US 11,732,610 B2
Sectioned engine structure for a gas turbine engine
Lawrence A. Binek, Glastonbury, CT (US); and Sean R. Jackson, Palm City, FL (US)
Assigned to Raytheon Technologies Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Nov. 24, 2021, as Appl. No. 17/535,078.
Prior Publication US 2023/0160323 A1, May 25, 2023
Int. Cl. F01D 9/02 (2006.01); F01D 25/24 (2006.01); F02C 7/22 (2006.01); F23R 3/00 (2006.01)
CPC F01D 25/24 (2013.01) [F01D 9/02 (2013.01); F02C 7/222 (2013.01); F23R 3/002 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2240/12 (2013.01); F05D 2240/128 (2013.01); F05D 2240/14 (2013.01); F05D 2240/35 (2013.01)] 16 Claims
OG exemplary drawing
 
1. An assembly for a gas turbine engine, comprising:
a stationary engine structure including a diffuser, a combustor, an engine case and a plenum, the combustor disposed within the plenum, the engine case forming a peripheral boundary of the plenum, and a gas path extending sequentially through the diffuser, the plenum and the combustor;
a first section of the stationary engine structure formed as a first monolithic body, the first section including the diffuser and the combustor; and
a second section of the stationary structure formed as a second monolithic body, the second section comprising the engine case;
wherein the second section circumscribes the first section.