US 11,808,203 B2
Offset cores for gas turbine engines
Gabriel L. Suciu, Glastonbury, CT (US); and James D. Hill, Tolland, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Sep. 13, 2019, as Appl. No. 16/570,923.
Application 16/570,923 is a division of application No. 14/921,575, filed on Oct. 23, 2015, granted, now 10,415,466.
Claims priority of provisional application 62/069,234, filed on Oct. 27, 2014.
Prior Publication US 2020/0025071 A1, Jan. 23, 2020
Int. Cl. F02C 3/14 (2006.01); F02C 3/04 (2006.01); F02K 3/00 (2006.01); F01D 25/24 (2006.01); F01D 25/30 (2006.01); F02C 3/10 (2006.01); F02K 3/04 (2006.01)
CPC F02C 3/14 (2013.01) [F01D 25/24 (2013.01); F01D 25/30 (2013.01); F02C 3/04 (2013.01); F02C 3/10 (2013.01); F02K 3/00 (2013.01); F02K 3/04 (2013.01); F05D 2220/36 (2013.01); F05D 2240/24 (2013.01); F05D 2240/35 (2013.01); F05D 2240/60 (2013.01); F05D 2250/314 (2013.01); Y02T 50/60 (2013.01)] 6 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a propulsor including a power turbine defining a centerline axis, and a fan aligned with the centerline axis forward of the power turbine operatively connected to be driven by the power turbine;
a fan case defined radially outward of the fan aligned with the centerline axis, wherein the fan case includes a fan inlet;
an outer core cowl radially inward of the fan case defining an axially extending splitter for dividing fluid flow entering at the fan inlet into a core gas path and a bypass flow path, wherein the core gas path includes a core inlet defined radially between the splitter and an inner core cowl, the core inlet being circumferentially segmented into a first duct inlet and a second duct inlet, the second duct inlet being in fluid isolation from the gas generator, and the first duct inlet is in fluid communication with the gas generator through the first duct, the inner core cowl being located between the outer core cowl and the centerline axis and the bypass flow path being located between the outer core cowl and the fan case;
a gas generator enclosed within the outer core cowl and located within the core gas path aft of the core inlet downstream from the fan and forward of the power turbine, the gas generator defining a generator axis offset from the centerline axis and wherein the fan extends radially and radially traverses the entire gas generator;
a first duct between the core inlet and the gas generator for fluid communication therebetween, wherein at least a portion of the first duct is angled relative to the centerline axis and the generator axis; and
a transition duct between an exhaust outlet of the gas generator and an inlet of the power turbine for fluid communication therebetween.