Nacelle inlet with extended outer barrel
AssigneeRohr, Inc.
InventorsKeith T. Brown, Frank J. Fowler, Stuart J. Byrne, Adam Stein
Life of this patent
Estimating the term…
Abstract
A nacelle inlet is provided for an aircraft propulsion system. This nacelle inlet includes an outer barrel, a bulkhead and a plurality of supports. The outer barrel extends around an axis and along the axis to an aft end. The bulkhead is within and connected to the outer barrel. An aft portion of the outer barrel projects axially aftward from the bulkhead to the aft end. The supports are disposed around the axis and next to the bulkhead. The supports are configured to support the aft portion of the outer barrel.
Claims12
A nacelle inlet for an aircraft propulsion system, the nacelle inlet comprising:
- an outer barrel extending around an axis and along the axis to an aft end;
- a bulkhead within and connected to the outer barrel, wherein an aft portion of the outer barrel projects aftward axially from the bulkhead to the aft end;
- a plurality of supports disposed around the axis and next to the bulkhead, the supports configured to support the aft portion of the outer barrel;
- and
- a plurality of plenums for an active laminar flow control system, wherein the outer barrel is perforated with a plurality of perforations that are respectively fluidly coupled with the plenums, wherein at least two of the plenums are axially forward of the bulkhead, and wherein at least one of the plenums is axially aft of the bulkhead.
An assembly for an aircraft propulsion system, the assembly comprising:
- a fan containment case extending along an axis;
- a nacelle inlet extending along the axis and around the fan containment case, the nacelle inlet including a bulkhead, an outer skin and a plurality of supports;
- the bulkhead within and connected to the outer skin;
- the outer skin axially overlapping the fan containment case;
- and
- the supports disposed around the axis and configured to support the outer skin over the fan containment case;
- and
- a plurality of plenums for an active laminar flow control system, wherein the outer skin is perforated with a plurality of perforations that are respectively fluidly coupled with the plenums, wherein at least two of the plenums are axially forward of the bulkhead, and wherein at least one of the plenums is axially aft of the bulkhead.
A nacelle inlet for an aircraft propulsion system, the nacelle inlet comprising:
- an outer barrel extending around an axis and along the axis to an aft end;
- a bulkhead within and connected to the outer barrel, wherein an aft portion of the outer barrel projects aftward axially from the bulkhead to the aft end;
- a plurality of supports disposed around the axis and next to the bulkhead, the supports configured to support the aft portion of the outer barrel;
- and
- a plurality of plenums for an active laminar flow control system, wherein the outer barrel is perforated with a plurality of perforations that are respectively fluidly coupled with the plenums, wherein a first of the plenums is axially forward of the bulkhead, and wherein a second of the plenums is axially aft of the bulkhead.
Dependencies are inferred from the claim text.