Patent ID: 11946412
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
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 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, 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; and
a transition duct between an exhaust outlet of the gas generator and an inlet of the power turbine for fluid communication therebetween.