# US 11,077,956 B2 · Pressure relief assembly

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- Number: US 11,077,956 B2
- Document ID: US11077956B2
- Status: Granted
- Kind: B2
- Application number: 16/255,189
- Filed: 2019-01-23
- Published: 2020-05-07
- Granted: 2021-08-03
- Earliest claimed: 2018-11-07
- Assignees: Rohr, Inc.
- Applicants: Rohr, Inc.
- Inventors: Michael Sean Pretty; Walter J. Heim
- Web page: https://patentgrep.com/patent/US11077956B2

## CPC

- B64D 29/06: Attaching of nacelles, fairings or cowlings
- B64D 45/00: Aircraft indicators or protectors not otherwise provided for
- B64D 29/00: Power-plant nacelles, fairings or cowlings
- B64D 29/08: Inspection panels for power plants
- B64F 5/10: Manufacturing or assembling aircraft, e.g. jigs therefor
- F02C 7/00: Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00)
- F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- 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)
- 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)

## Abstract

A thrust reverser of a nacelle may include a translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

## Claims

### Claim 1

A nacelle comprising:
an inner fixed structure;
a pressure relief assembly comprising:
a latch mechanism comprising a pressure relief latch pivotably coupled to the inner fixed structure;
a first hinge coupled to the inner fixed structure;
a pressure relief door coupled to and configured to pivot about the first hinge, the pressure relief door comprising a bracket, the pressure relief latch configured to hold the pressure relief door in a closed position, the bracket directly coupled to the pressure relief door, the pressure relief latch releasably coupled to the bracket, wherein:
the pressure relief latch is configured to automatically release from the bracket and pivot radially outward about a hinge line defined by a second hinge in response to a pressure difference across the pressure relief door,
the first hinge is coupled to the inner fixed structure proximate a first end of the pressure relief door, and
the pressure relief latch is coupled to the inner fixed structure proximate a second end of the pressure relief door, the second end opposite the first end.

### Claim 2 (depends on 1)

The nacelle of claim 1, wherein the pressure relief assembly is located on a bottom portion of the inner fixed structure.

### Claim 3 (depends on 1)

The nacelle of claim 1, further comprising a fan exit plane defined by a translating sleeve, wherein the pressure relief assembly is located aft of the fan exit plane.

### Claim 4 (depends on 1)

The nacelle of claim 1, wherein the latch mechanism has a latch mechanism weight and the bracket has a bracket weight, wherein the bracket weight is less than the latch mechanism weight.

### Claim 5 (depends on 1)

The nacelle of claim 1, wherein the inner fixed structure is configured to be mounted to a thrust reverser of the nacelle.