Clocked thrust reversers

Patent metadata

Field	Value
Publication number	US-9663239-B2
Application number	US-201314440718-A
Country	US
Kind code	B2
Filing date	Mar 14, 2013
Priority date	Nov 12, 2012
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

An aircraft includes a fuselage including a propulsion system supported within an aft portion. A thrust reverser is mounted proximate to the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser directs thrust at an angle relative to a vertical plane to reduce interference on control surfaces and reduce generation of underbody lift.

First claim

What is claimed is:

1. An aircraft propulsion system comprising:
first and second propulsors mounted at an aft portion of a fuselage, wherein the first propulsor comprises a first engine core disposed along a first engine axis and driving a first fan and a first bypass passage disposed along a first propulsor axis and the second propulsor comprises a second engine core disposed along a second engine axis and driving a second fan and a second bypass passage disposed along a second propulsor axis, wherein the first engine axis and the second engine axis are disposed at an angle relative to a corresponding one of the first propulsor axis and the second propulsor axis; and
first and second thrust reversers mounted proximate to corresponding first and second propulsors, wherein each of the first and second thrust reversers include respective thrust reverser doors, the thrust reverser doors rotatable to a deployed position such that longitudinal centerlines along the thrust reverser doors converge below the thrust reversers thereby reducing lift producible by redirected thrust.

2. The aircraft propulsion system as recited in claim 1 , wherein each of the first thrust reverser and the second thrust reverser doors comprises an upper door and a lower door pivotally mounted for movement between a stowed position and the deployed position.

3. The aircraft propulsion system as recited in claim 2 , wherein the upper door and the lower door are pivotally mounted for movement along the longitudinal centerline that is angled relative to the vertical plane.

4. The aircraft propulsion system as recited in claim 1 , wherein the first and second thrust reversers comprises corresponding first and second upper doors and first and second lower doors that are pivotally mounted for movement between a stowed position and the deployed position.

5. The aircraft propulsion system as recited in claim 4 , wherein the first and second upper doors and the first and second lower doors close on a centerline of corresponding ones of the first and second bypass passages to capture both a bypass flow stream and a core flow stream.

6. An aircraft comprising;
a fuselage including an aft portion;
a propulsion system supported within the aft portion of the fuselage, the propulsion system comprises a first engine core disposed along a first engine axis and driving a first fan within a first bypass passage disposed about a first propulsor axis and
a second engine core disposed along a second engine axis and driving a second fan within a second bypass passage disposed about a second propulsor axis, wherein the first engine axis and the second engine axis are disposed at an angle relative to a corresponding one of the first propulsor axis and the second propulsor axis;
a first thrust reverser mounted in the aft portion of the fuselage proximate to the fan and first bypass passage for directing thrust in a direction to slow the aircraft;
a second thrust reverser mounted in the aft portion of the fuselage proximate to the second fan and second bypass passage for directing thrust in a direction to slow the aircraft wherein each of the first thrust reverser and the second thrust reverser directs thrust at an angle relative to a vertical plane.

7. The aircraft as recited in claim 6 , wherein the first and second thrust reversers are angled away from each other such that airflow directed above the first and second thrust reversers flows away from each other and thrust directed below the first and second thrust reversers combines to reduce excess lift.

8. The aircraft as recited in claim 6 , wherein the first and second thrust reversers comprise corresponding first and second upper doors and first and second lower doors that are pivotally mounted for movement between a stowed position and a deployed position.

9. The aircraft as recited in claim 8 , wherein the first and second doors and the first and second lower doors close on a corresponding one of the first propulsor axis and the second propulsor axis to capture both a bypass flow stream and a core flow stream.

10. The aircraft as recited in claim 7 , wherein the aircraft includes a vertical stabilizer extending upward from the aft portion of the fuselage and the first and second thrust reversers direct thrust away from the vertical stabilizer.

11. The aircraft as recited in claim 10 , wherein the vertical stabilizer is disposed between the first and second bypass passages.

12. The aircraft as recited in claim 10 , wherein the aircraft includes a horizontal stabilizer supported on the vertical stabilizer.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M

Classifications

• F02K1/62

  by blocking the rearward discharge by means of flaps · CPC title

• F02K1/54

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

• B64D27/20

  within, or attached to, fuselages · CPC title

• B64C5/06

  Fins (B64C5/08 takes precedence) · CPC title

• B64C5/02

  Tailplanes · CPC title