A gas turbine engine (20) includes a propulsor for providing air into a core engine housing and propulsion air radially outwardly of the core engine housing. The core engine housing surrounds a compressor section. A combustor is positioned downstream of th...

A pressure regulating shut-off valve (1) has a valve member (2) regulating flow of fluid between an inlet (4) and an outlet (6). A pneumatic actuator (8) has a piston having first and second faces (14, 18) that define first and second volumes (16, 20) with...

A gas turbine system for part load efficiency improvement and anti-icing within the inlet (16) and at the compressor inlet is described. The system includes a gas turbine (12) having a compressor (13) which receives inlet-air (18). A direct-contact heat ex...

A resistive heating system for a combustion turbine susceptible to inlet air filter house component (42) and compressor icing includes a plurality of heating panels (bundles) (48) arranged in a substantially-planar array (46, 47), adapted to be located on ...

The attachment element has a nacelle (30) and an annular tube element (31) that are connected with each other by a fastening unit, such that relative movement between nacelle and annular tuber element is ensured. Two struts are arranged at specific angle w...

An anti-icing system for a nacelle (50) of an aircraft engine (10). The nacelle (50) has an inlet lip (56) that defines a leading edge of the nacelle (50), and further has an annular-shaped cavity (58) adjacent and delimited in part by an interior surface ...

A gas turbine engine (10) comprising a nacelle (21) having an intake (12), the intake (12) defining a generally annular chamber (35), an engine accessory (33, 34) and a heat exchanger (36) for cooling a fluid of the accessory (33, 34) characterised in that...