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US 9,845,159 B2Granted
Conjoined reverse core flow engine arrangement
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Brian D. Merry
Life of this patent
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Abstract
A system of conjoined gas turbine engines has a first engine with a first propulsor having a first axis and a first engine core having a second axis, and a second engine with a second propulsor having a third axis and a second engine core having a fourth axis. The first axis and third axis are parallel to one another; and the second axis and fourth axis are angled from one another.
Claims14
A system of conjoined gas turbine engines, the system comprising:
- a first engine with a first propulsor having a first axis and a first engine core having a second axis;
- a second engine with a second propulsor having a third axis and a second engine core having a fourth axis;
- wherein the first axis and third axis are parallel to one another;
- and
- wherein the second axis and fourth axis are angled from one another, such that the first engine core diverges from the second engine core in an axially aft direction;
- wherein the first engine core and the second engine core each include a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the respective propulsor than the compressor section;
- wherein the first engine core is aerodynamically connected to the first propulsor, and the second engine core is aerodynamically connected to the second propulsor;
- and
- wherein the first propulsor provides bypass air of the first engine.
6 more elements
An aircraft comprising:
- a main body fuselage;
- a first engine mounted to the fuselage, the first engine having a first propulsor having a first axis and a first engine core having a second axis;
- a second engine mounted adjacent the first engine, the second engine having a second propulsor having a third axis and a second engine core having a fourth axis;
- wherein the first engine core and the second engine core are disposed generally parallel to a horizontal plane of the aircraft;
- wherein the first axis and third axis are parallel to one another;
- and
- wherein the second axis and fourth axis are angled from one another such that the first engine core diverges from the second engine core in an axially aft direction;
- wherein the first engine core and the second engine core each include a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the respective propulsor than the compressor section;
- wherein the first engine core is aerodynamically connected to the first propulsor, and the second engine core is aerodynamically connected to the second propulsor;
- and
- wherein the first propulsor delivers a bypass flow of the first engine.
8 more elements
A system of adjacent gas turbine engines mounted to a rear of an aircraft fuselage, the system comprising:
- a first engine with a first propulsor and a first engine core;
- and
- a second engine with a second propulsor and a second engine core;
- wherein the first engine core and second engine core are not affected by an uncontained rotor failure of the adjacent engine;
- wherein the first engine core and the second engine core each include a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the respective propulsor than the compressor section;
- wherein the first engine core is aerodynamically connected to the first propulsor, and the second engine core is aerodynamically connected to the second propulsor;
- and
- wherein the first propulsor delivers a bypass flow of the first engine.
5 more elements
A system of adjacent gas turbine engines mounted to a rear of an aircraft fuselage, the system comprising:
- a first engine with a first propulsor and a first engine core;
- and
- a second engine with a second propulsor and a second engine core;
- wherein the first engine core and second engine core are positioned such that each of the first engine and second engine is out of a burst zone of the adjacent engine;
- wherein the first engine core and the second engine core each include a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the respective propulsor than the compressor section;
- wherein the first engine core is aerodynamically connected to the first propulsor, and the second engine core is aerodynamically connected to the second propulsor;
- and
- wherein the first propulsor delivers a bypass flow of the first engine.
5 more elements
Dependencies are inferred from the claim text.