Combustion and cooling performance in an aero-engine annular combustor

Effect of Inlet Temperature Non-Uniformity on High-Pressure Turbine Performance

“…The generated inlet temperature fields studied by Povey et al (2003) and Povey et al (2007) are quite similar to those found by Li et al (2006), in that the hot streaks are clearly subject to mixing and diffusion, while maintaining their general position near the centre of the flow field as they get convected downstream. These artificially-produced profiles seem to be marginally more coherent and uniform than those produced by an actual combustor, which is likely due to the assumed conditions that have a lower turbulence and a more uniform geometry than those in the actual case.…”

“…As the parts of the fluid stream that have a higher temperature, or hot streaks, flow through the transition duct toward the turbine, they are mixed and diffused until they become somewhat less distinct. Both the numerical and experimental combustor exit profiles published by Li et al (2006) show the existence of distinct hot streaks interacting with the cooler fluid as well as each other. The temperature fields also maintain the radial variation mentioned previously, with the central hot streaks surrounded by cooler regions near the duct boundaries.…”

CFD Study of Cooled Flow in Annular Combustor of Aircraft-Engine

“…Carrotte, etc. [29] shown in Fig.3. For local investigation of a various stages, namely S1 and S2 are located in between the pre-diffuser inlet and exit.…”

“…The entire calculation domain of the combustor contains 3D region from the pre-diffuser inlet to combustor exit, totally having 93 discrete film cooling holes. The simulated inlet and exit pre-diffuser velocities profile was compared with the results of J. F. Carrotte, et al [29] to validate the reliability of commercial CFD cod analysis for predicting the feature of the flow in a gas turbine combustor. Flow characteristics inside combustor show that majority of loss between diffuser exit and entrance of annulus associated with high turbulence in this zone.…”

Numerical investigations of cooling holes system role in the protection of the walls of a gas turbine combustion chamber

“…To our knowledge, the only work which has dealt with both problems simultaneously is that of Li et al [16] who conducted numerical investigations using commercial CFX software to understand the characteristics of the flow, combustion, cooling performance and their interaction in an aero-engine combustor. The entire calculation domain of the combustor consists on a three dimensional region from the pre-diffuser inlet to combustor exit, having 3,500 discrete film cooling holes.…”