초록 ▼

An apparatus for supplying high pressure atomizing and purging fluid to the fuel system of a gas turbine engine. The apparatus is comprised of a turbocompressor, multiple flow conduits and associated valves and controls. Alternative versions of the fundamental apparatus may include heat exchangers f

An apparatus for supplying high pressure atomizing and purging fluid to the fuel system of a gas turbine engine. The apparatus is comprised of a turbocompressor, multiple flow conduits and associated valves and controls. Alternative versions of the fundamental apparatus may include heat exchangers for heating and cooling the atomizing and purging fluid within the apparatus. The apparatus works with all types of gas turbine engine cycles well known to one skilled in the art. The apparatus includes a first conduit for extracting a small percentage of the fluid compressed by the turbine engine compressor, and the first conduit is further divided into second and third conduits for supplying portions of the small percentage of compressed fluid to the turbocompressor compressor and turbine. The portion of the fluid flowed to the turbocompressor compressor is compressed and then flowed to the turbine engine fuel system at a location that enhances atomization of the fuel or purges the fuel from the fuel system nozzle after shut-off. The fluid discharged from the turbocompressor turbine is flowed back to the turbine engine to offset engine efficiency losses. The turbocompressor may be configured in any number of mechanical configurations, familiar to one skilled in the art of turbomachinery.

대표청구항 ▼

[ Having described the invention, what is claimed is:] [1.] An apparatus comprising:A) a turbine engine comprising: a first fluid compressor having a first fluid compressor inlet for flowing uncompressed fluid into the compressor, and a first fluid compressor discharge for flowing a first volume of

[ Having described the invention, what is claimed is:] [1.] An apparatus comprising:A) a turbine engine comprising: a first fluid compressor having a first fluid compressor inlet for flowing uncompressed fluid into the compressor, and a first fluid compressor discharge for flowing a first volume of compressed fluid out of the first fluid compressor; a first turbine operably connected to the first fluid compressor to drive the first fluid compressor, said first turbine having a first turbine inlet; the turbine engine further comprising a fuel system; and a first conduit flow connecting the fuel system to the first fluid compressor discharge and to the first turbine inlet, the first conduit having primary and secondary conduit segments, the first conduit adapted to supply a first portion of the volume of compressed fluid to the fuel system through the primary conduit segment;B) a blast air turbocompressor comprising a second fluid compressor driven by a second turbine, the second fluid compressor having a second fluid compressor inlet, and a second fluid compressor discharge for flowing a second volume of compressed fluid out of the second fluid compressor, said first conduit further flow connecting the first fluid compressor discharge and the second fluid compressor inlet by the secondary conduit segment, and wherein a second portion of the first volume of compressed fluid is supplied to the second fluid compressor through the secondary conduit segment; the second turbine comprising a second turbine inlet and a second turbine discharge;C) the apparatus further including a third flow conduit having an inlet end flow connected to the primary conduit segment and a discharge end flow connected to the second turbine inlet; and a fourth conduit having a first end flow connected to the second turbine discharge and a second end located adjacent the fuel system; andD) a second conduit flow connecting the second compressor fluid discharge and the fuel system and whereby the second volume of compressed fluid is supplied to the fuel system.