Abstract: Air flow delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by directing a portion of a compressed air formed by the compressor section and located in a first fluid flow path to a second fluid flow path including a heat exchanger positioned operatively within the second flow path. The second fluid flow path results in a flow of cooled cooling air to be directed to the components of the gas turbine engine to be cooled. Thus, the components of the gas turbine engine are more efficiently cooled with a smaller quantity of air drawn from the compressor section generated air than if compressor generated air was used for cooling components of the gas turbine engine. Furthermore, more compressor generated air remains for combustion within the combustor section of the gas turbine engine.

Abstract: The present invention is an improvement in radial diffusers employed in a turbine engine having a centrifugal compressor. The walls of the diffuser define at least one flow passage through the diffuser having a first portion with a first cross-sectional area and a second portion having a larger, second cross-sectional area. The first wall section is spaced apart from the second wall section so as to define a bleed aperture therebetween. A vortex fence extends outwardly from the wall surface at the leading edge of the second wall portion. Preferably, the bleed aperture and the vortex fence are disposed on the suction surface of each vane in a vaned radial diffuser.