Rear mounted reverse core engine thrust reverser

Patent metadata

Field	Value
Publication number	US-9897040-B2
Application number	US-201414190171-A
Country	US
Kind code	B2
Filing date	Feb 26, 2014
Priority date	Mar 7, 2013
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow.

First claim

The invention claimed is:

1. A gas turbine engine for mounting to a rear of an aircraft fuselage comprising:
a propulsor that rotates on a first axis, the propulsor including a power turbine and a fan driven by the power turbine;
an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section, the engine core being aerodynamically connected to the propulsor and having a second axis, the propulsor disposed axially forward of the engine core and configured to provide air to the engine core, wherein an exit flow from the engine core is directed afterward upon leaving the power turbine; and
a nacelle positioned around the propulsor and engine core, the nacelle attached to the fuselage of the aircraft, wherein a downstream end of the nacelle has a plurality of pivoting doors with an actuation mechanism to pivot each of the plurality of pivoting doors between a stowed position and a vertical deployed position in which the plurality of pivoting doors inhibit a flow to provide a thrust reverse of the flow;
wherein the plurality of doors are positioned in a clamshell arrangement such that an aft end of a first one of the plurality of pivoting doors contacts an aft end of a second one of the plurality of pivoting doors in the vertical deployed position.

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

3. The gas turbine engine of claim 1 , wherein the propulsor delivers bypass air of the engine.

4. The gas turbine engine of claim 1 , wherein the flow includes a bypass flow from the propulsor and an exit flow from the engine core.

5. An aircraft comprising:
a main body fuselage; and
a gas turbine engine mounted to the main body fuselage, the gas turbine engine including:
a propulsor that rotates on a first axis, the propulsor including a power turbine and a fan driven by the power turbine;
an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section, the engine core being aerodynamically connected to the propulsor and having a second axis, the propulsor disposed axially forward of the engine core and configured to provide air to the engine core, wherein an exit flow from the engine core is directed afterward upon leaving the power turbine; and
a nacelle positioned around the propulsor and engine core, wherein a downstream end of the nacelle has a plurality of pivoting doors with an actuation mechanism to pivot each of the plurality of pivoting doors between a stowed position and a vertical deployed position in which the plurality of pivoting doors inhibit a flow to provide a thrust reverse of the flow;
wherein the plurality of doors are positioned in a clamshell arrangement such that an aft end of a first one of the plurality of pivoting doors contacts an aft end of a second one of the plurality of pivoting doors in the vertical deployed position.

6. The aircraft of claim 5 , wherein the first axis and second axis are non-parallel.

7. The aircraft of claim 5 , wherein the propulsor delivers bypass air of the engine.

8. The aircraft of claim 5 , wherein the flow includes a bypass flow from the propulsor and an exit flow from the engine core.

9. The aircraft of claim 5 further comprising:
a second engine adjacent the gas turbine engine, the second engine including:
a propulsor that rotates on a third axis;
an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section, the engine core being aerodynamically connected to the propulsor and having a fourth axis; and
a nacelle positioned around the propulsor and engine core, wherein a downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the at least one door between a stowed position and a vertical deployed position in which the at least one door inhibits a flow to provide a thrust reverse of the flow.

10. The aircraft as set forth in claim 5 , further comprising:
a power turbine positioned downstream of the turbine section of the engine core; and
a gear reduction between the power turbine and a fan of the propulsor to cause the fan to rotate at a slower speed than the power turbine.

11. The aircraft as set forth in claim 10 , wherein the engine core turbine section and said power turbine are separate turbines.

12. The aircraft as set forth in claim 11 , wherein the power turbine rotates on the first axis.

13. A gas turbine engine for mounting to a rear of an aircraft fuselage comprising:
a propulsor;
an engine core mounted at an angle to the propulsor, the engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section, the engine core being aerodynamically connected to the propulsor, the propulsor including a power turbine and a fan driven by the power turbine, the propulsor disposed axially forward of the engine core and configured to provide air to the engine core, wherein an exit flow from the engine core is directed afterward upon leaving the power turbine; and
a nacelle positioned around the propulsor and engine core, the nacelle attached to the fuselage of the aircraft;
wherein a downstream end of the nacelle has a plurality of pivoting doors with an actuation mechanism to pivot the plurality of pivoting doors between a stowed position and a vertical deployed position in which the plurality of pivoting doors inhibit a flow to provide a thrust reverse of the flow; and
wherein when the plurality of pivoting doors are in the deployed position, the plurality of pivoting doors do not contact the engine core or block airflow into the compressor section of the engine core; and
wherein the plurality of doors are positioned in a clamshell arrangement such that an aft end of a first one of the plurality of pivoting doors contacts an aft end of a second one of the plurality of pivoting doors in the vertical deployed position.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M
• Merry Brian D

Classifications

• F05D2250/314

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

• F05D2210/40

  Flow geometry or direction · CPC title

• F02K1/60 Primary

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