A gas turbine engine includes a compressor, an annular casing (44) surrounding the compressor, and a bleed flow adapter (56) mounted to an exterior side of the annular casing (44). The annular casing (44) includes an interior side that surrounds a compress...

A heating system for heating a component (48a) in a liquid distribution system (20) of an aircraft engine. The liquid distribution system (20) feeds a liquid to the component (48a). The heating system includes an acoustic generator (30) disposed in communi...

An aircraft engine (10), has: an inlet (12) extending circumferentially around a central axis (A); an annular inlet duct (22) having a duct inlet (22A) fluidly connected to an environment outside of the aircraft engine (10) and a duct outlet (220) fluidly ...

Gas turbines are one of leading sources for power generation with lower greenhouse gas emissions. However, due to environmental concerns, gas turbines are moving towards adopting greener fuels. The shift towards greener fuels comes with own set of challeng...

The turbine has an air intake (14), and a compressor (1) comprising a compressor flow channel (4). The compressor has a pre-conducting blade row (3) with pre-conducting blades. A freezing-up sensor unit (17) has a sensor e.g. temperature sensor (8) and pre...

A turbomachine (2) includes a fan (22) having a housing (23) and a plurality of vanes (42) rotatable within the housing (23). Each of the plurality of vanes (42) includes a pressure side (110) and a suction side (112). A pressure sensing system (100) inclu...

A system for reducing moisture in a burner pressure sensing line in a gas turbine engine. A water trap, 15, is mounted on the burner pressure sensing line with an inlet for receiving burner pressure air and an outlet, 37, for transferring burner pressure a...

A system includes a detector (36) configured to detect a fog condition within an air flow directed toward a compressor (22). The system also includes a controller (42) coupled to the detector, wherein the controller is configured to activate a first contro...

Certain embodiments of the invention may include systems (100) and methods (200) for compensating fuel composition variations in a gas turbine (108). According to an example embodiment of the invention, a method (200) is provided for compensating for fuel ...

A water-injection control system (42) is disclosed for a water supersaturation system (26) installed in a gas turbine air intake system (24) for augmenting gas turbine (10) power output during operation at high ambient-air temperature, while maintaining th...