Propulsion system, aircraft having a propulsion system, and method of manufacturing an aircraft

Patent metadata

Field	Value
Publication number	US-2022009645-A1
Application number	US-202117302325-A
Country	US
Kind code	A1
Filing date	Apr 30, 2021
Priority date	May 5, 2020
Publication date	Jan 13, 2022
Grant date	—

Abstract

A propulsion system for an aircraft is taught herein. The propulsion system includes, but is not limited to, an engine. The propulsion system further includes, but is not limited to, an outer cover associated with the engine. The engine and the outer cover are configured for coupling to the aircraft. The propulsion system further includes, but is not limited to, an external engine component. The propulsion system still further includes, but is not limited to, a coupler that operatively couples the external engine component to the engine. The external engine component is configured to be coupled to the aircraft at a location spaced apart from the engine.

First claim

What is claimed is:

1 . A propulsion system for an aircraft, the propulsion system comprising:
an engine; an outer cover associated with the engine, the engine and the outer cover configured for coupling to the aircraft; an external engine component; and a coupler operatively coupling the external engine component to the engine, wherein the external engine component is configured to be coupled to the aircraft at a location spaced apart from the engine.

2 . The propulsion system of claim 1 , wherein the outer cover comprises a nacelle.

3 . The propulsion system of claim 1 , wherein the engine is free of external engine components.

4 . The propulsion system of claim 1 , wherein the outer cover is free of peripheral protuberances along a longitudinal portion of the outer cover that corresponds with an entire longitudinal length of the engine.

5 . The propulsion system of claim 1 , wherein a gap is defined between an internal surface of the outer cover and an entire outer surface of the engine, and wherein a maximum magnitude of the gap is smaller than a minimum external dimension of the external engine component.

6 . An aircraft comprising:
a fuselage; a wing; a propulsion system coupled with at least one of the fuselage and the wing, wherein the propulsion system comprises:
an engine,
an outer cover associated with the engine,
an external engine component, and
a coupler operatively coupling the external engine component to the engine,
wherein the external engine component is coupled to the aircraft at a location spaced apart from the engine.

7 . The aircraft of claim 6 , wherein the outer cover comprises a nacelle.

8 . The aircraft of claim 6 , wherein the engine and the outer cover are coupled to one of the fuselage and the wing via a pylon.

9 . The aircraft of claim 8 , wherein the external engine component is mounted within the pylon.

10 . The aircraft of claim 8 , wherein the external engine component is mounted within the wing.

11 . The aircraft of claim 8 , wherein the external engine component is mounted within the fuselage.

12 . The aircraft of claim 6 , wherein the engine and the outer cover are embedded within a portion of the aircraft.

13 . The aircraft of claim 12 , wherein the external engine component is mounted within the wing.

14 . The aircraft of claim 12 , wherein the external engine component is mounted within the fuselage.

15 . The aircraft of claim 6 , wherein the engine is free of external engine components.

16 . The aircraft of claim 6 , wherein the outer cover is free of peripheral protuberances along a longitudinal portion of the outer cover that corresponds with an entire longitudinal length of the engine.

17 . The aircraft of claim 6 , wherein a gap is defined between an internal surface of the outer cover and an entire outer surface of the engine, and wherein a maximum magnitude of the gap is smaller than a minimum external dimension of the external engine component.

18 . A method of manufacturing an aircraft, the method comprising:
obtaining a wing, a fuselage, an engine, an engine cover, an external engine component, and a coupler; coupling the wing with the fuselage; mounting the engine cover to the engine; mounting the engine cover and the engine to one of the wing and the fuselage; mounting the external engine component at a location spaced apart from the engine; and coupling the external engine component to the engine via the coupler.

19 . The method of claim 18 , wherein mounting the engine and the engine cover to the aircraft comprises attaching the engine and the engine cover to one of the wing and the fuselage with a pylon.

20 . The method of claim 18 , wherein mounting the engine and the engine cover to the aircraft comprises embedding the engine and the engine cover into one of the wing and the fuselage.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Freund Donald
• Muzychka Derek
• Klutzke Douglas

Classifications

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64D27/402

  comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant · CPC title

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title