US 12,480,460 B1
Composite tubular structure
Brady Michael Hildebrand, Niskayuna, NY (US); James A. Tallman, Scotia, NY (US); and Grant Henson, Niskayuna, NY (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 21, 2024, as Appl. No. 18/669,738.
Int. Cl. F02K 9/97 (2006.01); B33Y 80/00 (2015.01); F02K 9/64 (2006.01)
CPC F02K 9/972 (2013.01) [B33Y 80/00 (2014.12); F02K 9/64 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A thrust chamber assembly, comprising:
a monolithic preform defining a combustion chamber and a nozzle, the monolithic preform having a tubular shape and including a first end, a second end opposite the first end, an inner surface, and an outer surface, the monolithic preform defining:
a plurality of fluid inlets disposed at the first end,
a plurality of fluid outlets disposed at the first end, and
a plurality of fluid passages between the inner surface and the outer surface, the plurality of fluid passages in fluid communication with the plurality of fluid inlets and the plurality of fluid outlets;
wherein each of the plurality of fluid passages comprises a first pathway portion, a second pathway portion, and a curved portion between the first pathway portion and the second pathway portion;
wherein the curved portion is adjacent the second end, the first pathway portion extends between the plurality of fluid inlets and the curved portion, and the second pathway portion extends between the curved portion and the plurality of fluid outlets;
wherein the plurality of fluid passages are arranged in a helical pattern; and wherein a first fluid passage of the plurality of fluid passages and a second fluid passage of the plurality of fluid passages are arranged such that at least a portion of the first fluid passage and at least a portion of the second fluid passage are interwoven to limit thermal stresses and prevent premature failure of the thrust chamber assembly.