Conjoined reverse core flow engine arrangement

Patent metadata

Field	Value
Publication number	US-9845159-B2
Application number	US-201414190175-A
Country	US
Kind code	B2
Filing date	Feb 26, 2014
Priority date	Mar 7, 2013
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

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.

First claim

The invention claimed is:

1. 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.

2. The system of claim 1 , wherein the first axis and the second axis are non-parallel.

3. The system of claim 1 , wherein the third axis and the fourth axis are non-parallel.

4. The system of claim 1 further comprising:
a first nacelle positioned around the first propulsor and the first engine core, wherein a downstream end of the first nacelle has a first thrust reverser with at least one pivoting door with an actuation mechanism to pivot the at least one pivoting door between a stowed position and a deployed position in which the at least one door inhibits a flow to provide a thrust reverse of a flow of the first engine.

5. The system of claim 4 further comprising:
a second nacelle positioned around the second propulsor and the second engine core, wherein a downstream end of the second nacelle has a second thrust reverser with at least one pivoting door with an actuation mechanism to pivot the at least one door between a stowed position and a deployed position in which the at least one door inhibits a flow to provide a thrust reverse of a flow of the second engine.

6. The system of claim 5 , wherein the first thrust reverser and second thrust reverser are positioned with respect to first engine core and second engine core so that the first thrust reverser and second thrust reverser are not affected by an uncontained rotor failure of the adjacent engine.

7. 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. The aircraft of claim 7 , wherein the first axis and the second axis are non-parallel.

9. The aircraft of claim 7 , wherein the third axis and the fourth axis are non-parallel.

10. The aircraft of claim 7 further comprising:
a first nacelle positioned around the first propulsor and the first engine core, wherein a downstream end of the first nacelle has a first thrust reverser with at least one pivoting door with an actuation mechanism to pivot the at least one door between a stowed position and a deployed position in which the at least one door inhibits a flow to provide a thrust reverse of a flow of the first engine.

11. The aircraft of claim 10 further comprising:
a second nacelle positioned around the second propulsor and the second engine core, wherein
a downstream end of the second nacelle has a second thrust reverser with at least one pivoting door with an actuation mechanism to pivot the at least one door between a stowed position and a deployed position in which the at least one door inhibits a flow to provide a thrust reverse of a flow of the second engine.

12. The aircraft of claim 11 , wherein the first thrust reverser and second thrust reverser are positioned with respect to first engine core and second engine core so that the first thrust reverser and second thrust reverser are not affected by an uncontained rotor failure of the adjacent engine.

13. 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.

14. 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.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Merry Brian D

Classifications

• F02K1/54

  Nozzles having means for reversing jet thrust (reversing jet thrust using fluid jets F02K1/32) · CPC title

• B64D29/06 Primary

  Attaching of nacelles, fairings or cowlings · CPC title

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F02K1/64

  Reversing fan flow · CPC title

• F01D13/003

  with at least two independent shafts, i.e. cross-compound · CPC title