# US 12,600,487 B2 · Segmented nacelle inlet lip with electric anti-icing system

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 12,600,487 B2
- Document ID: US12600487B2
- Status: Granted
- Kind: B2
- Application number: 18/231,579
- Filed: 2023-08-08
- Published: 2025-02-13
- Granted: 2026-04-14
- Earliest claimed: 2023-08-08
- Assignees: Rohr, Inc.
- Applicants: Rohr, Inc.
- Inventors: Jeffrey W. Moe; John E. Van Doren; Aleksandar Ratajac
- Web page: https://patentgrep.com/patent/US12600487B2

## CPC

- B64D 33/02: of combustion air intakes
- B64D 15/12: by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84)
- F01D 25/02: De-icing means for engines having icing phenomena
- F02C 7/047: Heating to prevent icing
- B64D 2033/0206: {comprising noise reduction means, e.g. acoustic liners}
- B64D 2033/0233: {comprising de-icing means}
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)

## Abstract

An assembly for an aircraft propulsion system includes a nacelle inlet structure which extends axially along and circumferentially around a centerline. The nacelle inlet structure includes an inlet lip, an inner barrel, an outer barrel and a plurality of structure segments. The inlet lip forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft away from the inlet lip. The outer barrel projects axially aft away from the inlet lip. The outer barrel is radially outboard of and axially overlaps the inner barrel. Each of the structure segments includes an exterior skin, a mount and an electric heater configured to heat the exterior skin. The exterior skin forms a respective circumferential section of the inlet lip. The mount is connected to the exterior skin. A fastener extends radially through the mount and attaches a respective one of the structure segments to the inner barrel.

## Claims

### Claim 1

An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure extending axially along and circumferentially around a centerline, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel, a bulkhead and a plurality of structure segments;
the inlet lip forming a leading edge of the nacelle inlet structure;
the inner barrel projecting axially aft away from the inlet lip;
the outer barrel projecting axially aft away from the inlet lip, and the outer barrel radially outboard of and axially overlapping the inner barrel;
each of the plurality of structure segments including an exterior skin, a mount and an electric heater configured to heat the exterior skin;
the bulkhead extending radially between and connected to the mount and the outer barrel, the bulkhead including a bulkhead inner flange, a bulkhead outer flange, and a bulkhead web connected to and extending radially between the bulkhead inner flange and the bulkhead outer flange;
the exterior skin forming a respective circumferential section of the inlet lip; and
the mount connected to the exterior skin, the mount including an inner flange, an outer flange and a web connected to and extending radially between the inner flange and the outer flange, the inner flange bonded to the exterior skin, wherein a fastener extends radially through the outer flange and the bulkhead inner flange, and the fastener attaches a respective one of the plurality of structure segments to the inner barrel.

### Claim 2 (depends on 1)

The assembly of claim 1, wherein
the inner barrel projects axially aft away from an inner lip portion of the inlet lip;
the outer barrel projects axially aft away from an outer lip portion of the inlet lip;
the mount is radially outboard of and connected to the inner lip portion of the inlet lip.

### Claim 3 (depends on 2)

The assembly of claim 2, wherein the bulkhead extends radially between and is connected to the mount and a respective circumferential section of the outer lip portion formed by the exterior skin.

### Claim 4 (depends on 1)

The assembly of claim 1, wherein the fastener projects radially inward and partially into a core of the inner barrel.

### Claim 5 (depends on 1)

The assembly of claim 1, wherein the fastener extends radially through the mount connected to and projecting axially forward away from a core of the inner barrel.

### Claim 6 (depends on 1)

The assembly of claim 1, wherein
the inner flange projects axially forward out from the web; and
the outer flange projects axially aft out from the web and axially overlaps the inner barrel.

### Claim 7 (depends on 1)

The assembly of claim 1, wherein
the mount further includes a channel;
the channel projects axially into the mount to the web; and
the channel extends radially within the mount between the inner flange and the outer flange.

### Claim 8 (depends on 1)

The assembly of claim 1, further comprising a seal element axially between and engaged with the mount and the inner barrel.

