Donald J Jacques

US Patent:

20200291815, Sep 17, 2020

Filed:

Mar 11, 2019

Appl. No.:

16/297936

Inventors:

- Farmington CT, US
Donald A. Jacques - Tolland CT, US

International Classification:

F01D 25/06
F01D 5/14
F01D 5/26
F01D 9/04
F02K 3/06
F02C 3/04

Abstract:

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending in a spanwise direction, extending between a leading edge and a trailing edge in a chordwise direction, and extending in a thickness direction between a pressure side and a suction side. The airfoil section has a main body and a first skin. The main body includes a plurality of ribs defining a plurality of internal channels. The first skin is attached to the main body to enclose the plurality of internal channels such that the main body and the first skin cooperate to define the pressure and suction sides. A damper has at least one layer of damping material sandwiched between the first skin and the plurality of ribs. A method of forming a gas turbine engine component is also disclosed.