초록 ▼

The present invention provides means for significantly increasing the available power from an aircraft turbine engine, especially a turboprop or turboshaft engine. This is achieved by including a heat exchanger intermediate the compressor and the combuster; to significatnly reduce the temperature of

The present invention provides means for significantly increasing the available power from an aircraft turbine engine, especially a turboprop or turboshaft engine. This is achieved by including a heat exchanger intermediate the compressor and the combuster; to significatnly reduce the temperature of the compressed gases fed to the combustor; the temperature drop ratio across the combustor air precooler must be greater than the pressure drop ratio across the precooler. This provides an increase in density of the air fed to the combustor with a resultant increase in mass flow through the combustor and the turbine, which increases available power, especially at higher altitudes. The aircraft turbine engine comprises a compressor to compress ambient air; a combustor in fluid flow connection with the compressor, for combusting compressed air and fuel; a heat exchanger means in intermediate fluid flow connection between the compressor and the combustor, to cool the compressed air; and a turbine in fluid flow connection with the combustor outlet, designed to be driven by the heated gases from the combustor.

대표청구항 ▼

In a turbine engine designed for use on aircraft, the turbine engine comprising a compressor having an inlet for ambient air and having an outlet for compressed air; a combustor to burn compressed air and fuel and having an air intake in fluid flow connection with the outlet of the compressor and an

In a turbine engine designed for use on aircraft, the turbine engine comprising a compressor having an inlet for ambient air and having an outlet for compressed air; a combustor to burn compressed air and fuel and having an air intake in fluid flow connection with the outlet of the compressor and an exhaust for hot combustion gases, and a turbine in fluid flow connection with the exhaust from the combustor and having mechanical power output means in operative connection with the compressor; the improvement comprising: a combustor air pre-cooler heat exchanger means having a hot compressed air inlet and a cooled compressed air outlet, first fluid flow connection means between the compressor and the compressed air inlet, and second fluid flow connection means between the cooled compressed air outlet and the combustor, the second fluid flow connection means being free of means to increase fluid pressure, the precooler being designed to cool the compressed air from the compressor outlet, such that the temperature of the cooled compressed air entering the combustor is reduced such that the temperature drop ratio between the compressor outlet and the combustor air intake is greater than the pressure drop ratio between those two locations.