Unison ring system for counter rotating propellers

Patent metadata

Field	Value
Publication number	US-9963221-B2
Application number	US-201514692308-A
Country	US
Kind code	B2
Filing date	Apr 21, 2015
Priority date	May 8, 2014
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

Unison ring system includes first unison ring portion, second unison ring portion, and bearing. Second unison ring portion is co-axial with first unison ring portion. First unison ring portion includes first unison ring and first bearing location portion and second unison ring portion includes second unison ring and second bearing location portion. First bearing location portion is co-axial with first unison ring and projects axially from first unison ring, while second bearing location portion is co-axial with second unison ring and projects axially from second unison ring. First bearing location portion includes outwardly opening groove, and second bearing location portion includes inwardly opening groove. First unison ring portion and second unison ring portion positioned with first bearing location portion being concentric with second bearing location portion defining annular cavity there between. Bearing is accommodated in annular cavity, with axial length of annular cavity being greater than axial length of bearing.

First claim

What is claimed is:

1. An aircraft powerplant comprising at least one engine, a first propeller assembly, a second propeller assembly and a unison ring system, the unison ring system comprising:
a first unison ring portion;
a second unison ring portion, the second unison ring portion being co-axial with the first unison ring portion; and
a bearing;
the first unison ring portion comprising:
a first unison ring; and
a first bearing location portion;

the second unison ring portion comprising:
a second unison ring; and
a second bearing location portion;

wherein the first bearing location portion is co-axial with the first unison ring and projects axially from the first unison ring, the second bearing location portion is co-axial with the second unison ring and projects axially from the second unison ring,
the first bearing location portion comprising a radially outwardly opening groove, the second bearing location portion comprising a radially inwardly opening groove,
the first unison ring portion and the second unison ring portion being axially positioned such that the first bearing location portion is concentric with the second bearing location portion thereby defining an annular cavity there between;
the bearing being accommodated in the annular cavity, an axial length of the annular cavity being greater than an axial length of the bearing, and
wherein the bearing comprises a plurality of rolling elements, a radially outwardly facing surface of the first bearing location portion being formed as an inner bearing race, a radially inwardly facing surface of the second bearing location portion being formed as an outer bearing race, and the plurality of rolling elements being disposed between the first bearing location portion and the second bearing location portion, and each of the first and second propeller assemblies comprising a plurality of propeller blades, wherein a pitch of the blades of the first propeller assembly is altered by the first unison ring portion and a pitch of the blades of the second propeller assembly is altered by the second unison ring portion.

2. The aircraft powerplant as claimed in claim 1 , wherein the first propeller assembly rotates in an opposite direction to the second propeller assembly.

3. An aircraft powerplant comprising at least one engine, a first propeller assembly, a second propeller assembly and a unison ring system, the unison ring system comprising:
a first unison ring portion;
a second unison ring portion, the second unison ring portion being co-axial with the first unison ring portion; and
a bearing;
the first unison ring portion comprising:
a first unison ring; and
a first bearing location portion;

the second unison ring portion comprising:
a second unison ring; and
a second bearing location portion;

wherein the first bearing location portion is co-axial with the first unison ring and projects axially from the first unison ring, the first bearing location portion is integrally formed with the first unison ring, and the second bearing location portion is co-axial with the second unison ring and projects axially from the second unison ring,
the first bearing location portion comprising a radially outwardly opening groove, the second bearing location portion comprising a radially inwardly opening groove,
the first unison ring portion and the second unison ring portion being axially positioned such that the first bearing location portion is concentric with the second bearing location portion thereby defining an annular cavity there between;
the bearing being accommodated in the annular cavity, an axial length of the annular cavity being greater than an axial length of the bearing, and
wherein the bearing comprises a plurality of rolling elements, a radially outwardly facing surface of the first bearing location portion being formed as an inner bearing race, a radially inwardly facing surface of the second bearing location portion being formed as an outer bearing race, and the plurality of rolling elements being disposed between the first bearing location portion and the second bearing location portion, and each of the first and second propeller assemblies comprising a plurality of propeller blades, wherein a pitch of the blades of the first propeller assembly is altered by the first unison ring portion and a pitch of the blades of the second propeller assembly is altered by the second unison ring portion.

4. An aircraft powerplant comprising at least one engine, a first propeller assembly, a second propeller assembly and a unison ring system, the unison ring system comprising:
a first unison ring portion;
a second unison ring portion, the second unison ring portion being co-axial with the first unison ring portion; and
a bearing;
the first unison ring portion comprising:
a first unison ring; and
a first bearing location portion;

the second unison ring portion comprising:
a second unison ring; and
a second bearing location portion;

wherein the first bearing location portion is co-axial with the first unison ring and projects axially from the first unison ring, the second bearing location portion is co-axial with the second unison ring and projects axially from the second unison ring, and the second bearing location portion is integrally formed with the second unison ring,
the first bearing location portion comprising a radially outwardly opening groove, the second bearing location portion comprising a radially inwardly opening groove,
the first unison ring portion and the second unison ring portion being axially positioned such that the first bearing location portion is concentric with the second bearing location portion thereby defining an annular cavity there between;
the bearing being accommodated in the annular cavity, an axial length of the annular cavity being greater than an axial length of the bearing, and
wherein the bearing comprises a plurality of rolling elements, a radially outwardly facing surface of the first bearing location portion being formed as an inner bearing race, a radially inwardly facing surface of the second bearing location portion being formed as an outer bearing race, and the plurality of rolling elements being disposed between the first bearing location portion and the second bearing location portion, and each of the first and second propeller assemblies comprising a plurality of propeller blades, wherein a pitch of the blades of the first propeller assembly is altered by the first unison ring portion and a pitch of the blades of the second propeller assembly is altered by the second unison ring portion.

Assignees

• Rolls Royce Plc

Inventors

• Grice Christopher Michael

Classifications

• B64C11/06 Primary

  for variable-pitch blades · CPC title

• B64C11/48

  Units of two or more coaxial propellers · CPC title

• F16C19/24

  for radial load mainly · CPC title

• B64C11/306 Primary

  specially adapted for contrarotating propellers · CPC title