Pratt-Whitney Canada Corp

Dave Menheere

Eduardo David Hawie

Daniel Alecu

Nathan Tomes

Tyler Richardson

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 combustor assembly for a turbine engine includes a combustor assembly where a first combustion space is defined between a first closed end of a combustion chamber and a first piston, a second combustion space is defined between a second closed end of the combustion chamber and a second piston and a center combustion space is defined between the first piston and the second piston. An air inlet assembly provides for communication of inlet air to the first combustion space, the second combustion space and the center combustion space. First, second and center injectors are provided to inject fuel into a corresponding one of the first combustion space, the second combustion space, and the center combustion space. An exhaust outlet communicates an exhaust gas flow generated in each of the first combustion space, the second combustion space and the center combustion space to a turbine section.

Constant volume combustor for gas turbine engine

Gas turbine engines include a compressor section configured to compress a core flow and a combustor section having a combustor that is arranged downstream from the compressor section along a path of the core flow. A turbine section is arranged downstream from the combustor along the path of the core flow, and includes a plurality of first vanes arranged at an outlet of the combustor, with at least one first vane of the plurality of first vanes having an internal vane path. A compressor diffuser is arranged to direct the core flow from the compressor section through the internal vane path. The path of the core flow, in a flow direction, passes through the compressor section, the compressor diffuser, the internal vane path, the combustor, and then between the first vanes of the plurality of first vanes to enter the turbine section.

Integrated axial compressor diffuser and high pressure turbine vane assembly

The pump can have a support having a guide extending around an axis, a radial position of the guide relative the axis varying around the axis, and a first oil passage formed in the support; a rotary assembly mounted to the support via support bearings, and rotatable around the axis, the rotary assembly having a second oil passage and a cylinder, the cylinder extending radially relative the axis, an inlet port fluidly connecting the first oil passage to the cylinder, and an outlet port fluidly connecting the cylinder to the second oil passage, and a piston slidingly mounted in the cylinder, a radially-outer end of the piston further slidingly engaged with the guide.

Oil pump for gas turbine engine and associated method of pumping oil

A gas turbine engine includes a turbine for driving a shaft to in turn drive a rotor. A combustor receives compressed air, and combusts the compressed air. The shaft is supported by at least one bearing. An oil delivery system is associated with the at least one bearing including an oil scoop rotating with the at least one shaft and a stationary oil jet provided with a source of lubricant. A mixed fluid chamber is within the shaft. The mixed fluid chamber is connected to an air exit. There further is an oil chamber radially outward of the mixed fluid chamber. The oil chamber is connected to the at least one bearing.

Gas turbine engine oil scoop with air separator

Gas turbine engines include a compressor section having an impeller configured to compress a core flow. A combustor section having a combustor is arranged downstream from the compressor section along a path of the core flow. A turbine section is arranged downstream from the combustor section along the path of the core flow, with the turbine section having a plurality of first vanes arranged at an outlet of the combustor and at least one first vane of the plurality of first vanes includes an internal vane path. The path of the core flow, in a flow direction, passes through the impeller of the compressor section, the internal vane path internal to the first vane, the combustor, and then between external surfaces of the plurality of first vanes to enter the turbine section.

Integrated centrifugal compressor diffuser and high pressure turbine vane assembly

The centrifugal compressor can have a shroud engaged to a case via a plurality of circumferentially interspaced slots and lugs, the slots extending in at least one of a radial direction and an axial direction relative to a rotation axis of the compressor, the lugs slidingly received in a corresponding slot and configured for sliding in the slot in response to thermal growth of the case relative to the shroud.

Shroud assembly for centrifugal compressor and method

The shroud can have a wall curved radially outwardly from an axially oriented inlet to an outlet end, a structural member having a flange at the outlet end, and an insert of Greek Ascoloy exposed on an inner face of the wall.

Growing community of inventors

Norval, Canada

Dave Menheere