NDLI: A Reliable Transition Duct With Separation Planes for the Annular Combustor of GT13E2 Gas Turbine

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Tschuor, Remigi Trbojevic, Bogdan Markovic, Alen
Copyright Year	2016
Abstract	Designing a state-of-the-art combustor requires an iterative process where mechanical design solutions in the early concept phase are continuously assessed using analytical cooling and lifetime assessments, which are later backed up with experimental investigations and validation measures. This paper describes the integrated design process in terms of design, cooling, manufacturing, aerodynamic and mechanical integrity for the transition duct of the GT13E2 combustor, which houses the flame development region of the combustor. The objective was to develop a retrofit design with reduced lifecycle costs, with no impact on the combustor-turbine interface and no impact on the overall engine performance. The major challenges were the on-site welding of the two half-shells as well as the increasing demand for cyclic operation of the engine. During the development process, the focus was on selecting reliable and robust cooling schemes on the inner and outer shell to reduce mechanical deflections and thus to reduce the overall stress distribution. Key features of the GT13E2 combustor zone 2 are the following: • Drastically reduced lifecycle cost with no performance penalty (retrofit) • Separation planes at 3 and 9 o’clock position with mechanical locking connections (bridges) and a recess weld with film cooling • Bellmouth shaped inlet of cooling channel with improved impingement and convective cooling • Unique membrane seals with great mechanical flexibility around the turbine inlet outer diameter including mitigation against hot gas ingress (bow wave effect) • Improved cooling during transient conditions to reduce mechanical deflections • Reduced reconditioning effort due to innovative manufacturing methods The cooling schemes were successfully validated against laboratory experiments and integrated into a stable manufacturing process. Increased dimensional stability was achieved through higher rigidity and led to an improved on-site welding process for the separation planes. All the aforementioned features result in a marked improvement of the cyclic lifetime with no performance penalty. This is proven by the fact that the GT13E2 with annular combustor transition duct has now accumulated more than 30,000 operating hours with 1,200 starts.
Sponsorship	International Gas Turbine Institute
File Format	PDF
ISBN	9780791849828
DOI	10.1115/GT2016-57627
Volume Number	Volume 6: Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy
Conference Proceedings	ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition
Language	English
Publisher Date	2016-06-13
Publisher Place	Seoul, South Korea
Access Restriction	Subscribed
Subject Keyword	Life cycle costing Bridges (structures) Stress concentration Membranes Cooling Stability Deflection Welding Ducts Shells Separation (technology) Waves Engines Transients (dynamics) Design Design engineering Flames Gas turbines Stiffness Manufacturing Film cooling Combustion chambers Turbines
Content Type	Text
Resource Type	Article

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