Main Article Content
On Rotor-Blade Deterioration and Pressure Losses in a Gas-Turbine Plant
Abstract
Sustenance of rotor-blade design shape is fundamental to the gas-turbine compressor performance. Blade
deterioration causes adverse pressure gradient which imposes unfavourable force on the boundary layer, resulting
in aerodynamic losses. This paper investigates the relationship between rotor-blade deterioration and pressure
losses in a gas-turbine plant. This was achieved by measuring certain performance characteristics of an operational
gas-turbine. Corresponding theoretical predictions were obtained from computer simulations. Rotor-blade
deterioration result in 1.2 percent drop in pressure ratio across the compressor, with a corresponding drop in
isentropic efficiency from 0.83 to 0.72.
deterioration causes adverse pressure gradient which imposes unfavourable force on the boundary layer, resulting
in aerodynamic losses. This paper investigates the relationship between rotor-blade deterioration and pressure
losses in a gas-turbine plant. This was achieved by measuring certain performance characteristics of an operational
gas-turbine. Corresponding theoretical predictions were obtained from computer simulations. Rotor-blade
deterioration result in 1.2 percent drop in pressure ratio across the compressor, with a corresponding drop in
isentropic efficiency from 0.83 to 0.72.
