Investigations of Combustor Inlet Swirl on the Liner Wall Temperature in an Aero Engine Combustor

Abstract

Experimental and numerical investigations are carried out on an annular, straight flow, swirl-stabilized aero engine combustor. In this work, the effect of degree and direction of swirl at the inlet of combustion chamber is examined on the liner wall temperature and hot spots. This is carried out by experimentally measuring the liner outer wall temperature at discrete positions along the circumferential and axial directions of the combustor liner in the engine test facility. The RANS based turbulence modeling with reacting flow approach is used to simulate the flow domain. Conjugate heat transfer analysis is used to estimate the liner wall temperature using Ansys CFX frame work. The degree and direction of swirl at the inlet of combustion chamber is found to alter the velocity and temperature profiles inside the combustor and hence found to have a significant effect on the liner hot spots and its location. Hotspot with 43 % increase in temperature near the secondary zone is observed with the increase in swirl angle from 5° to 15° at the combustor inlet. The location of the hotspot is found to be dependent on the swirl direction.

Coating roughness impact on the combustion chambers life of the turbo engines

“…Different types of combustion chambers have been developed in the past century and different fuels are used there. In aero-engine or gas turbine combustor design, complete combustion, 1-3 low total pressure loss, 4 stability, 5,6 freedom from flash back and flame out, 7,8 relightabality, 9,10 occupying a small space, and no hot spots [11][12][13] are desired, and many researches have been performed on these areas to have better designs.…”

Influence of inlet swirl on pattern factor and pressure loss in an aero engine combustor

“…They concluded that the flow condition from compressors have an obvious influence on the design of combustor and more attention should be focused on this by the designers. Rao et al 4 investigated the effect of compressor exit swirl on the liner wall temperature distribution in an aero engine combustor. They showed the development of hotspots on liner surfaces with the increase in swirl angle at the combustor inlet.…”

“…From the above literature review, it is clear that the compressor exit will always have some swirl [1][2][3][4] which cannot be neglected in analysing an actual combustor performance. The effect of various combustor design parameters such as fuel nozzle spray patterns, dilution hole geometry, fuel type, swirl number and different fuel injection methods on combustor exit pattern factor has been reported by authors.…”

“…Rao et al. 4 investigated the effect of compressor exit swirl on the liner wall temperature distribution in an aero engine combustor. They showed the development of hotspots on liner surfaces with the increase in swirl angle at the combustor inlet.…”