Acoustic liner with varied properties
AssigneeUnited Technologies Corporation
InventorsJonathan Gilson, Constantine Baltas
Life of this patent
Estimating the term…
Abstract
A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.
Claims36
A geared turbofan engine, comprising:
- a first rotor;
- a fan connected to the first rotor, wherein the fan is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60;
- a second rotor;
- a gear train that connects the first rotor to the second rotor;
- a fan casing and a nacelle arranged circumferentially about a centerline and defining a bypass flow duct in which the fan is disposed;
- and
- a plurality of discrete acoustic liner segments having varied geometric properties disposed along the bypass flow duct;
- wherein the plurality of discrete acoustic liner segments comprises a first acoustic liner segment, and a second acoustic liner segment spaced apart from the first acoustic liner segment;
- wherein each the first and second acoustic liner segments includes a cellular core structure, the cellular core structure comprising one or more resonator chambers having a width;
- and
- wherein the width of the one or more resonator chambers of the first acoustic liners differs from the width of the one or more resonator chambers of the second acoustic liner.
A geared turbofan engine, comprising:
- a gear train connecting a first rotor to a second rotor;
- a core casing extending circumferentially around the first rotor and defining a portion of an inner surface of a bypass flow duct;
- a nacelle and a fan casing extending circumferentially around the core casing and defining an outer surface of the bypass flow duct;
- and
- an acoustic liner with two or more zones disposed along the bypass flow duct, the two or more zones being tuned to attenuate a different frequency range of acoustic noise;
- wherein a first zone of the two or more zones comprises a first face sheet having a first radial thickness;
- and
- wherein a second zone of the two or more zones comprises a second face sheet having a second radial thickness different from the first radial thickness.
A gas turbine engine, comprising:
- a fan rotatably arranged along an axial centerline;
- a fan casing and a nacelle arranged circumferentially around the centerline and defining a bypass flow duct in which the fan is disposed;
- and
- a plurality of discrete acoustic liner segments with varied geometric properties disposed along the bypass flow duct;
- wherein the plurality of discrete acoustic liner segments comprises a first acoustic liner segment, and a second acoustic liner segment spaced apart from the first acoustic liner segment;
- wherein each the first and second acoustic liner segments includes a cellular core structure, the cellular core structure comprising one or more resonator chambers having a width;
- and
- wherein the width of the one or more resonator chambers of the first acoustic liners differs from the width of the one or more resonator chambers of the second acoustic liner.
A gas turbine engine, comprising:
- a core casing extending circumferentially around the first rotor and defining a portion of an inner surface of a bypass flow duct;
- a nacelle and a fan casing extending circumferentially around the core casing and defining an outer surface of the bypass flow duct;
- a fan rotatably disposed in the bypass flow duct;
- and
- an acoustic liner with two or more zones disposed in the bypass flow duct, wherein the two or more zones being tuned to attenuate a different frequency range of acoustic noise;
- wherein a first zone of the two or more zones comprises a first face sheet having a first radial thickness;
- and
- wherein a second zone of the two or more zones comprises a second face sheet having a second radial thickness different from the first radial thickness.
Dependencies are inferred from the claim text.