Thrust reverser with forward positioned blocker doors

Patent metadata

Field	Value
Publication number	US-10184426-B2
Application number	US-201514746380-A
Country	US
Kind code	B2
Filing date	Jun 22, 2015
Priority date	Jun 22, 2015
Publication date	Jan 22, 2019
Grant date	Jan 22, 2019

Abstract

An assembly is provided for an aircraft propulsion system. This assembly includes a thrust reverser cascade, a fan ramp fairing and a blocker door. The thrust reverser cascade extends along an axial centerline from a forward cascade end to an aft cascade end. The fan ramp fairing is disposed at the forward cascade end. The fan ramp fairing is configured with a fairing surface that provides a forward boundary for bypass air flowing into the thrust reverser cascade during a first mode of operation. The blocker door is configured to completely axially overlap the fairing surface during a second mode of operation.

First claim

What is claimed is:

1. An assembly for an aircraft propulsion system, the assembly comprising:
a thrust reverser cascade extending along an axial centerline from a forward cascade end to an aft cascade end;
a translating sleeve configured to axially translate relative to the thrust reverser cascade between an open position and a closed position;
a fan ramp fairing disposed at the forward cascade end,
the fan ramp fairing comprising a fan ramp fairing body,
the fan ramp fairing configured with a fairing surface that provides a forward boundary for bypass air flowing into the thrust reverser cascade during a first mode of operation, wherein the translating sleeve is in the open position, and
the fairing surface extending axially from an aftmost end to a forwardmost distal end of the fan ramp fairing body;

a blocker door comprising a first end and a second end,
the first end configured to completely axially overlap the fairing surface during a second mode of operation, wherein the translating sleeve is in the closed position;

a first hinge mounted on the first end of the blocker door that pivotally attaches the blocker door to the translating sleeve,
wherein the first hinge projects into a pocket formed in the fan ramp fairing surface between the aftmost end and the forwardmost distal end; and

a second hinge mounted on the second end of the blocker door that pivotally attaches the blocker door to an inner fixed structure disposed coaxially along the centerline and radially inward of the fan ramp fairing;
wherein the forwardmost distal end of the fan ramp fairing is fixed in the same location when the blocker door is deployed and when the blocker door is stowed.

2. The assembly of claim 1 , wherein the blocker door is configured to project axially forward of the fan ramp fairing during the second mode of operation.

3. The assembly of claim 1 , wherein the fairing surface extends circumferentially about the centerline, and the fairing surface flares radially outward as the fan ramp fairing extends aft along the centerline.

4. The assembly of claim 1 , wherein the fan ramp fairing has an arcuate sectional geometry.

5. The assembly of claim 1 , further comprising a fan case extending axially to and aft case end, wherein the first end of the blocker door is substantially axially coincident with the aft case end.

6. The assembly of claim 1 , further comprising a fan case, wherein the fan ramp fairing extends between the fan case and the thrust reverser cascade.

7. The assembly of claim 1 , wherein the blocker door is configured to provide an aft boundary for bypass air flowing into the thrust reverser cascade during the first mode of operation.

8. An assembly for an aircraft propulsion system, the assembly comprising:
a thrust reverser cascade extending along an axial centerline from a forward cascade end to an aft cascade end;
a translating sleeve configured to axially translate relative to the thrust reverser cascade between a deployed position and a stowed position;
a fan ramp fairing disposed at the forward cascade end,
the fan ramp fairing configured to provide a forward boundary for air flowing into the thrust reverser cascade when the translating sleeve is in the deployed position, and
the fan ramp faring comprises a discrete body that extends axially from a forwardmost edge to an aftmost edge;

a blocker door comprising a first end and a second end,
the first end configured to completely axially cover the fan ramp fairing when the translating sleeve is in the stowed position;

a first hinge mounted on the first end of the blocker door that pivotally attaches the blocker door to the translating sleeve,
wherein the first hinge projects into a pocket formed in the fan ramp fairing between the forwardmost edge and the aftmost edge; and

a second hinge mounted on the second end of the blocker door that pivotally attaches the blocker door to an inner fixed structure disposed coaxially along the centerline and radially inward of the fan ramp fairing;
wherein the forwardmost edge is located at a position when the blocker door is deployed, and the forwardmost edge is located at the same position when the blocker door is stowed.

9. The assembly of claim 8 , further comprising a fan case extending axially to an aft case end, wherein the first end of the blocker door is substantially axially coincident with the aft case end.

10. An assembly for an aircraft propulsion system, the assembly comprising:
a fan case extending along an axial centerline from a forward case end to an aft case end;
a fan cowling circumscribing and providing an aerodynamic covering for the fan case;
a thrust reverser cascade extending axially from a forward cascade end to an aft cascade end;
a translating sleeve configured to axially translate relative to the thrust reverser cascade between an open position and a closed position;
a fan ramp fairing extending between the aft case end and the forward cascade end,
wherein the fan ramp fairing and the fan case are discrete bodies, and
the discrete body of the fan ramp fairing extends from a forwardmost edge to an aftmost edge;

a blocker door comprising a first end and a second end,
the first end configured to completely axially overlap the fan ramp fairing and abut against the fan case to block air flow to the thrust reverser cascade during a mode of operation, wherein the translating sleeve is in the closed position;

a first hinge mounted on the first end of the blocker door that pivotally attaches the blocker door to the translating sleeve,
wherein the first hinge projects into a pocket formed in the fan ramp fairing between the aftmost edge and the forwardmost edge; and

a second hinge mounted on the second end of the blocker door that pivotally attaches the blocker door to an inner fixed structure disposed coaxially along the centerline and radially inward of the fan ramp fairing;
wherein the fan ramp fairing has a sectional geometry when the blocker door is deployed, and the fan ramp fairing has the sectional geometry when the blocker door is stowed.

11. The assembly of claim 10 , wherein the first end of the blocker door is substantially axially coincident with the aft case end during the mode of operation.

12. The assembly of claim 10 , wherein the blocker door is configured to completely axially cover a fairing surface of the fan ramp fairing during the mode of operation, and the fairing surface is configured to provide a forward boundary for bypass air flowing into the thrust reverser cascade during another mode of operation.

Assignees

• Rohr Inc

Inventors

• Schrell Johann S

Classifications

• F02K1/52

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

• F02K1/625 Primary

  the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title

• F02K1/68

  Reversers mounted on the engine housing downstream of the fan exhaust section · CPC title

• F02K1/805

  Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps · CPC title

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title