gas turbine engine

Abstract

A gas turbine engine comprising: a compressor section including a compressor mean radius; a combustor section fluidly coupled downstream of the compressor section and including a combustor mean radius; and a turbine section fluid is coupled downstream of the combustor section and includes a turbine midspan radius. The average combustor radius is larger than each of the compressor average radius and the turbine midspan radius.

Description

technical field [0001] This application claims priority to US Serial No. 62 / 675,284, filed on May 23, 2018. [0002] The present disclosure relates generally to turbine engines, and more particularly, to combustor architectures that provide desired downstream conditions. Background technique [0003] Conventional gas turbine engines generally include a compressor for compressing air, which is mixed with fuel and ignited in a combustor to generate a high-pressure, high-temperature gas stream, referred to as combustion gas. The combustion gases flow to the turbine where they expand, converting the thermal energy from the combustion gases into mechanical energy, which is used to drive the shaft to power the compressor and produce output power for powering a generator or for example in aviation Generate thrust in the application. [0004] In at least some known gas turbines, a first set of guide vanes (or diffusers) are coupled between the outlet of the compressor and the inle...

AI Technical Summary

Problems solved by technology

However, the use of the first set of guide vanes and the second set of guide vanes to redirect the flow of air and combustion gases increases the operational inefficiency of the gas turbine

Additionally, the inclusion of additional components such as the first set of guide vanes and the second set of guide vanes typically adds weight, cost and complexity to the gas turbine

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