PROPULSION SYSTEM NACELLE WITH REDUCED NUMBER OF EXTERNAL SPLIT LINES

• US 20150110613A1
• Filed: 10/18/2013
• Published: 04/23/2015
• Est. Priority Date: 10/18/2013
• Status: Active Grant

• Current Assignee: ROHR Incorporated (Rtx Corporation)
• Original Assignee: ROHR Incorporated (Rtx Corporation)
• Inventors: Aten, Michael
• Granted Patent: US 9,873,504 B2
• Time in Patent Office: Days
• US Class Current: 415/182.1
• CPC Class Codes: B64C 7/02 Nacelles
• CPC Class Codes: B64D 29/08 Inspection panels for power plants
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045

Abstract

A cowl for use in a nacelle is provided. The nacelle at least partially surrounds an engine that extends circumferentially about an axially-extending engine centerline. The cowl includes a first side portion and a second side portion. The first and second side portions each are pivotably connected to the nacelle proximate a top of the nacelle. The first and second side portions are configured so that they abut one another to form an external split line proximate the top of the nacelle.

Claims

1. A cowl for use in a nacelle, the nacelle at least partially surrounding an engine that extends circumferentially about an axially-extending engine centerline, the cowl comprising:

a first side portion and a second side portion, the first and second side portions each being pivotably connected to the nacelle proximate a top of the nacelle, and the first and second side portions being configured so that they abut one another to form an external split line proximate the top of the nacelle.

2. The cowl of claim 1, wherein the cowl is an annular structure that extends circumferentially about an axially-extending cowl centerline;

wherein the cowl is circumferentially segmented into at least a first segment and a second segment;

wherein the first side portion is the first segment and the second side portion is the second segment.

3. The cowl of claim 1, wherein the first and second side portions each are selectively moveable between a closed position and an open position;

and

wherein the first and second side portions are configured so that when they are both in their respective closed positions, they abut one another to form the external split line proximate the top of the nacelle.

4. The cowl of claim 1, wherein the first and second side portions each include a top edge portion, a bottom edge portion, a forward edge portion, and an aft edge portion;

wherein the first and second side portions each extend axially between their respective forward and aft edge portions; and

wherein the first and second side portions each extend circumferentially between their respective top and bottom edge portions.

5. The cowl of claim 4, wherein the respective top edge portions of the first and second side portions each are pivotably connected to the nacelle.

6. The cowl of claim 4, wherein the first and second side portions are configured so that when they are both in their respective closed positions, their respective top edge portions abut one another to form the external split line proximate the top of the nacelle.

7. The cowl of claim 1, wherein the external split line proximate the top of the nacelle extends in an axial direction that is at least substantially parallel to the engine centerline.

8. The cowl of claim 4, wherein the first and second side portions are configured so that when they are both in their respective closed positions, their respective bottom edge portions abut one another to form an external split line proximate a bottom of the nacelle.

9. The cowl of claim 1, wherein the first and second side portions are pivotably connected to the nacelle in a manner that permits the first and second side portions to be moved between their respective closed and opened positions without interfering with one another.

10. The cowl of claim 9, wherein the first side portion of the cowl is pivotably connected to the nacelle such that it pivots about an axially-extending pivot axis;

and

wherein the second side portion of the cowl is pivotably connected to the nacelle such that it pivots about the pivot axis.

11. The cowl of claim 1, wherein the cowl is a fan cowl, and the nacelle at least partially surrounds a fan section of a turbofan type gas turbine engine.

12. A cowl for use in a nacelle, the nacelle at least partially surrounding an engine that extends circumferentially about an axially-extending engine centerline, the cowl comprising:

a first side portion and a second side portion, the first and second side portions collectively extending around substantially all of a circumferentially-extending outer surface of at least an axial portion of a fan section of the engine, the first and second side portions being pivotably connected to the nacelle proximate a top of the nacelle such that they abut one another to form an external split line proximate the top of the nacelle.

13. The cowl of claim 12, wherein the nacelle further includes an inlet that extends annularly about the engine centerline;

wherein the first and second side portions of the cowl are configured so that when they are both in their respective closed positions, forward edge portions of each of the first and second side portions abut an aft edge of the unitary structure that forms the radially outer surface of the inlet.

14. The cowl of claim 12, wherein a pylon connects the nacelle and the engine to a vehicle;

wherein the first and second side portions of the cowl are configured so that when they are both in their respective closed positions, they collectively define a protrusion that permits the cowl to cover a forward portion of the pylon.

15. The cowl of claim 12, wherein the nacelle further includes a thrust reverser that extends annularly about the engine centerline;

wherein the first and second side portions of the cowl are configured so that when they are both in their respective closed positions, aft edge portions of each of the first and second side portions abut a forward edge of the thrust reverser.