	US 12,234,747 B2
	Part of a gas turbine engine and method for the manufacturing the part
Christoph Klaus, Teltow (DE); Reyya Nitin Rao, Berlin (DE); Sebastian Spitzer, Dresden (DE); and Maik Gude, Dresden (DE)
Assigned to ROLLS-ROYCE DEUTSCHLAND LTD & CO KG, Blankenfelde-Mahlow (DE)
Filed by Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow (DE)
Filed on Dec. 15, 2022, as Appl. No. 18/066,536.
Claims priority of application No. 10 2021 214 605.8 (DE), filed on Dec. 17, 2021.
Prior Publication US 2023/0193770 A1, Jun. 22, 2023
Int. Cl. F01D 9/04 (2006.01); B29C 70/38 (2006.01); F01D 5/28 (2006.01)

CPC F01D 9/041 (2013.01) [B29C 70/38 (2013.01); B32B 2262/16 (2021.05); F01D 5/282 (2013.01); F05D 2220/36 (2013.01); F05D 2230/30 (2013.01); F05D 2300/603 (2013.01)]

16 Claims

1. A method for producing a component of a gas turbine engine, comprising:

providing:

a substrate;

a fiber-composite material having a plurality of rovings, and

at least one chosen from:

at least one of the plurality of rovings, along a spatial extent thereof, having a variable cross section prior to depositing on the substrate, and

at least two of the plurality of rovings each having a dissimilar cross section as compared to one another prior to depositing on the substrate,

wherein the at least one chosen from the at least one of the plurality of rovings and the at least two of the plurality of rovings are deposited on the substrate via tailored fiber placement, and the variable cross section or the dissimilar cross-sections are achieved during depositing by a variation in tension with respect to the substrate imparted on the at least one of the plurality of rovings or the at least two of the plurality of rovings.