Session: 04-21 Combustor Design III
Paper Number: 129071
129071 - Investigating the Influence of Non-Uniform Radial Inlet Distortion on the Performance of Counterflow Model Combustor
In the context of ongoing advancements in gas turbine technology, design capabilities, and numerical simulation techniques, conventional assumptions of non-uiform inflow at the inlet of combustors are no longer tenable. Morden designs necessitate the careful consideration of the distorting effects originating from the upstream compressor exit flow on combustor performance. This paper, building upon experimental validations of numerical model accuracy, employs numerical simulation methodologies to conduct an in-depth analysis of the dynamic characteristics of radial distortion at the inlet of a recirculation model combustor. The study primarily delves into the repercussions of variations in the velocity peak of radial distortion at different positions and distortion levels on various physical parameters within the combustor, encompassing aspects such as air distribution ratio, combustor performance, and flame shape. The research findings emphasize that the position of the velocity peak during radial distortion at the inlet insignificantly influences the combustion efficiency of the combustor. However, this distortion markedly impacts the non-uniformity index of outlet temperature, the localization of hotspots, and the overall total pressure loss coefficient. As the peak of inlet distortion ascends within the combustor, the swirl vortices within the diffusion section shift from the upper side to the lower side, resulting the number of vortices increases. In addition, the total pressure loss generated within the diffusion section gradually increases in tandem with the degree of inlet distortion. Concurrently, changes occur in the depth of penetration of the dilution holes on the lower side of the combustor, leading to shifts in the flame's position. When the distortion position remains constant, an augmentation of inlet non-uniformity only has a minor impact on flame shape and flow field structure, with combustion efficiency consistently exceeding 99%. Nevertheless, this increase in non-uniformity contributes to an elevated total pressure loss (from 3.45% to 3.7%) and an expanded Outlet Temperature Distribution Factor (OTDF) (from 16% to 24%).This study holds significant utility in the development of accurate boundary condition models for the description of inlet effects within numerical simulations of gas turbine combustors.
Presenting Author: Yunjiao Shi Harbin Engineering University
Presenting Author Biography: Yunjiao Shi, female, phD. at the School of Energy and Power Engineering at Harbin
Engineering University.
Authors:
Yunjiao Shi Harbin Engineering UniversityShaowen Luo Harbin Engineering Universit
Ningbo Zhao Harbin Engineering University
Ren Yang Harbin Engineering University
Hongtao Zheng Harbin Engineering University
Investigating the Influence of Non-Uniform Radial Inlet Distortion on the Performance of Counterflow Model Combustor
Paper Type
Technical Paper Publication