A test rig for investigations of gas turbine combustor cooling concepts under realistic operating conditions

Abstract

In the current paper, a new test rig for the characterization of advanced combustor cooling concepts for gas turbine combustors is presented. The test rig is designed to allow investigations at elevated pressures and temperatures representing realistic operating conditions of future lean low emission combustors. The features and capabilities of the test rig in comparison to existing rigs are described. The properties of the hot gas flow are measured in order to provide the necessary data for a detailed analysis of the measured cooling effectivity of combustor wall test samples. Results of the characterization of the velocity and temperature distribution in the hot gas flow at the leading edge of the test sample at pressures up to p ¼ 10 bar and global flame temperatures up to T F ¼ 2000 K are presented.

Evaluation of preparation and combustion rig tests of an effusive cooled SiC/SiCN panel

“…The velocity and temperature boundary layer caused by the convectively cooled liner walls was removed by means of a boundary layer bleed immediately upstream of the test sample. A more detailed description of the test rig is given in Ref 27 . The conditions of the hot gas flow, listed in Table 1, are laterally averaged values from detailed measurements reported in Ref 27 .…”

“…27 The conditions of the hot gas flow, listed in Table 1, are laterally averaged values from detailed measurements reported in Ref. 27 The cooling air temperature was measured on the rear of the test sample and was kept constant at T c = 470 K. The relative cooling air pressure drop, defined as the pressure drop of the cooling air across a test sample divided by the hot gas pressure, was varied in the range Δp c = 2.1%-4%. The total cooling effectiveness was measured for this pressure drop range.…”

Influence of blowing ratio on double-wall cooling characteristics under the condition of high-temperature flue gas

“…); the main flow was rectified to obtain a uniform incoming temperature; and the boundary conditions of the experiments were more precise. Because the mainstream air temperature of such trials was lower, and the influence of radiation at lower temperatures was not apparent, more desired cooling results are frequently obtained (Behrendt and Hassa, 2008). In the operational environment of a real combustion engine, however, the temperature and flow fields in the combustion chamber fluctuated with the flame morphology, affecting the temperature distribution on the wall (Ji et al, 2018;Ahmed et al, 2022).…”