초록 ▼

A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic tri

A method and device for decoupling combustor attenuation and pressure fluctuation from turbine attenuation and pressure fluctuation in a gas turbine engine. The engine has: a compressor; a combustor; and a turbine, that generate a flow of hot gas from the combustor to the turbine. An aerodynamic trip is disposed in at least one of; a combustor wall; and an inner shroud of the nozzle guide vane ring, and is adapted to emit jets of compressed air from cross flow ports into the flow of hot gas from the combustor. The air jets from the cross flow ports increase turbulence and equalize temperature distribution in addition to decoupling the attenuation and pressure fluctuations between the combustor and the turbine.

대표청구항 ▼

I claim: 1. A method of reducing far field low frequency noise created by a combustor of a gas turbine engine, the engine having, a compressor, the combustor being an annular combustor having an inside wall and an outside wall, and a turbine, the engine having a centreline axis and defining an annu

I claim: 1. A method of reducing far field low frequency noise created by a combustor of a gas turbine engine, the engine having, a compressor, the combustor being an annular combustor having an inside wall and an outside wall, and a turbine, the engine having a centreline axis and defining an annular gas path adapted to guide an annular flow of hot gas from the annular combustor, through a nozzle guide vane ring to the turbine, the method comprising: emitting a plurality of jets of compressed air from an inner shroud of the nozzle guide vane ring downstream of a combustor exit annular flow of hot gas upstream of the turbine in a direction substantially perpendicular to the flow of gas in the gas path and adjacent an exit of the annular combustor to introduce turbulence into the flow substantially downstream of the annular combustor and equalize a temperature distribution of the flow, the turbulence in the hot gas flow resulting in a decoupling between sound attenuation and pressure fluctuation within the turbine and sound attenuation and pressure fluctuations in the combustor. 2. A method according to claim 1 wherein the jets are emitted from a plurality of cross flow ports in communication with the compressor. 3. A method according to claim 1 wherein an outside wall of the nozzle guide vane ring opposing each port is free of cross-flow ports adapted to emit a jet of compressed air into the gas path in a direction substantially perpendicular to the flow of gas in the gas path.