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Unsteady Aerodynamics of a High Pressure Compressor Working under Pressure Gain Combustion Disturbances
Citation key 2019_bicalho_igtc
Author Bicalho Civinelli de Almeida, V. and Motta, V. and Peitsch, D.
Pages IGTC2019-0070
Year 2019
Location Tokyo, Japan
Journal IGTC - International Gas Turbine Congress
Month 11
Note Paper WePM14.1,
Technische Universit├Ąt Berlin:
V. Bicalho Civinelli de Almeida, D. Peitsch
GE Renewable Energy:
V. Motta
Editor Gas Turbine Society of Japan
Abstract The current work assesses the unsteady operation of a high pressure compressor (HPC) subject to disturbances stemming from pressure gain combustion processes. Novel fuel-burning technologies in gas turbines (such as pulse or rotating detonation, wave rotor and resonant combustion) introduce periodic disturbances in the already unsteady flow field of the adjacent components, i.e., the compressor upstream and the turbine downstream. This manuscript analyzes numerically how a well-established industrial HPC, namely the NASA EEE engine, responds to periodic variation of boundary conditions matching pressure gain combustion disturbances. Initially, the unsteady operation of a multirow setup is assessed to determine how performance parameters (such as isentropic efficiency, losses and pressure ratio) are affected by the combustion disturbances. Proper orthogonal decomposition (POD) is applied to the unsteady results to better assess the origin and propagation of losses and high entropy regions within the domains. Additionally, the unsteady damping is computed, to evaluate how farther upstream the disturbances effectively propagate. Finally, for further aeroelastic analysis, the forcing spectrum of the aerodynamics loads on the blades is calculated, comparing undisturbed and disturbed operation. The results pinpoint the potentially harmful disturbance ranges from the turbomachinery viewpoint, indicating how much of the promised thermodynamic efficiency improvements of pressure gain combustion might be hindered by component operation losses.
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