Jet noise is reduced by weakening Mach cones (16) in a jet exhaust gas streamtube (14) by modifying exhaust gas flow in a longitudinal axial core (13) of the exhaust gas streamtube (14). This may be achieved by deploying a transpiration element (24), such ...

The cone part has a partition wall (3) positioned between an outside cone part (1) and an inside cone part (2) for connecting the inside cone part to the outside cone part in a spaced apart manner to form an interspace between the outside cone part and the...

A method for operating a gas turbine engine (10) includes channeling compressed air from the gas turbine engine to a noise suppression system (50), and selectively operating the noise suppression system such that air discharged from the noise suppression s...

The device (12) has a set of grooves that is provided in the extension of an end of a tailpipe (10) of a turbomachine. A set of indentations is provided between two successive grooves. The set of grooves and indentations are unsymmetrical with respect to a...

A system for jet engine noise control of a jet engine having a main jet (32) stream exiting an exhaust nozzle (44) and flowing along a jet axis (30) includes a thermal acoustic shield (42) directed at a non-zero angle relative to the jet axis (30). The the...

The turbojet engine (1) has a double-tube structure with an inner flow channel (14) and an outer flow channel (12) shrouding it. The main flow (11) is passed into the outer channel (12) with an auxiliary flow (13) into the inner channel (14). The inner cha...

The method enables a gas turbine engine (10) to be operated. The method comprises channeling exhaust gases from a core engine (13) through an exhaust assembly (40) and past at least one flow boundary surface (104), and selectively operating a noise suppres...

A method and a system (10) for exhausting gas via a nozzle (19, 21) of a gas turbine engine, for example. The system (10) comprises a nozzle (19, 21) comprising a nozzle body portion (32, 33, 74) defining a nozzle exit (42, 43), characterised in that the n...

A by-pass gas turbine engine including a primary and a secondary nozzle which are substantially convergent, wherein the primary nozzle is situated radially within, but axially protruding from, the secondary nozzle characterised in that the primary and seco...