Parametric analysis of effect of blade cooling means on gas turbine based cogeneration cycle

2008 ◽  
Vol 81 (4) ◽  
pp. 197-204 ◽  
Author(s):  
◽  
O. Singh ◽  
B. N. Prasad
Keyword(s):  
Gas Turbine ◽  
Parametric Analysis ◽  
Blade Cooling ◽  
Cogeneration Cycle

scholarly journals Performance of the Integrated Gas and Steam Cycle (IGSC) for Reheat Gas Turbines

1987 ◽  
Author(s):  
Kazuo Takeya ◽  
Hajime Yasui
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Ceramic Coating ◽  
Research Association ◽  
Performance Tests ◽  
Gas Temperature ◽  
Power Station ◽  
Engineering Research ◽  
Blade Cooling ◽  
Advanced Technologies

In 1978, the Japanese government started a national project for energy conservation called the Moonlight Project. The Engineering Research Association for Advanced Gas Turbines was selected to research and develop an advanced gas turbine for this project. The development stages were planned as follows: First, the development of a reheat gas turbine for a pilot plant (AGTJ-100A), and second, a prototype plant (AGTJ-100B). The AGTJ-100A has been undergoing performance tests since 1984 at the Sodegaura Power Station of the Tokyo Electric Power Co., Inc. (TEPCO). The inlet gas temperature of the high pressure turbine (HPT) of the AGTJ-100A is 1573K, while that of the AGTJ-100B is 100K higher. Therefore, various advanced technologies have to be applied to the AGTJ-100B HPT. Ceramic coating on the HPT blades is the most desirable of these technologies. In this paper, the present situation of development, as well as future R & D plans for ceramic coating, is taken into consideration. Steam blade cooling is applied for the IGSC.

scholarly journals A Method for Determining the Main Requirements of Outlet Gas Temperature Profile of Marine Gas Turbine Combustors

1982 ◽  
Author(s):  
Tang Chian-ti
Keyword(s):  
Temperature Distribution ◽  
Temperature Profile ◽  
Gas Turbine ◽  
Guide Vane ◽  
Safety Margin ◽  
Gas Temperature ◽  
Distribution Factor ◽  
Radial Temperature ◽  
Blade Height ◽  
Blade Cooling

Taking account of the marine gas turbine operation features, the author has chosen the hot corrosion peak temperature of materials as the guide vane material limiting temperature while evaluating the overall temperature distribution factor. Along with the blade cooling effectiveness a safety margin factor has been introduced during its evaluation. The gas temperature distribution along blade height is assumed to satisfy the condition that approximately equal safety factor in respect of strength prevails along blade height. Once the gas radial temperature profile becomes known, the radial temperature distribution factor can be readily determined.

Performance Study of a 1 MW Gas Turbine Using Variable Geometry Compressor and Turbine Blade Cooling

2010 ◽  
Author(s):  
Cleverson Bringhenti ◽  
Jesuino Takachi Tomita ◽  
Joa˜o Roberto Barbosa
Keyword(s):  
Gas Turbine ◽  
Guide Vane ◽  
Turbine Blades ◽  
Axial Flow ◽  
Operating Conditions ◽  
Inlet Guide Vane ◽  
Variable Geometry ◽  
Performance Study ◽  
Turbine Blade Cooling ◽  
Blade Cooling

This work presents the performance study of a 1 MW gas turbine including the effects of blade cooling and compressor variable geometry. The axial flow compressor, with Variable Inlet Guide Vane (VIGV), was designed for this application and its performance maps synthesized using own high technological contents computer programs. The performance study was performed using a specially developed computer program, which is able to numerically simulate gas turbine engines performance with high confidence, in all possible operating conditions. The effects of turbine blades cooling were calculated for different turbine inlet temperatures (TIT) and the influence of the amount of compressor-bled cooling air was studied, aiming at efficiency maximization, for a specified blade life and cooling technology. Details of compressor maps generation, cycle analysis and blade cooling are discussed.

Influence of converging conical hole angles on jet impingement blade cooling of gas turbine blade leading edge

2022 ◽  
Author(s):  
S. Sathish ◽  
S. Seralathan ◽  
Mohan Sai Narayan Ch ◽  
V. Mohammed Rizwan ◽  
U. Prudhvi Varma ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Leading Edge ◽  
Jet Impingement ◽  
Gas Turbine Blade ◽  
Blade Cooling ◽  
Blade Leading Edge

scholarly journals The 701F Gas Turbine Design Process: Upgrade and Innovations

1999 ◽  
Author(s):  
B. Facchini ◽  
C. Carcasci ◽  
G. Ferrara ◽  
L. Innocenti ◽  
D. Coutandin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Design Process ◽  
Cooling System ◽  
Design Procedure ◽  
Operating Conditions ◽  
Pollutant Emission ◽  
Inlet Section ◽  
Blade Cooling ◽  
Cooling Design ◽  
Power Capability

In this paper, a Fiat Avio 701F gas turbine re-design process is presented. This already tested gas turbine has been modified, for a particular re-powering application: a reduction in the net power production is required, whereas efficiency and exhaust temperature have been improved by mean of increased hot gas temperature at the first nozzle inlet section. Consequently this re-powering solution clearly requires consistent re-design efforts to satisfy specific plant operating conditions. The gas turbine power output has been tuned to the required value by reducing the air inlet mass flowrate; the combustion chamber setting has been modified with particular attention to the control of pollutant emission level. The increase of inlet stator turbine temperature necessitated a complete review of the three cooled turbine stages. The aim of greater overall efficiency with inlet and exit turbine temperature increase also involved the introduction of a new blade material. For design tool flexibility the blade cooling design procedure has been improved making better optimization of the cooling system possible. In this paper a detailed description of the several gas turbine modifications with particular attention to the blade cooling design procedure and to the corresponding simulation results is reported. The modifications developed could also be introduced on the new version of the 701F, at full power capability, in order to get better efficiency and power.

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