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Ansaldo Energia Gas Turbine Technology Developments

[+] Author Affiliations
A. D. Ramaglia

Ansaldo Energia, Genoa, Italy

U. Ruedel, V. Stefanis, S. Florjancic

Ansaldo Energia Switzerland, Baden, Switzerland

Paper No. GT2018-76665, pp. V003T08A006; 10 pages
doi:10.1115/GT2018-76665
From:
  • ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
  • Volume 3: Coal, Biomass, and Alternative Fuels; Cycle Innovations; Electric Power; Industrial and Cogeneration; Organic Rankine Cycle Power Systems
  • Oslo, Norway, June 11–15, 2018
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5104-3
  • Copyright © 2018 by ASME

abstract

The operating conditions of the gas turbine combined cycle (GTCC) power plants have significantly changed over the last few years and are directed towards an improved operational and fuel flexibility, increased GT power output and efficiency and improved component lifetime. The purpose of this paper is to provide an overview of the development, analysis and validation of modern gas turbine features, parts and components for the AE64.3, AE94.2, AE94.3A, the GT26 and GT36. The development of compressor blades with a low uncertainty using multidisciplinary optimization techniques is outlined while the lifetime of a welded rotor is quantified using a damage-tolerant lifetime assessment method based on experimental creep data. For the lateral dynamics of the shaft train a modal-based approach supported by elastic structures will be described. For the axial flow turbine, the aerodynamic and heat transfer related design and validation of film cooled vanes and blades will be introduced with a particular focus on the tip area, the platforms and the application of under-platform dampers. Furthermore, the impact of the combustor-turbine interface on the turbine vane aerodynamics and film cooling characteristics is shown. For the continued very successful operation of the Constant Pressure Sequential Combustion System (CPSC), the thermos-acoustic activities of can combustors as well as the rig-to-engine transferability are presented. Recent approaches to the development of SLM parts for turbine hardware, specifically the approach used to select process parameters and creation of preliminary material models will also be briefly summarized.

Copyright © 2018 by ASME

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