Abstract: 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.

Abstract: There is provided for use in a reciprocating engine, a motive flow pump to provide a constant suction pressure in order to draw oil from a breather oil recovery device back to the engine oil reservoir. The motive power for this pump is provided from the flow of oil from a different source.