Thrust reverser fan ramp with blocker door pocket

Patent metadata

Field	Value
Publication number	US-9765729-B2
Application number	US-201314056629-A
Country	US
Kind code	B2
Filing date	Oct 17, 2013
Priority date	Oct 17, 2013
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

A fan ramp for use in a thrust reverser portion of a nacelle is disclosed. The nacelle is included in a propulsion system. The fan ramp extends circumferentially about an axial fan ramp centerline. The fan ramp includes a forward edge, an aft edge, and a first blocker door pocket. The forward edge is disposed proximate an aft end of a fan case. The fan case at least partially surrounds a fan section of a gas turbine engine. The aft edge is disposed proximate a forward end of an array of cascades. The array of cascades is operable to permit a bypass airstream to pass there through during a thrust reversing operation. The first blocker door pocket is operable to receive at least a portion of a forward edge of a first blocker door included in the nacelle.

First claim

What is claimed is:

1. A thrust reverser comprising:
a first blocker door; and
a fan ramp for use in a thrust reverser portion of a nacelle, the nacelle being included in a propulsion system, the fan ramp extending circumferentially about an axial fan ramp centerline, the fan ramp comprising:
a forward edge disposed proximate an aft end of a fan case, the fan case at least partially surrounding a fan section of a gas turbine engine;
an aft edge disposed proximate a forward end of an array of cascades, the array of cascades being operable to permit a bypass airstream to pass there-through during a thrust reversing operation;
a first blocker door pocket operable to receive a center portion of a forward edge of a first blocker door included in the nacelle that is configured to redirect the bypass airstream toward the array of cascades during the thrust reversing operation;
a second blocker door pocket circumferentially spaced from the first blocker door pocket, the second blocker door pocket being operable to receive a portion of a forward edge of a second blocker door included in the nacelle; and
a third blocker door pocket circumferentially spaced from the first blocker door pocket, the third blocker door pocket being operable to receive a portion of a forward edge of a third blocker door included in the nacelle;
wherein the forward edge of the first blocker door follows a convex curvature as the forward edge of the first blocker door extends laterally between opposing first and second lateral sides of the first blocker door, the first lateral side is next to the second blocker door, and the second lateral side is next to the third blocker door;
a first side portion of the forward edge of the first blocker door is outside of the first blocker door pocket when the center portion is received within the first blocker door pocket; and
wherein the center portion is disposed circumferentially between and circumferentially separates, relative to the axial fan ramp centerline, the first side portion and a second side portion of the forward edge of the first blocker door.

2. The thrust reverser of claim 1 , wherein the fan ramp is an aerodynamic surface that is active during the thrust reversing operation.

3. The thrust reverser of claim 1 , wherein the fan ramp is exposed to the bypass airstream passing through a bypass duct of the propulsion system during the thrust reversing operation.

4. The thrust reverser of claim 3 , wherein the fan ramp aids in guiding the bypass airstream to make a radially outward turn from the bypass duct through the array of cascades during the thrust reversing operation.

5. The thrust reverser of claim 1 , wherein the axial fan ramp centerline is aligned with an axial centerline of the gas turbine engine included in the propulsion system.

6. The thrust reverser of claim 1 , wherein the first blocker door pocket is a depression extending in a radially outward direction relative to the axial fan ramp centerline.

7. The thrust reverser of claim 1 , wherein the first blocker door pocket is a depression extending in an axially forward direction relative to the axial fan ramp centerline.

8. A thrust reversing nacelle for a turbofan propulsion system, the thrust reversing nacelle extending circumferentially about an axial centerline, the thrust reversing nacelle comprising:
an array of cascades extending circumferentially about the axial centerline;
a translating structure operable to be moved in an axial direction between a stowed position, in which the translating structure blocks a bypass airstream from passing from a bypass duct through the array of cascades, and a deployed position, in which the translating structure permits the bypass airstream to pass from the bypass duct through the array of cascades;
a blocker door pivotally mounted to the translating structure, and operable to be moved between a stowed position, in which the blocker door is positioned adjacent to the translating structure and is extending generally parallel to the axial centerline, and a deployed position, in which the blocker door is positioned away from the translating structure and is extending generally perpendicular to the axial centerline to aid in guiding the bypass airstream from the bypass duct through the array of cascades;
a fan ramp operable to aid in guiding the bypass airstream from the bypass duct through the array of cascades when the translating structure and the blocker door are in their respective deployed positions, the fan ramp including a blocker door pocket operable to receive a first portion of a forward edge of the blocker door, wherein a second portion of the forward edge of the blocker door is outside of the blocker door pocket when the first portion is received by the blocker door pocket;
wherein the blocker door includes a surface configured to form an outer peripheral portion of the bypass duct when the blocker door is in the stowed position, the surface extends longitudinally along a length of the blocker door between the forward edge and an aft edge of the blocker door, and the surface extends laterally along a width of the blocker door between opposing first and second sides of the blocker door; and
wherein the second portion of the forward edge projects laterally out from the first portion of the forward edge to the first side of the blocker door.

9. The thrust reversing nacelle of claim 8 , wherein the fan ramp extends between a forward fan ramp edge and an aft fan ramp edge, wherein the forward fan ramp edge is disposed proximate an aft end of a fan case and the aft fan ramp edge is disposed proximate a forward end of the array of cascades.

10. The thrust reverser of claim 1 , wherein the second side portion of the forward edge of the first blocker door is not received within the first blocker door pocket.

11. The thrust reverser of claim 1 , wherein the second side portion of the forward edge of the first blocker door is outside of the first blocker door pocket.

12. A thrust reverser comprising:
a first blocker door; and
a fan ramp for a thrust reverser portion of a nacelle for an aircraft propulsion system, the fan ramp extending circumferentially about an axial centerline, and the fan ramp comprising:
a forward edge disposed proximate an aft end of a fan case, the fan case at least partially surrounding a fan section of a gas turbine engine;
an aft edge disposed proximate a forward end of an array of cascades, the array of cascades being operable to permit a bypass airstream to pass there-through during a thrust reversing operation;
a first blocker door pocket configured to receive a center portion of a forward edge of the first blocker door included in the nacelle, wherein a first side portion of the forward edge of the first blocker door is outside of the first blocker door pocket when the center portion is received within the first blacker door pocket, wherein a second side portion of the forward edge of the first blocker door is outside of the first blocker door pocket when the center portion is received within the first blocker door pocket, and wherein the center portion is disposed circumferentially between and circumferentially separates, relative to the axial centerline, the first side portion and the second side portion.

13. The thrust reverser of claim 12 , further comprising a second blocker door pocket configured to receive a first portion of a forward edge of a second blocker door included in the nacelle, wherein a second portion of the forward edge of the second blocker door is outside of the second blocker door pocket when the first portion of the forward edge of the second blocker door is received with

Assignees

• Aten Michael
• Mitrovic Milan
• Rohr Inc

Inventors

• Aten Michael
• Mitrovic Milan

Classifications

• F02K1/72 Primary

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

• F02K1/70

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F05D2260/97

  Reducing windage losses · CPC title

• F02K1/625

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