# US 11,993,389 B2 · Aircraft propulsion system inlet structure with variable airflow inlet area

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- Number: US 11,993,389 B2
- Document ID: US11993389B2
- Status: Granted
- Kind: B2
- Application number: 17/544,521
- Filed: 2021-12-07
- Published: 2022-08-04
- Granted: 2024-05-28
- Earliest claimed: 2020-12-11
- Assignees: Rohr, Inc.
- Applicants: Rohr, Inc.
- Inventors: Timothy Gormley
- Web page: https://patentgrep.com/patent/US11993389B2

## CPC

- B64D 33/02: of combustion air intakes
- F02C 7/042: having variable geometry
- B64D 2033/026: {for supersonic or hypersonic aircraft}
- B64D 2033/0286: {for turbofan engines}
- F05D 2220/323: for aircraft propulsion, e.g. jet engines
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- 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)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle inlet structure. The nacelle inlet structure includes an inner inlet opening, an outer inlet opening and a rotating structure. The rotating structure extends circumferentially about the inner inlet opening. The rotating structure is configured to rotate about an axis between a first position and a second position. The rotating structure at least partially closes the outer inlet opening in the first position. The rotating structure at least partially opens the outer inlet opening in the second position.

## Claims

### Claim 1

An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
the rotating structure extending circumferentially about the inner inlet opening;
the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position;
the rotating structure forming an outer peripheral boundary of the inner inlet opening; and
the rotating structure forming an inner peripheral boundary of the outer inlet opening.

### Claim 2 (depends on 1)

The assembly of claim 1, wherein the inner inlet opening is formed by an inner bore of the rotating structure.

### Claim 3 (depends on 1)

The assembly of claim 1, wherein the inner inlet opening is a fixed area opening.

### Claim 4 (depends on 1)

The assembly of claim 1, wherein the inner inlet opening is a non-annular opening.

### Claim 5 (depends on 1)

The assembly of claim 1, wherein the axis is coaxial with an axial centerline of the nacelle inlet structure.

### Claim 6

An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
the rotating structure extending circumferentially about the inner inlet opening;
the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position; and
the rotating structure forming an inlet lip of the nacelle inlet structure.

### Claim 7

An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
the rotating structure extending circumferentially about the inner inlet opening;
the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position;
the nacelle inlet structure further including a second outer inlet opening;
the rotating structure at least partially closing the second outer inlet opening in the first position; and
the rotating structure at least partially opening the second outer inlet opening in the second position.

### Claim 8 (depends on 7)

The assembly of claim 7, wherein the outer inlet opening and the second outer inlet opening are arranged on opposing sides of the inner inlet opening.

### Claim 9

An assembly for an aircraft propulsion system, comprising:
a nacelle inlet structure including an inner inlet opening, an outer inlet opening and a rotating structure;
the rotating structure extending circumferentially about the inner inlet opening;
the rotating structure configured to rotate about an axis between a first position and a second position, wherein the rotating structure at least partially closes the outer inlet opening in the first position, and the rotating structure at least partially opens the outer inlet opening in the second position;
the nacelle inlet structure further including a static structure that extends circumferentially about the rotating structure; and
the outer inlet opening radially between the rotating structure and the static structure.

### Claim 10 (depends on 9)

The assembly of claim 9, wherein a forward edge of the static structure has a concave portion that forms an outer peripheral boundary of the outer inlet opening.

### Claim 11 (depends on 9)

The assembly of claim 9, wherein
the rotating structure includes a channel that extends axially along the rotating structure;
the static structure is configured to cover the channel in the first position; and
the static structure is configured to uncover the channel in the second position.

### Claim 12 (depends on 1)

The assembly of claim 1, wherein
the inner inlet opening has an inner inlet opening flow area; and
the outer inlet opening has an outer inlet opening flow area that is less than the inner inlet opening flow area.