Conjoined reverse core flow engine arrangement

Patent metadata

Field	Value
Publication number	US-2015121838-A1
Application number	US-201414190175-A
Country	US
Kind code	A1
Filing date	Feb 26, 2014
Priority date	Mar 7, 2013
Publication date	May 7, 2015
Grant date	—

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

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.

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 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.

5 . The system of claim 4 wherein the first engine core is aerodynamically connected to the first propulsor, and the second engine core is aerodynamically connected to the second propulsor.

6 . The system of claim 5 , wherein the first propulsor provides bypass air of the first engine.

7 . 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.

8 . The system of claim 7 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.

9 . The system of claim 8 , 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.

10 . 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 axis and third axis are parallel to one another; and wherein the second axis and fourth axis are angled from one another.

11 . The aircraft of claim 10 , wherein the first axis and the second axis are non-parallel.

12 . The aircraft of claim 10 , wherein the third axis and the fourth axis are non-parallel.

13 . The aircraft of claim 10 , 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.

14 . The aircraft of claim 14 , wherein the first engine core is aerodynamically connected to the first propulsor, and the second engine core is aerodynamically connected to the second propulsor.

15 . The aircraft of claim 15 , wherein the first propulsor delivers a bypass flow of the first engine.

16 . The aircraft of claim 10 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.

17 . The aircraft of claim 17 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.

18 . The aircraft of claim 18 , 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.

19 . A system of adjacent gas turbine engines mounted to a rear of an aircraft fuselage, the system comprising:
a first engine with a first engine core; and a second engine with 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.

20 . A system of adjacent gas turbine engines mounted to a rear of an aircraft fuselage, the system comprising:
a first engine with a first engine core; and a second engine with 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.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Merry Brian D

Classifications

• F01D13/003

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

• F05D2250/314

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

• F02K1/52

  Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing · CPC title

• F02K1/60

  by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers · CPC title

• F02K1/64

  Reversing fan flow · CPC title