Turbine blisk including ceramic matrix composite blades and methods of manufacture
US-2016130957-A1 · May 12, 2016 · US
Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade
US2016341221A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2016341221-A1 |
| Application number | US-201515112032-A |
| Country | US |
| Kind code | A1 |
| Filing date | Jan 23, 2015 |
| Priority date | Jan 24, 2014 |
| Publication date | Nov 24, 2016 |
| Grant date | — |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The damper includes a cantilever spring arm that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. A method is also provided for damping a blade of a gas turbine engine. The method includes deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade.
First claim
Opening claim text (preview).
What is claimed is: 1 . A blade for a gas turbine engine, comprising: an airfoil portion with at least one internal cavity; and a damper located within the internal cavity, the damper including a cantilever spring arm. 2 . The blade as recited in claim 1 , wherein the airfoil portion extends from a platform portion of a fan blade. 3 . The blade as recited in claim 2 , wherein the cantilever spring arm extends from a base between a concave pressure side and a convex suction side. 4 . The blade as recited in claim 3 , wherein the cantilever spring arm terminates with a rub surface pad. 5 . The blade as recited in claim 4 , wherein the rub surface pad is located adjacent to a friction bridge between the concave pressure side and the convex suction side. 6 . The blade as recited in claim 5 , wherein the rub surface pad is located between the friction bridge and a motion limit bridge between the concave pressure side and the convex suction side. 7 . The blade as recited in claim 5 , further comprising a clip removable mounted to at least one of the rub surface pad and the friction bridge. 8 . The blade as recited in claim 5 , further comprising a clip additively manufactured to the friction bridge, the clip additively manufactured of a material different than the friction bridge. 9 . The blade as recited in claim 5 , further comprising a clip additively manufactured to the rub surface pad, the clip additively manufactured of a material different than the rub surface pad. 10 . A fan blade for a gas turbine engine, comprising: an airfoil portion with at least one internal cavity; and a damper located within the internal cavity, the damper including a cantilever spring aim that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. 11 . The fan blade as recited in claim 10 , wherein the cantilever spring arm extends from a base between a concave pressure side and a convex suction side. 12 . The fan blade as recited in claim 10 , wherein the rub surface pad is located between the friction bridge and a motion limit bridge between the concave pressure side and the convex suction side. 13 . The fan blade as recited in claim 10 , wherein the cantilever spring arm extends toward a leading edge of the airfoil portion. 14 . The fan blade as recited in claim 10 , wherein the cantilever spring aim extends toward a trailing edge of the airfoil portion. 15 . A method of damping a blade of a gas turbine engine, comprising: deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade. 16 . The method as recited in claim 15 , further comprising deflecting the cantilever spring arm under a centrifugal load generated by rotation of the blade. 17 . The method as recited in claim 16 , wherein the centrifugal load generated by rotation of the blade is on the order of about thirty and about sixty thousand Gs. 18 . The method as recited in claim 16 , wherein the rub surface pad and the friction bridge include a fretting surface coating. 19 . The method as recited in claim 15 , further comprising additively manufacturing the concave pressure side and the convex suction side. 20 . The method as recited in claim 19 , further comprising additively manufacturing the cantilever spring arm and the friction bridge with the concave pressure side and the convex suction side.
Assignees
Inventors
Classifications
Assembly methods · CPC title
by sintering · CPC title
with deposition of material · CPC title
in gas turbines · CPC title
Layer deposition · CPC title
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Frequently asked questions
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- What does patent US2016341221A1 cover?
- A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The dampe…
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F04D29/668. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Thu Nov 24 2016 00:00:00 GMT+0000 (Coordinated Universal Time) (A1). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).