Engine installation

Patent metadata

Field	Value
Publication number	US-9346551-B2
Application number	US-201414173394-A
Country	US
Kind code	B2
Filing date	Feb 5, 2014
Priority date	Mar 5, 2013
Publication date	May 24, 2016
Grant date	May 24, 2016

Abstract

A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other.

First claim

The invention claimed is:

1. A fuselage mounted gas turbine engine installation, the installation comprising:
at least one propeller stage that defines a plane of rotation substantially perpendicular to an axis of rotation of the propeller stage; and
a gas turbine core configured, in use, to drive the propeller stage, where the core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other, the core and the propeller stage being positioned relative to each other such that the plane of rotation of the propeller stage passes through the core between the propeller stage and the fuselage.

2. The fuselage mounted gas turbine engine installation according to claim 1 , where the position of the core is disposed such that the cantilevered load produced by the core and propeller stage combined is reduced in comparison with a combined cantilevered load that would be produced if the rotational axes of the core and propeller stage were the same.

3. The fuselage mounted gas turbine engine installation according to claim 1 , where the installation is rear mounted on the fuselage.

4. An aircraft provided with a fuselage mounted gas turbine engine installation in accordance with claim 1 .

5. The fuselage mounted gas turbine engine installation according to claim 1 , where
the core is provided with a core nacelle, and
at least a portion of drive gear for the propeller stage is provided within a propeller stage nacelle, the blades of the propeller stage being arranged to rotate outside of the propeller stage nacelle and where the core nacelle and propeller stage nacelle are separate.

6. The fuselage mounted gas turbine engine installation according to claim 5 , where the core is at least partially supported by a core pylon.

7. The fuselage mounted gas turbine engine installation according to claim 6 , where the propeller stage is supported by a propeller stage pylon which extends from the fuselage.

8. The fuselage mounted gas turbine engine installation according to claim 7 , where the propeller stage nacelle is directly connected to the propeller stage pylon.

9. The fuselage mounted gas turbine engine installation according to claim 7 , where the core is provided with an exhaust that passes around the propeller stage pylon.

10. The fuselage mounted gas turbine engine installation according to claim 7 , where at least a proportion of drive components for operatively connecting the core and the propeller stage are contained within the propeller stage pylon.

11. The fuselage mounted gas turbine engine installation according to claim 7 , where the blades of the propeller stage are positioned forward of the propeller stage pylon.

12. A gas turbine engine installation mounted to a fuselage, the installation comprising:
at least one propeller stage; and
a gas turbine core configured, in use, to drive the propeller stage, where the core is external to the fuselage and rotational axes of the core and propeller stage are offset with respect to each other, the propeller stage and core being positioned such that blades of the propeller stage extend aft of the core position, the core including an exhaust nozzle that is ducted to prevent the incidence of exhaust gas into the blades of the propeller stage.

13. The fuselage mounted gas turbine engine installation according to claim 12 , where, in use, exhaust ducted by the exhaust nozzle passes between the propeller stage and the fuselage and passes through a plane of rotation defined by the propeller stage, the plane of rotation being substantially perpendicular to the axis of rotation of the propeller stage.

14. The fuselage mounted gas turbine engine installation according to claim 12 , where the exhaust nozzle includes an exhaust nozzle outlet that is elongated to increase the fuselage area screened by an exhaust plume produced by the exhaust nozzle outlet from acoustic waves generated by the propeller stage.

15. The fuselage mounted gas turbine engine installation according to claim 12 , where
the propeller stage is supported by a propeller stage pylon that extends from the fuselage, and
the blades of the propeller stage are positioned aft of the propeller stage pylon and the core is positioned forward of the propeller stage pylon.

Assignees

• Rolls Royce Plc

Inventors

• Stretton Richard Geoffrey

Classifications

• B64D27/14 Primary

  within, or attached to, fuselages · CPC title

• B64D29/04

  associated with fuselages · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• Y02T50/66

  Cross-Sectional Technologies · mapped topic

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title