# US 11,441,482 B2 · Single track translating inlet

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- Number: US 11,441,482 B2
- Document ID: US11441482B2
- Status: Granted
- Kind: B2
- Application number: 16/431,170
- Filed: 2019-06-04
- Published: 2020-12-10
- Granted: 2022-09-13
- Earliest claimed: 2019-06-04
- Assignees: Rohr, Inc.
- Applicants: Rohr, Inc.
- Inventors: Anthony Lacko
- Web page: https://patentgrep.com/patent/US11441482B2

## CPC

- B64D 29/06: Attaching of nacelles, fairings or cowlings
- F02C 7/042: having variable geometry
- B64D 33/02: of combustion air intakes
- B64C 7/02: Nacelles
- F05D 2250/41: with one degree of freedom
- 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)
- B64C: AEROPLANES; HELICOPTERS
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A translating inlet assembly may comprise a first inlet portion and a second portion configured to translate relative to the first portion. A track may be located in the first portion. A rail may be coupled to the second portion and configured to translate along the track. The rail and the track may form a load bearing component configured to transfer inertial loads experienced by the second portion. A first actuator may be operationally coupled to the rail and configured to drive the rail along the track.

## Claims

### Claim 1

A translating inlet assembly for a nacelle, the translating inlet assembly comprising:
a first portion;
a second portion configured to translate relative to the first portion;
a track located in the first portion;
a rail coupled to the second portion and configured to translate along the track, wherein the rail and the track form a load bearing component configured to transfer inertial loads experienced by the second portion;
a first actuator coupled to the rail and configured to drive the rail along the track;
a guide rod extending from the second portion, wherein the guide rod is located through an orifice defined by the first portion; and
an electrical conduit located through a channel defined by at least one of the rail or the guide rod.

### Claim 2 (depends on 1)

The translating inlet assembly of claim 1, wherein the guide rod includes a stop configured to limit a translation of the guide rod.

### Claim 3 (depends on 1)

The translating inlet assembly of claim 1, further comprising a second actuator operationally coupled to the guide rod.

### Claim 4 (depends on 1)

The translating inlet assembly of claim 1, further comprising a support strut located within the first portion and configured to support the guide rod.

### Claim 5 (depends on 1)

The translating inlet assembly of claim 1, wherein the rail and the track are configured to divert the inertial loads experienced by the second portion away from the first actuator.

### Claim 6

A nacelle, comprising:
a pylon; and
a translating inlet assembly comprising:
a first portion;
a second portion configured to translate relative to the first portion;
a track located in the first portion and coupled to the pylon;
a rail coupled to the second portion and configured to translate along the track, wherein the rail and the track form a load bearing component configured to transfer inertial loads experienced by the second portion to the pylon;
a first actuator coupled to the rail and configured to drive the rail along the track;
a guide rod extending from the second portion, wherein the guide rod is located through an orifice defined by the first portion; and
an electrical conduit located through a channel defined by at least one of the rail or the guide rod.

### Claim 7 (depends on 6)

The nacelle of claim 6, further comprising a second actuator operationally coupled to the guide rod.

### Claim 8 (depends on 6)

The nacelle of claim 6, wherein the translating inlet assembly further comprises a support strut located within the first portion and configured to support the guide rod.

### Claim 9 (depends on 6)

The nacelle of claim 6, wherein the rail and the track are configured to divert the inertial loads experienced by the second portion away from the first actuator.

### Claim 10

A propulsion system, comprising:
a gas turbine engine;
a pylon mounted to the gas turbine engine; and
a translating inlet assembly located forward of the gas turbine engine, the translating inlet assembly comprising:
a first portion;
a second portion configured to translate relative to the first portion;
a track located in the first portion and coupled to the pylon;
a rail coupled to the second portion and configured to translate along the track, wherein the rail and the track form a load bearing component configured to transfer inertial loads experienced by the second portion to the pylon;
a guide rod extending from the second portion, wherein the guide rod is located through an orifice defined by the first portion;
an electrical conduit located through a channel defined by at least one of the rail or the guide rod;
a first actuator operationally coupled to the rail, wherein the first actuator is configured to drive the rail along the track; and
a controller in operable communication with the first actuator and configured to send actuation commands to the first actuator, wherein the controller is configured to locate the second portion a first axial distance from the first portion during a first flight condition and is further configured to locate the second portion a second axial distance from the first portion during a second flight condition, the second axial distance being greater than the first axial distance, and wherein at the second axial distance an airflow gap is formed between the first portion and the second portion such that air may flow through the airflow gap and into the gas turbine engine.

### Claim 11 (depends on 10)

The propulsion system of claim 10, further comprising a second actuator operationally coupled to the guide rod.

### Claim 12 (depends on 10)

The propulsion system of claim 10, wherein the rail and the track are configured to divert the inertial loads experienced by the second portion away from the first actuator.