Design of an optically accessible single cup sector of a full-scale annular gas turbine combustor

Rathod, DD and Kumbhare, S and Chaudhuri, S and Panda, P and Basu, S and Maurya, D (2023) Design of an optically accessible single cup sector of a full-scale annular gas turbine combustor. In: AIAA SciTech Forum and Exposition, 2023, 23 January 2023 through 27 January 2023, Orlando.

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Abstract

This paper summarizes the design and development of a unique optically accessible sector of a full-scale annular gas turbine combustor. The distinctive feature of the experimental setup is that it preserves the geometrical details of an annular combustor that includes the casing, dome and combustor liner. The combustor design features a series of primary and secondary dilution holes with multiple film cooling strips on outer and inner liner. The details of the facility requirements and instrumentation and controls are provided in the paper. The methodology employed in the design of the optically accessible combustion chamber is elucidated, including quartz window considerations and thermal management of the experimental hardware under extremely high heat loads. The goal is to obtain the evolution of global parameters such as spray patternation, pattern factor, pressure drop and combustion efficiency through measurement of the local flow-flame interactions using advanced optical diagnostics. Rig contains multiple ports for measurements of temperature and pressure. For current isothermal study, simultaneous pressure and mass flow rate data of the rig is acquired during PIV measurements to ensure the state of the system. 2D two component PIV experiments are conducted to measure the velocity inside the combustor under isothermal conditions. Experiments are conducted at 0.1, 0.3 and 0.5 kg/s of inlet flow rate and time averaged flow structures inside the combustor are reported. The major structure of flow such as central recirculation zone (CRZ) and swirl jet deflection angle for the respective cases are elucidated here. © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Item Type:	Conference Paper
Publication:	AIAA SciTech Forum and Exposition, 2023
Publisher:	American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information:	The copyright for this article belongs to the publisher.
Keywords:	Film cooling; Flow rate; Gas turbines; Isotherms, Annular combustor; Combustor designs; Combustor liners; Design and Development; Design features; Dilution holes; Dome-liner; Film cooling; Gas turbine combustor; Multiple films, Combustors
Department/Centre:	Division of Interdisciplinary Sciences > Interdisciplinary Centre for Energy Research Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	12 Oct 2024 10:09
Last Modified:	12 Oct 2024 10:09
URI:	http://eprints.iisc.ac.in/id/eprint/86427

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