### Claim 9

An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure extending axially along and circumferentially around a centerline, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel, a first bulkhead and a plurality of structure segments;
the inlet lip forming a leading edge of the nacelle inlet structure;
the inner barrel projecting axially aft away from the inlet lip;
the outer barrel projecting axially aft away from the inlet lip, and the outer barrel radially outboard of and axially overlapping the inner barrel;
each of the plurality of structure segments including an exterior skin, a mount and an electric heater configured to heat the exterior skin;
the first bulkhead extending radially between and connected to the mount and the outer barrel, the first bulkhead including a first bulkhead inner end, a first bulkhead outer end and a bulkhead web connected to and extending radially between the first bulkhead inner end and the first bulkhead outer end, the first bulkhead connected to the inner barrel at the first bulkhead inner end, and the first bulkhead connected to the exterior skin at the first bulkhead outer end;
the exterior skin forming a respective circumferential section of the inlet lip; and
the mount connected to the exterior skin, the mount including an inner flange, an outer flange and a web connected to and extending radially between the inner flange and the outer flange, the inner flange bonded to the exterior skin, wherein a fastener extends radially through the outer flange and the first bulkhead inner end, and the fastener attaches a respective one of the plurality of structure segments to the inner barrel.

### Claim 10 (depends on 9)

The assembly of claim 9, wherein a second fastener extends radially through the exterior skin and the first bulkhead outer end.

### Claim 11 (depends on 9)

The assembly of claim 9, wherein the first bulkhead is bonded to the exterior skin at the first bulkhead outer end.

### Claim 12 (depends on 9)

The assembly of claim 9, further comprising:
a second bulkhead extending between a second bulkhead inner end and a second bulkhead outer end;
the second bulkhead connected to the inner barrel at the second bulkhead inner end; and
the second bulkhead connected to a respective circumferential section of the outer barrel formed by the exterior skin at the second bulkhead outer end.

### Claim 13 (depends on 12)

The assembly of claim 12, wherein a second fastener extends radially through the exterior skin and the second bulkhead.

### Claim 14 (depends on 9)

The assembly of claim 9, wherein the outer barrel is discrete from the exterior skin and mechanically fastened to the first bulkhead at the first bulkhead outer end.

### Claim 15 (depends on 14)

The assembly of claim 14, wherein a second fastener extends radially through the exterior skin, the outer barrel and the first bulkhead outer end.

### Claim 16

An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure extending axially along and circumferentially around a centerline, the nacelle inlet structure including an inlet lip, an inner barrel, an outer barrel, a first bulkhead and a plurality of structure segments;
the inlet lip including an inner lip portion and an outer lip portion that intersects the inner lip portion at a leading edge of the nacelle inlet structure;
the inner barrel projecting axially aft away from the inner lip portion;
the outer barrel projecting axially aft away from the outer lip portion;
each of the plurality of structure segments including an exterior skin, a mount and an electric heater configured to heat the exterior skin, the electric heater extending longitudinally along an entirety of the inner lip portion and an entirety of the outer lip portion;
the mount including an inner flange, an outer flange and a web connected to and extending radially between the inner flange and the outer flange; and
the exterior skin forming a respective circumferential section of the inner lip portion that is mechanically attached to the inner barrel by the mount and a second fastener, and the exterior skin forming a respective circumferential section of the outer lip portion;
wherein a first fastener extends radially through the outer barrel, the exterior skin and an outer radial end of the first bulkhead, and the first fastener engages a nut of a nut plate attached to an inner side of the outer radial end of the first bulkhead; and
wherein the second fastener extends radially through the outer flange and an inner radial end of the first bulkhead, and the second fastener attaches a respective one of the plurality of structure segments to the inner barrel.

### Claim 17 (depends on 16)

The assembly of claim 16, further comprising:
a second bulkhead extending between an inner radial end of the second bulkhead and an outer radial end of the second bulkhead;
the second bulkhead connected to the inner barrel at the inner radial end of the second bulkhead; and
the second bulkhead connected to a respective circumferential section of the outer barrel formed by the exterior skin at the outer radial end of the second bulkhead.

### Claim 18 (depends on 17)

The assembly of claim 17, wherein a third fastener extends radially through the exterior skin and an outer flange of an outer mounting structure the outer radial end of the second bulkhead secured to an aft flange of the outer mounting structure.