Pratt-whitney Canada Corp

Nathan Tomes

David Gagnon-Martin

Antwan Shenouda

Thomas Veitch

Dave Menheere

Bruce Fielding

Steven Strecker

Tyler Richardson

Steve Strecker

A casing for a gas turbine engine, including: a plurality of layers of a structural material, wherein each layer of the plurality of layers of the structural material are separated from each other by at least one layer of an impact absorbing material, the at least one layer of impact absorbing material being different from the structural material and the impact absorbing material having a radial thickness that is greater than a radial thickness of the structural material, wherein the plurality of layers of the structural material comprises at least three layers.

Containment ring for gas turbine engine

A casing for a gas turbine engine, including: an inner ring portion; an intermediate layer of honeycomb and/or foam secured to a radially outward surface of the inner ring portion; an outer ring portion secured to a radially outward surface of the layer of honeycomb and/or foam; and a composite containment belt secured to a radially outward surface of the outer ring portion, the composite containment belt having a central portion integrally formed with a forward ring portion and an aft ring portion, the composite containment belt including at least one single woven belt wound about the outer ring portion, the at least one single woven belt including a plurality of continuous fibers, wherein a first portion of the plurality of continuous fibers are at arranged at an angle of 45/−45 degrees or greater with respect to a circumferential direction of the composite containment belt in the central portion and a second portion of the plurality of continuous fibers are at arranged at an angle of less than 45/−45 degrees with respect to the circumferential direction of the composite containment belt in the forward ring portion and the aft ring portion.

An aircraft powerplant apparatus includes a rotating structure configured to rotate about an axis. The rotating structure includes a bladed rotor, a first component, a second component, a first balancing mass, a second balancing mass and a spring element. The first balancing mass and the second balancing mass are configured to rotationally balance the rotating structure about the axis. The first component include a plurality of first component teeth. The second component includes a plurality of second component teeth. The first balancing mass includes a first mass ring and a plurality of first mass teeth. The first mass teeth are meshed with the first component teeth. The second balancing mass includes a second mass ring and a plurality of second mass teeth. The second mass teeth are meshed with the second component teeth. The spring element is engaged with the first balancing mass and the second balancing mass.

In situ balancing mass(es) for aircraft powerplant

A casing for a gas turbine engine, including: at least one axial hairpin feature located proximate to either a forward flange or a rearward flange; and a central connecting portion extending from the at least one axial hairpin feature, the at least one axial hairpin feature being located between the central connecting portion and one of the forward flange or a rearward flange.

A casing for a gas turbine engine, including: at least one axial hairpin feature located proximate to either a forward flange or a rearward flange of the casing; and a central connecting portion extending from the at least one axial hairpin feature, the at least one axial hairpin feature being located between the central connecting portion and one of the forward flange or a rearward flange, the central connecting portion including a plurality of features that extend from the at least one axial hairpin features, each feature of the plurality of features has a pair of radially extending portions, each pair of radially extending portions are connected to each other by an upper portion and one of each pair of the radially extending portions of one of the plurality of features is connected to another one of a pair of radially extending portions of an adjacent feature of one of the plurality of features by a lower portion, wherein the upper portion is radially outward with respect to the lower portion such that a plurality of troughs and peaks are defined by the plurality of features.

A casing for a gas turbine engine, including: an inner ring portion that provides a gaspath and structural features of the casing; an outer ring portion; and an inner ceramic layer arranged radially between the inner ring portion and the outer ring portion, wherein the inner ceramic layer is bonded directly to an inner surface of the outer ring portion such that the combination of the outer ring portion and the inner ceramic layer provide both containment and primary structural features of the casing.

A mounting arrangement for mounting a rotary engine to an aircraft structure, wherein the engine has a three orthogonal axes comprising: a roll axis; a pitch axis; and a yaw axis. The mounting arrangement comprises: one-degree-of-freedom links with reaction axes passing through the roll axis. A separate roll constraint has a moment reaction about the roll axis to decouple the torque roll mode from the other one-degree-of-freedom links.

Mount arrangement for torque roll vibration isolation

A damping device for connecting a bearing housing to a bearing outer race is provided. The damping device may permit an allowable range of radial movement of the bearing. The damping device has an elastomeric body connected to one of the bearing outer race and the bearing housing and a cover portion connected to the other one of the bearing outer race and the bearing housing. It also has two or more deformable fluid chambers fluidly connected to one another via at least one orifice and in which fluid is encapsulated. The damping device may dissipate at least partially vibrations travelling between the bearing housing and the bearing outer race by compressing its elastomeric body and by discharging fluid from one fluid chamber to another. There may be a plurality of such damping devices disposed circumferentially about the bearing outer race.

Damping device for a bearing housing

A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.

Low profile vane retention

A connector for multi-phase conductors. The connector includes conductors for conducting multi-phase currents, and at least one conductive plate corresponding to each phase. Each conductive plate defines apertures for the conductors to pass through, there being at least one aperture in each conductive plate for each respective conductor. Each conductive plate includes at least one connecting member for forming an external electrical connection. Each conductor passes through a respective aperture of each conductive plate. Each conductor is selectively coupled to form electrical connection only to a conductive plate corresponding to the respective phase of the conductor.

Growing community of inventors

Toronto, Canada

Nathan Tomes