas turbine in the ACRO-GT-2000 (Advanced Carbon Dioxide Recovery System of Closed-Cycle Gas Turbine Aiming 2000 K) project. In the ACRO-GT closed cycle power plant system, the thermal efficiency aimed at is more than 60% of the higher heating value of fuel (HHV). Because of the high thermal efficiency requirement, the 1700°C-class high-temperature gas turbine must be designed with the minimum amount of cooling and seal steam consumption. The hybrid cooling scheme, which is a combination of closed loop internal cooling and film ejection cooling, was chosen from among several cooling schemes. The elemental experiments and numerical studies, such as those on blade surface heat transfer, internal cooling channel heat transfer, and pressure loss and rotor coolant passage distribution flow phenomena, were conducted and the results were applied to the conceptual design advancement. As a result, the cooling steam consumption in the first stage nozzle and blade was reduced by about 40% compared with the previous design that was performed in the WE-NET (World Energy Network) Phase-I.
Publisher
ASME International
Subject
Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering
Reference18 articles.
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