Aircraft power system
AssigneeROLLS-ROYCE plc
InventorsMichael Abraham KARAM, Craig HEATHCO, Andrew EIFERT
Life of this patent
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Abstract
A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.
Claims20
An apparatus comprising:
- a gas turbine engine having a core flow path and a bypass duct structured to bypass a working flow around a combustor of the gas turbine engine;
- and
- a moveable component associated with the bypass duct and structured to change a flow area by moving between a first position and a second position, the moveable component actuated to the second position such that a geometry of the duct forms a resonance space tuned to attenuate a noise.
An apparatus comprising:
- an aircraft adaptive cycle powerplant having a duct operable to selectively admit a working fluid to adapt the powerplant to operate at different flight conditions, the duct reconfigurable to provide a resonance chamber structured to emit a noise when working fluid is discouraged from flowing through the duct.
A method comprising:
- flowing a working fluid through a bypass passage of a gas turbine engine;
- moving a component to discourage a flow of working fluid through an offtake passage of the gas turbine engine;
- forming a noise producing space that includes the offtake passage;
- and
- producing a targeted resonance as a result of the forming.
Dependencies are inferred from the claim text.