Liner for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsMichaela M. Logue, Oliver V. Atassi
Life of this patent
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Abstract
A gas turbine engine is provided having a fan case and a translating sleeve positioned downstream from the fan case. A flow channel extends between the fan case and the translating sleeve. The flow channel includes an inner diameter and an outer diameter. A structural guide vane is positioned within the flow channel and extends from the inner diameter to the outer diameter. A liner is positioned between an aft end of the fan case and an aft end of the translating sleeve to reduce vibratory stress on the structural guide vane.
Claims14
A gas turbine engine comprising:
- a fan case, a translating sleeve positioned downstream in a direction of flow from the fan case,
- a flow channel extending axially between the fan case and the translating sleeve, the flow channel including a plurality of walls including an inner diameter wall and an outer diameter wall, and a structural guide vane positioned within the flow channel and extending from the inner diameter wall to the outer diameter wall;
- and
- a plurality of liner patches on one or both of the plurality of walls for covering a discrete portion of the one or both of the plurality of walls, the plurality of liner patches being mutually independent and individual vibration attenuating liner patches, the plurality of liner patches positioned aft of the fan case, proximate in the direction of flow to the structural guide vane and distal in the direction of flow to the fan case and the translating sleeve, and the plurality of liner patches being mutually spaced in the direction of flow along the flow channel so that the plurality of liner patches are mutually nonabutting, and
- wherein the plurality of liner patches reduce vibratory stress on the structural guide vane, the liner having a thickness capable of attenuating vibrations having a frequency of less than 1,000 Hertz.
A method of reducing vibratory stress on a structural guide vane in a gas turbine engine,
- wherein the gas turbine engine includes:
- a fan case, a translating sleeve positioned downstream in a direction of flow from the fan case,
- a flow channel extending axially between the fan case and the translating sleeve, the flow channel including a plurality of walls including an inner diameter wall and an outer diameter wall, and the structural guide vane positioned within the flow channel and extending from the inner diameter wall to the outer diameter wall;
- and
- the structural guide vane extending between an inner diameter and outer diameter of a flow channel, the flow channel extending axially between a fan case and a translating sleeve,
- the method comprising:
- positioning a plurality of liner patches on one or both of the plurality of walls for covering a discrete portion of the one or both of the plurality of walls, the plurality of liner patches being mutually independent and individual vibration attenuating liner patches, the plurality of liner patches positioned aft of the fan case, proximate in the direction of flow to the structural guide vane and distal in the direction of flow to the fan case and the translating sleeve, and the plurality of liner patches being mutually spaced in the direction of flow along the flow channel so that the plurality of liner patches are mutually nonabutting, and
- wherein the plurality of liner patches reduce vibratory stress on the structural guide vane, the liner having a thickness capable of attenuating vibrations having a frequency of less than 1.000 Hertz.
Dependencies are inferred from the claim text.