A system 10 for heating fuel in a combined cycle gas turbine 12 includes a fuel heat exchanger 50 downstream from a turbine outlet 36, and the fuel heat exchanger 50 has an exhaust gas inlet 52, an exhaust gas outlet 54, a fuel inlet 56, and a fuel outlet ...

A system (1) for recovering heat from a gas turbine (10) is presented. The system includes the gas turbine (10) including at least one compressor (3) and an expansion turbine (2), the expansion turbine (2) located downstream of the compressor (3), a combus...

A ventilation inlet comprising a ventilation pipe to receive flow from a first flow zone and to deliver the flow to a second flow zone; a divider arranged to divide a portion of the ventilation pipe into a static pressure zone and a total pressure zone; an...

A gas turbine engine assembly (10) is provided for use with an aircraft. The gas turbine engine assembly comprises a propelling gas turbine engine and an auxiliary power unit (12). The propelling gas turbine engine includes a fan (14) and a core engine (11...

A gas turbine system that includes a compressor (12), a turbine component (14) and a load (16), wherein fuel and compressor discharge bleed air are supplied to a combustor (20) and gaseous products of combustion are introduced into the turbine component (1...