# US 2020/0400029 A1 · Nacelle thrust reverser compression rod supporting system

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- Number: US 2020/0400029 A1
- Document ID: US20200400029A1
- Status: Published application
- Kind: A1
- Application number: 16/450,799
- Filed: 2019-06-24
- Published: 2020-12-24
- Earliest claimed: 2019-06-24
- Assignees: Rohr, Inc.
- Applicants: Rohr, Inc.
- Inventors: Jinqiu Lu; Frank Zabatta; Travis Michael Frazier; Karina Alejandra Hernandez
- Web page: https://patentgrep.com/patent/US20200400029A1

## CPC

- B64C 7/02: Nacelles
- F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)}
- B64D 29/00: Power-plant nacelles, fairings or cowlings
- B64D 29/06: Attaching of nacelles, fairings or cowlings
- B64D 33/04: of exhaust outlets or jet pipes
- F01D 25/243: {Flange connections; Bolting arrangements (F01D25/265 takes precedence)}
- F02K 1/64: Reversing fan flow
- F02K 1/70: using thrust reverser flaps or doors mounted on the fan housing
- F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
- F02K 1/80: Couplings or connections
- F05D 2230/60: Assembly methods
- F05D 2250/232: conical
- F05D 2260/36: by a form fit connection, e.g. by interlocking
- B64C: AEROPLANES; HELICOPTERS
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.

## Claims

### Claim 1

An aircraft nacelle arrangement, comprising:
a first half comprising a first engagement feature, and a second half comprising a second engagement feature, wherein the first half and the second half are rotatable about a hinge between a closed position in which the first half and the second half enclose a portion of an aircraft engine, and an open position in which the first half and the second half are separated and allow access to the portion of the aircraft engine;
a compression rod comprising a first end and a second end, wherein in response to the aircraft nacelle arrangement being in the closed position, the first end is in contact with the first engagement feature and the second end is in contact with the second engagement feature; and
a first mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the first mounting bracket.

### Claim 2 (depends on 1)

The aircraft nacelle arrangement of claim 1, further comprising a second mounting bracket coupled to the exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the second mounting bracket.

### Claim 3 (depends on 2)

The aircraft nacelle arrangement of claim 2, wherein the second mounting bracket is disposed circumferentially from the first mounting bracket.

### Claim 4 (depends on 1)

The aircraft nacelle arrangement of claim 1, further comprising:
a first engagement member coupled to the first end; and
a second engagement member coupled to the second end.

### Claim 5 (depends on 4)

The aircraft nacelle arrangement of claim 4, wherein in response to the first half being rotated about the hinge to the closed position, the first engagement member is configured to engage the first engagement feature and in response to the second half being rotated about the hinge to the closed position, the second engagement member is configured to engage the second engagement feature.

### Claim 6 (depends on 5)

The aircraft nacelle arrangement of claim 5, wherein at least one of the first engagement member and the second engagement member comprise at least one of a cap or a button end.

### Claim 7 (depends on 1)

The aircraft nacelle arrangement of claim 1, wherein the first engagement feature comprises a first cone coupled to the first half, and wherein the second engagement feature comprises a second cone coupled to the second half.

### Claim 8 (depends on 1)

The aircraft nacelle arrangement of claim 1, wherein the first mounting bracket extends radially outward from the exhaust nozzle flange.

### Claim 9

An arrangement for an aircraft nacelle, comprising:
a turbine engine;
an exhaust assembly coupled to the turbine engine, the exhaust assembly extends aft ward from the turbine engine;
an exhaust nozzle flange, whereby the exhaust assembly is coupled to the turbine engine;
a compression rod disposed radially from the exhaust nozzle flange; and
a first mounting bracket coupled to the exhaust nozzle flange, wherein the compression rod extends through the first mounting bracket.

### Claim 10 (depends on 9)

The arrangement of claim 9, further comprising a second mounting bracket coupled to the exhaust nozzle flange, wherein the compression rod extends through the second mounting bracket.

### Claim 11 (depends on 10)

The arrangement of claim 10, wherein the second mounting bracket is disposed circumferentially from the first mounting bracket.

### Claim 12 (depends on 9)

The arrangement of claim 9, further comprising:
a first engagement member coupled to a first end of the compression rod; and
a second engagement member coupled to a second end of the compression rod.

### Claim 13 (depends on 12)

The arrangement of claim 12, wherein at least one of the first engagement member and the second engagement member comprise at least one of a cap or a button end.

### Claim 14 (depends on 9)

The arrangement of claim 9, wherein the first mounting bracket extends radially outward from the exhaust nozzle flange.

### Claim 15 (depends on 12)

The arrangement of claim 12, further comprising a first half comprising a first engagement feature, and a second half comprising a second engagement feature, wherein the first half and the second half are rotatable about a hinge between a closed position in which the first half and the second half enclose a portion of the turbine engine, and an open position in which the first half and the second half are separated and allow access to the portion of the turbine engine.

### Claim 16 (depends on 15)

The arrangement of claim 15, wherein in response to the first half being rotated about the hinge to the closed position, the first engagement member is configured to engage the first engagement feature and in response to the second half being rotated about the hinge to the closed position, the second engagement member is configured to engage the second engagement feature.

### Claim 17 (depends on 16)

The arrangement of claim 16, wherein the first engagement feature comprises a first cone coupled to the first half, and wherein the second engagement feature comprises a second cone coupled to the second half.

### Claim 18

A method for installing a compression rod, comprising:
coupling a first mounting bracket to an exhaust nozzle flange of an aircraft engine; and
disposing the compression rod to extend through the first mounting bracket.

### Claim 19 (depends on 18)

The method of claim 18, further comprising:
coupling a second mounting bracket to the exhaust nozzle flange; and
disposing the compression rod to extend through the second mounting bracket.

### Claim 20 (depends on 18)

The method of claim 18, further comprising:
rotating a first half towards a closed position; and
rotating a second half towards the closed position,
wherein the compression rod is compressed between the first half and the second half in response to the first half and the second half being rotated to the closed position.