A spool (14) for turbo machinery comprises a fluid flow path (16) defined by an axial compressor stage (18) adjacent to a mixed flow compressor stage (20) to thereby provide a compression system which has a relatively high ratio of efficiency to compressor...

The aircraft engine has one-or multi-stage compressor arrangement (V), downstream combustion chamber (BK), one or multi-stage turbine assembly (HT,NT), compressor heat exchanger arrangement (WV), turbine heat exchanger arrangement (WT) and by-pass unit (BY...

A fuel nozzle assembly (34) for use with a turbine engine is described herein. The fuel nozzle assembly includes a plurality of fuel nozzles (38) positioned within an air plenum defined by a casing. Each of the plurality of fuel nozzles is coupled to a com...

Gas turbine (100) comprising a combustion chamber (101) with an exhaust section (102) through which a combustion gas (103) is exhausted, a plenum chamber (104) and a compressor (105) for generating a compressed fluid (106). The plenum chamber (104) is coup...

Methods and devices useable in turbo-engines premixing of compressed air and fuel are provided. A premixer has a mixing part configured to receive a gas flow input in a flow direction and fluid fuel injected substantially perpendicular to the flow directio...

The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages ...