Flutter inhibiting intake for gas turbine propulsion system
Disclosed is a flutter damper including a first plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode, the first plurality of chambers in fluid communication with a flow surface, and a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode, the second plurality of chambers in fluid communication with the flow surface, and wherein the first plurality of chambers and second plurality of chambers are disposed in a grid pattern.
1. A flutter damper comprising:
a first plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode;
the first plurality of chambers in fluid communication with a flow surface; and
a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode;
the second plurality of chambers in fluid communication with the flow surface; and
wherein;
the flow surface is an annular surface disposed about an axis that extends in an axial direction; and
the first plurality of chambers and second plurality of chambers are axially and circumferentially intermixed, along a plurality of axially adjacent annular rows, to form a checkerboard pattern, and each chamber of the first plurality of chambers and the second plurality of chambers has an elliptically shaped portion, for which a minor axis for the first plurality of chambers and a major axis for the second plurality of chambers are disposed along the axial direction.
2. The flutter damper of claim 1 , wherein the elliptically shaped portion of every chamber is spaced from the flow surface by a cylindrically shaped neck portion.
3. The flutter damper of claim 2 , wherein the chambers in the first plurality of chambers have a greater volume than the chambers in the second plurality of chambers.
4. A gas turbine propulsion system comprising:
a nacelle; and
a flutter damper secured to the nacelle, the flutter damper comprising:
a first plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode;
the first plurality of chambers in fluid communication with a flow surface; and
a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode;
the second plurality of chambers in fluid communication with the flow surface; and
wherein;
the flow surface is an annular surface disposed about an axis that extends in a nacelle axial direction; and
the first plurality of chambers and second plurality of chambers are axially and circumferentially intermixed, along a plurality of axially adjacent annular rows, to form a checkerboard pattern, and each chamber of the first plurality of chambers and the second plurality of chambers has an elliptically shaped portion, for which a minor axis for the first plurality of chambers and a major axis for the second plurality of chambers are disposed along the nacelle axial direction.
5. The gas turbine propulsion system of claim 4 , wherein the elliptically shaped portion of every chamber is spaced from the flow surface by a cylindrically shaped neck portion.
6. The gas turbine propulsion system of claim 5 , wherein the chambers in the first plurality of chambers have a greater volume than the chambers in the second plurality of chambers.
7. A method of providing flutter damping to a gas turbine engine, comprising:
absorbing acoustic energy with a first plurality of chambers in fluid communication with a flow surface and configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode; and
absorbing acoustic energy with a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode; and
wherein;
the flow surface is an annular surface disposed about an axis that extends in axial direction; and
the first plurality of chambers and second plurality of chambers are axially and circumferentially intermixed, along a plurality of axially adjacent annular rows, to form a checkerboard pattern, and each chamber of the first plurality of chambers and the second plurality of chambers has an elliptically shaped portion, for which a minor axis for the first plurality of chambers and a major axis for the second plurality of chambers are disposed along the nacelle axial direction.
8. The method of claim 7 , wherein the elliptically shaped portion of every chamber is spaced from the flow surface by a cylindrically shaped neck portion.