US 11,053,801 B2
Gas turbine engine composite vane assembly and method for making the same
Richard C. Uskert, Timonium, MD (US); David J. Thomas, Brownsburg, IN (US); Wayne S. Steffier, Huntington Beach, CA (US); Robert J. Shinavski, Mission Viejo, CA (US); and Adam L. Chamberlain, Mooresville, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US); and Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Nov. 27, 2018, as Appl. No. 16/201,301.
Application 16/201,301 is a continuation of application No. 14/138,725, filed on Dec. 23, 2013, granted, now 10,174,619.
Claims priority of provisional application 61/774,987, filed on Mar. 8, 2013.
Prior Publication US 2020/0024955 A1, Jan. 23, 2020
Int. Cl. F01D 5/14 (2006.01); F01D 9/04 (2006.01); F01D 5/28 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 5/282 (2013.01); F01D 9/044 (2013.01); F05D 2230/64 (2013.01); F05D 2260/36 (2013.01); F05D 2300/6012 (2013.01); F05D 2300/6033 (2013.01); Y02T 50/60 (2013.01); Y10T 29/49229 (2015.01)] 20 Claims
OG exemplary drawing
 
1. A method for forming a gas turbine engine component comprising:
providing at least two composite preform components, the composite preform components comprising an airfoil and an endwall shaped to define an opening sized to receive a portion of the airfoil,
interlocking the composite preform components with a first locking component so that mating faces of the composite preform components face each other, and
inserting a filler material between the mating faces of the composite preform components,
wherein the airfoil includes an airfoil body, a seat portion defined by a portion of an outer end of the airfoil body, and at least one airfoil connecting tab that extends from the outer end perpendicular to the seat portion, the airfoil body including a pressure side wall and a suction side wall that define a hollow space therebetween, and the opening of the endwall is sized to receive therethrough the at least one airfoil connecting tab,
wherein the providing step comprises inserting the at least one airfoil connecting tab of the airfoil into the opening of the endwall so that the endwall rests over the seat portion, and
wherein the seat portion provides the mating face of the airfoil and the portion of the endwall over the seat portion provides the mating face of the endwall, and the inserting the filler material comprises inserting the filler material between the mating face of the airfoil and the mating face of the endwall.