US 11,739,690 B2
Attritable engine additively manufactured inlet cap
Lawrence A. Binek, Glastonbury, CT (US); Jesse R. Boyer, Middletown, CT (US); Evan J. Butcher, Suffield, CT (US); Michael Winter, New Haven, CT (US); Jesus A. Garcia, San Diego, CA (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 May 17, 2022, as Appl. No. 17/746,206.
Application 17/746,206 is a continuation of application No. 16/434,453, filed on Jun. 7, 2019, granted, now 11,359,543.
Prior Publication US 2023/0077719 A1, Mar. 16, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/055 (2006.01); B22F 10/28 (2021.01)
CPC F02C 7/055 (2013.01) [B22F 10/28 (2021.01); F05D 2230/31 (2013.01); F05D 2260/607 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine engine comprising:
a compressor;
a combustor;
a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and
inlet member along the gas flowpath upstream of the compressor and comprising a unitarily-formed, single piece combination of:
a three dimensional (3D) lattice portion; and
a nose cap body surrounding the lattice portion,
wherein:
the lattice portion is a regular lattice leaving beam fragments free/cantilevered at a domed forward perimeter.