Stable blade vibration damper for gas turbine engine
First Claim
1. A blade-to-blade vibration damper for a gas turbine engine comprising:
- a primary planar load face oriented to abut a portion of a first blade;
a secondary planar load face oriented to abut a portion of a second blade, said secondary face intersecting said primary face forming a vertex therewith, said vertex having an included angle having a value of at least about 90 degrees; and
a distribution of mass in said damper such that a center of gravity thereof is offset from said vertex in a direction toward said primary face.
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Accused Products
Abstract
An improved, highly stable blade-to-blade vibration damper configuration which provides substantially continuous blade vibration damping and sealing of an interplatform gap due to positional stability thereof. Disposed in a subplatform cavity, the damper is comprised of a generally triangular shaped body having a vertex thereof aligned with the interplatform gap. A primary damper load face abuts a first inclined platform load face and a secondary damper load face abuts a second inclined platform load face. Maintenance of sliding planar contact between primary and first load faces and sliding linear contact between secondary and second load faces is afforded by orienting inclined platform faces to have an included angle greater than that of the damper vertex and offsetting a damper center of gravity toward the primary load face. The damper may include one or more legs to orient the damper in the cavity and one or more extending tabs to discourage hot gas flow thereby. In a preferred embodiment, the damper is utilized as an as-cast member, without the need for additional processing or machining, and the vertex included angle is greater than about 90 degrees.
120 Citations
18 Claims
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1. A blade-to-blade vibration damper for a gas turbine engine comprising:
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a primary planar load face oriented to abut a portion of a first blade; a secondary planar load face oriented to abut a portion of a second blade, said secondary face intersecting said primary face forming a vertex therewith, said vertex having an included angle having a value of at least about 90 degrees; and a distribution of mass in said damper such that a center of gravity thereof is offset from said vertex in a direction toward said primary face. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A stage of a rotor of a gas turbine engine comprising:
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a rotatable disk having a plurality of contoured slots in a rim portion thereof defined by a common number of contoured disk posts; a common number of blades having complementarily shaped dovetails disposed in said contoured slots, said blades having platform portions extending therefrom in circumferential and axial directions forming a substantially contiguous flowpath surface disposed radially outwardly from said disk rim; and at least one blade-to-blade vibration damper disposed in a cavity bounded at least in pan by a disk post and respective platforms of first and second adjacent blades, said damper comprising; a primary planar load face oriented to abut said platform of said first blade; a secondary planar load face oriented to abut said platform of said second blade, said secondary face intersecting said primary face forming a vertex therewith, said vertex having an included angle having a value of at least about 90 degrees; and a distribution of mass in said damper such that a center of gravity thereof is offset from said vertex in a direction toward said primary face. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18)
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Specification