Nacelle inlet with extended outer barrel

Patent metadata

Field	Value
Publication number	US-9874228-B2
Application number	US-201514713680-A
Country	US
Kind code	B2
Filing date	May 15, 2015
Priority date	May 15, 2015
Publication date	Jan 23, 2018
Grant date	Jan 23, 2018

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.

First claim

We claim:

1. 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.

2. The nacelle inlet of claim 1 , wherein a first of the supports comprises a gusset.

3. The nacelle inlet of claim 1 , wherein a first of the supports comprises a strut.

4. The nacelle inlet of claim 1 , wherein a first of the supports is mounted to and extends between the bulkhead and the aft portion of the outer barrel.

5. The nacelle inlet of claim 1 , further comprising a fan containment case attachment ring, wherein the bulkhead and a first of the supports are independently mounted to the attachment ring.

6. The nacelle inlet of claim 1 , further comprising a second bulkhead within and connected to the outer barrel, wherein the bulkhead is axially between the second bulkhead and the aft end.

7. The nacelle inlet of claim 1 , further comprising an inlet lip forming an inlet orifice of the nacelle inlet, wherein at least a circumferential portion of the inlet lip and a circumferential portion of the outer barrel are integrally formed together from a monolithic outer skin.

8. The nacelle inlet of claim 1 , further comprising an inlet lip forming an inlet orifice of the nacelle inlet, wherein the inlet lip is discrete from and attached to the outer barrel.

9. The nacelle inlet of claim 1 , further comprising an acoustic panel circumscribed by the outer barrel, wherein the aft portion of the outer barrel projects axially beyond and aft of the acoustic panel to the aft end.

10. 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.

11. The assembly of claim 10 , wherein a first of the supports comprises a gusset mounted to and extending between the bulkhead and the outer skin.

12. 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.

Assignees

• Rohr Inc

Inventors

• Brown Keith T
• Fowler Frank J
• Byrne Stuart J
• Stein Adam

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2260/963

  by Helmholtz resonators · CPC title

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D2033/0226

  comprising boundary layer control means · CPC title