Moveable aircraft cowl and bypass section

Patent metadata

Field	Value
Publication number	US-10899464-B2
Application number	US-201815920571-A
Country	US
Kind code	B2
Filing date	Mar 14, 2018
Priority date	Mar 14, 2018
Publication date	Jan 26, 2021
Grant date	Jan 26, 2021

Abstract

The aircraft can have an aircraft engine and a cowl, the engine having an engine part disposed within the cowl, the cowl having a cowl section movable relative to a remainder of the cowl, the engine further having a gas path duct internal to the cowl with a first portion and a cooperating second portion, the second portion mounted to the cowl section, the cowl section moveable between a first position in which the first portion and the second portion are in fluid flow communication with one another and a second position in which the cowl section and the second portion are moved away from the first portion, wherein in the first position at least the second portion obstructs external access to the engine part and in the second position at least the second portion is displaced to permit external access to the engine part.

First claim

The invention claimed is:

1. An aircraft comprising an aircraft engine and a cowl, the aircraft engine having:
an engine part disposed within the cowl, the cowl having a cowl section movable relative to a remainder of the cowl;
an inlet duct secured to the remainder of the cowl and leading to an inlet of the aircraft engine:
an exhaust; and
bypass duct internal to the cowl and branching off the inlet duct and leading to the exhaust, the bypass duct having a first portion and a cooperating second portion, the second portion mounted to the cowl section, the cowl section movable between a first position in which the first portion and the second portion of the bypass duct are in fluid flow communication with one another and a second position in which the cowl section and the second portion of the bypass duct are moved away from the first portion,
wherein in the first position the second portion of the bypass duct obstructs external access to the engine part and in the second position the second portion of the bypass duct is displaced to permit external access to the engine part.

2. The aircraft of claim 1 wherein the cowl section and the remainder of the cowl are connected to one another via a sliding connection, the cowl section being slidingly movable relative to the remainder of the cowl, between the first position and the second position, via the sliding connection.

3. The aircraft of claim 1 wherein the aircraft is a helicopter, the aircraft engine is a turboshaft engine.

4. The aircraft of claim 1 wherein the first portion of the bypass duct comprises an upstream portion of the bypass duct and an oil cooler positioned across the upstream portion of the bypass duct.

5. The aircraft of claim 1 wherein the inlet is a quasi scroll inlet, and the inlet duct has a deflector screen upstream of the quasi scroll inlet, the quasi scroll inlet having a duct extending circumferentially around a portion of the aircraft engine, the duct communicating with the aircraft engine.

6. The aircraft of claim 1 wherein the cowl section and the remainder of the cowl are connected to one another via a hinged connection, the cowl section being hingedly movable relative to the remainder of the cowl, between the first position and the second position, via the hinged connection.

7. The aircraft of claim 1 further comprising a second aircraft engine, both the first aircraft engine and the second aircraft engine being internal to the cowl.

8. The aircraft of claim 1 wherein the engine part includes at least one of a field control unit, fuel nozzles, a harness attachment, engine cam accessories mounted to a gearbox, and a starter.

9. The aircraft of claim 1 wherein the first portion of the bypass duct comprises an oil cooler.

10. An aircraft comprising a cowl, the cowl having:
a cowl section movably mounted to a remainder of the cowl between a first position and a second position;
an inlet duct secured to the remainder of the cowl; and
a bypass duct branching off the inlet duct and leading to an exhaust section, the bypass duct being internal to the cowl and having a first portion and a cooperating second portion, the second portion mounted to the cowl section, the cowl section movable between a first position in which the first portion and the second portion of the bypass duct are in fluid flow communication with one another and a second position in which the cowl section and the second portion of the bypass duct are moved away from the first portion.

11. The aircraft of claim 10 wherein the cowl section and the remainder of the cowl are connected to one another via a sliding connection, the cowl section being slidingly movable relative to the remainder of the cowl, between the first position and the second position, via the sliding connection.

12. The aircraft of claim 10 wherein the aircraft is a helicopter.

13. The aircraft of claim 10 wherein the first portion of the duct comprises an upstream portion of the bypass duct and an oil cooler positioned across the upstream portion of the bypass duct.

14. The aircraft of claim 10 wherein the inlet duct has a deflector screen upstream of the bypass duct.

15. The aircraft of claim 10 wherein the cowl section and the remainder of the cowl are connected to one another via a hinged connection, the cowl section being hingedly movable relative to the remainder of the cowl, between the first position and the second position, via the hinged connection.

16. The aircraft of claim 10 wherein the first portion of the duct comprises an oil cooler.

17. A cowl section for an aircraft, the cowl section having an attachment for movably mounting the cowl section to a remainder of a cowl of the aircraft, the cowl section having a portion of a bypass duct portion secured thereto, the portion of the bypass duct selectively fluidly connectable to a remainder of the bypass duct with movements of the cowl section relative to the remainder of the cowl.

Assignees

• Pratt & Whitney Canada

Inventors

• Weaver Paul
• Smith Scott
• Cunningham Mark Huzzard

Classifications

• F02C7/04 Primary

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title