Combined convection/effusion cooled one-piece can combustor

Abstract

The invention relates to a combined convection / effusion cooled one-piece can combustor. An industrial turbine engine comprises a combustion section, an air discharge section downstream of the combustion section, a transition region between the combustion and air discharge section, a combustion transition piece (120) and a sleeve (129). The transition piece (120) defines an interior space (304) for combusted gas flow. The sleeve (129) surrounds the combustor transition piece (120) so as to form a flow annulus (124) between the sleeve (129) and the transition piece (120). The sleeve (129) includes a first set of apertures (400) for directing cooling air (I) from compressor discharge air into the flow annulus (124). The transition piece (120) includes an outer surface (300a) bounding the flow annulus (124) and an inner surface (300b) bounding the interior surface (304), and includes a second set of apertures (200) for directing cooling air in the flow annulus (124) to the interior space (304). Each of the second set of apertures (200) extends from an entry portion (200a) on the outer surface (300a) to an exit portion (200b) on the inner surface (300b).

Description

technical field [0001] The present invention relates generally to means for cooling gas turbine components, and more particularly to cooling a one-piece can combustor by a combination of convective cooling and effusion cooling. Background technique [0002] Gas turbines can operate with higher efficiency if the turbine inlet temperature can be raised to a maximum. However, the combustion gases originate in the combustion chamber before entering the turbine inlet, and the combustion chamber reaches operating temperatures well above 1500°F, and even the most advanced alloys cannot withstand prolonged use at these temperatures. Thus, the performance and life of the turbine is greatly dependent on the degree of cooling available to the turbine components exposed to extreme thermal conditions. [0003] The general concept of using compressor discharge air to cool turbine components is known in the art. However, developments and changes in turbine design have not necessarily bee...

AI Technical Summary

Problems solved by technology

However, the combustion gases originate in the combustion chamber before entering the turbine inlet, and the combustion chamber reaches operating temperatures well above 1500°F, and even the most advanced alloys cannot withstand prolonged use at these temperatures

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