Trunnion retention for a turbine engine
AssigneeGeneral Electric Company
InventorsBrandon Wayne Miller, Ian Francis Prentice, Daniel Alan Niergarth
Life of this patent
Estimating the term…
Abstract
A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
Claims10
A fan for a gas turbine engine, the fan comprising:
- a fan blade;
- a trunnion mechanism comprising a trunnion and a primary attachment system, the fan blade attached to the trunnion;
- a disk having a generally annular shape and comprising a disk segment, the disk segment having a collar, the trunnion extending at least partially through the disk segment and attached to the disk segment using the primary attachment system;
- a retention member attached to the collar of the disk segment and including a means for catching the trunnion should the primary attachment system fail;
- and
- wherein the trunnion mechanism defines a radial direction and a circumferential direction, wherein the trunnion includes a platform for attachment to the fan blade, wherein the platform of the trunnion includes an outer surface defining a first recess extending generally along the circumferential direction, and wherein the means for catching the trunnion included with the retention member is second recess defined by an inner surface of the retention member extending along the circumferential direction and at least one retention feature positioned at least partially in the first recess and the second recess.
A fan for a gas turbine engine comprising:
- a fan blade;
- a trunnion mechanism comprising a trunnion and a primary attachment system, the trunnion including a platform for attachment to the fan blade, the platform having an outer surface;
- a disk having a generally annular shape and comprising a disk segment, the trunnion extending at least partially through the disk segment and attached to the disk segment using the primary attachment system;
- a retention ring having a generally annular shape and comprising a retention member defining an auxiliary support channel with the outer surface of the platform of the respective trunnion;
- and
- at least one retention feature positioned in the auxiliary support channel.
A gas turbine engine comprising:
- a core engine;
- and
- a variable pitch fan in mechanical communication with the core engine, the fan including:
- a fan blade;
- a trunnion mechanism comprising a trunnion and a primary attachment system, the fan blade attached to the trunnion;
- a disk having a generally annular shape and comprising a disk segment, the disk segment having a collar, the trunnion extending at least partially through the disk segment and attached to the disk segment using the primary attachment system;
- a retention member attached to the collar of the disk segment and including a means for catching the trunnion should the primary attachment system fail;
- and
- wherein the trunnion mechanism defines a radial direction and a circumferential direction, wherein the trunnion includes a platform for attachment to the fan blade, wherein the platform of the trunnion includes an outer surface defining a first recess extending generally along the circumferential direction, and wherein the means for catching the trunnion included with the retention member is a second recess defined by an inner surface of the retention member extending along the circumferential direction and at least one retention feature positioned at least partially in the first recess and the second recess.
Dependencies are inferred from the claim text.