Pusher fan engine with in wing configuration

Patent metadata

Field	Value
Publication number	US-2016207631-A1
Application number	US-201514600946-A
Country	US
Kind code	A1
Filing date	Jan 20, 2015
Priority date	Jan 20, 2015
Publication date	Jul 21, 2016
Grant date	—

Abstract

An aircraft is provided that includes a wing and a pusher fan engine. The pusher fan engine is configured in the wing.

First claim

What is claimed is:

1 . An aircraft, comprising:
a wing; and a pusher fan engine configured in the wing.

2 . The aircraft of claim 1 , wherein the pusher fan engine has a generally mid-wing configuration.

3 . The aircraft of claim 1 , wherein the pusher fan engine includes a nacelle, and the wing intersects the nacelle.

4 . The aircraft of claim 1 , further comprising an inlet duct extending within the wing to a core of the pusher fan engine.

5 . The aircraft of claim 4 , wherein the inlet duct extends from an inlet arranged at a side of the wing.

6 . The aircraft of claim 5 , wherein the side is a suction side of the wing.

7 . The aircraft of claim 5 , further comprising a splitter configured between the side and the inlet, the splitter adapted to at least partially divert wing boundary layer air away from the inlet.

8 . The aircraft of claim 1 , wherein the pusher fan engine includes a core generally aligned with the wing.

9 . The aircraft of claim 1 , wherein
the wing includes a pair of ribs; and the pusher fan engine includes a core and a fan casing, the core is disposed spanwise between the ribs, and the fan casing is mounted to the ribs.

10 . The aircraft of claim 9 , wherein the pusher fan engine includes one or more guide vanes structurally tying the core with the fan casing.

11 . The aircraft of claim 1 , wherein the pusher fan engine is disposed adjacent a trailing edge of the wing.

12 . The aircraft of claim 1 , wherein the pusher fan engine is configured as a geared pusher fan engine.

13 . The aircraft of claim 1 , wherein the pusher fan engine includes a fan rotor, a turbine rotor and a gear train connecting the turbine rotor with the fan rotor.

14 . The aircraft of claim 13 , wherein the turbine rotor is a free turbine rotor.

15 . The aircraft of claim 1 , wherein the pusher fan engine includes a fan rotor and a core axially forward of the fan rotor.

16 . The aircraft of claim 16 , wherein an axis of rotation of the fan rotor is non-coaxial with an axis of rotation of the core.

17 . An aircraft, comprising:
a wing; and a pusher fan engine including a fan rotor and a nacelle housing the fan rotor; wherein the wing intersects the nacelle.

18 . The aircraft of claim 17 , further comprising an inlet duct extending within the wing to a core of the pusher fan engine, wherein the inlet duct extends at least from an inlet arranged at a side of the wing.

19 . A pusher fan engine for arranging with a wing of an aircraft, comprising:
a core; a pusher fan rotor downstream of the core; and a nacelle housing the pusher fan rotor; wherein the nacelle is configured to be mounted to and integrated with the wing.

20 . The pusher fan engine of claim 19 , wherein the nacelle is configured to be intersected by the wing.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Lord Wesley K
• Chandler Jesse M

Classifications

• B64D33/02

  of combustion air intakes · CPC title

• B64D29/02

  associated with wings · CPC title

• B64D2033/0286

  for turbofan engines · CPC title

• B64C3/32

  specially adapted for mounting power plant · CPC title

• B64D27/18 Primary

  within, or attached to, wings · CPC title