Apparatus and methods for powering an electrical device associated with an aircraft rotor

Patent metadata

Field	Value
Publication number	US-9828109-B2
Application number	US-201414338711-A
Country	US
Kind code	B2
Filing date	Jul 23, 2014
Priority date	Jul 23, 2014
Publication date	Nov 28, 2017
Grant date	Nov 28, 2017

Abstract

Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.

First claim

The invention claimed is:

1. An apparatus for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft, the apparatus comprising:
a rotor shaft configured to be coupled to the bladed rotor of the aircraft and to be driven by a turbine shaft of the engine via a speed-reducing power transfer device;
a speed-augmenting power transfer device having an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device; and
an electric generator coupled to the output of the speed-augmenting power transfer device and configured to be disposed inside a hub of the bladed rotor and axially coincide with the bladed rotor to generate electrical power for the device associated with the bladed rotor.

2. The apparatus of claim 1 , wherein the output of the speed-augmenting power transfer device outputs rotational motion in a direction opposite that of the rotor shaft.

3. The apparatus of claim 1 , wherein the electrical generator includes a member coupled for rotation with the rotor shaft.

4. The apparatus of claim 1 , wherein the speed-augmenting power transfer device comprises a two-stage epicyclic gear train.

5. The apparatus of claim 4 , wherein a first stage of the epicyclic gear train has a star arrangement having a fixed carrier and a second stage of the epicyclic gear train has a planetary arrangement having a fixed ring.

6. The apparatus of claim 1 , wherein at least part of the speed-augmenting power transfer device is disposed inside the rotor shaft.

7. The apparatus of claim 1 , wherein the speed-augmenting power transfer device is disposed adjacent an end of the rotor shaft and inside the hub of the bladed rotor.

8. The apparatus of claim 1 , wherein the speed-augmenting power transfer device is disposed adjacent an end of the rotor shaft distal to the rotor.

9. The apparatus of claim 1 , wherein the rotor shaft comprises a first passage therethrough and the speed-augmenting power transfer device comprises a second passage therethrough, the first and second passages being in communication with each other.

10. The apparatus of claim 9 , wherein the output of the speed-augmenting power transfer device and the rotor shaft are substantially coaxial.

11. The apparatus of claim 1 , wherein the speed-augmenting power transfer device provides a speed ratio of about 16:1.

12. An aircraft engine comprising:
a bladed rotor comprising a hub and an electrical device configured to carry out a function associated with the rotor;
a rotor shaft coupled to the bladed rotor, the rotor shaft being coupled to a turbine shaft of the engine via a speed-reducing power transfer device;
a speed-augmenting power transfer device having an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device; and
an electric generator disposed in the hub of the bladed rotor and axially coinciding with the bladed rotor, the electric generator being coupled to the output of the speed-augmenting power transfer device, the electric generator being electrically coupled to the electrical device of the rotor.

13. The engine of claim 12 , wherein the output of the speed-augmenting power transfer device outputs rotational motion in a direction opposite that of the rotor shaft.

14. The engine of claim 12 , wherein the speed-augmenting power transfer device comprises a two-stage epicyclic gear train wherein a first stage of the epicyclic gear train has a star arrangement having a fixed carrier and a second stage of the epicyclic gear train has a planetary arrangement having a fixed ring.

15. The engine of claim 12 , wherein the electrical device associated with the rotor comprises one or more of a rotor de-icing system and a pitch control system.

16. The engine of claim 12 , wherein the bladed rotor comprises a propeller.

17. A method of generating electrical power for powering an electrical device for carrying out a function associated with a bladed rotor driven by a gas turbine engine, the method comprising:
driving a rotor shaft coupled to the bladed rotor via a speed-reducing power transfer device using a turbine shaft of the gas turbine engine;
receiving input rotational motion from the rotor shaft coupled to the bladed rotor;
augmenting an input rotation speed of the input rotational motion to produce an output rotational motion having an output rotation speed higher than the input rotation speed;
generating, using an electric generator disposed in a hub of the bladed rotor and axially coincident with the bladed rotor, electrical power from the output rotational motion at the output rotation speed and
delivering the electrical power to the electrical device associated with the bladed rotor.

18. The method of claim 17 , wherein the output rotational motion is in a direction opposite that of the input rotational motion.

Assignees

• Pratt & Whitney Canada

Inventors

• Mitrovic Lazar
• Ullyott Richard

Classifications

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64C11/44 Primary

  electric · CPC title

• F16H3/666

  with intermeshing orbital gears (F16H3/663 takes precedence) · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title