Pratt-whitney Canada Corp

Ivan Sidorovich Paradiso

Daniel Alecu

Domenico Di Florio

Louis Duranleau-Hendrickx

Michael Andrew Fryer

Martin John Dobson

Marc Lavoie

Oleg Iskra

Tibor Urac

Gabriel Naccache

Laslo Diosady

David Koo

Jean-Francois Caron

Pouya Mottaghian

Liam Xue

Michael Fryer

An oil system for an aircraft engine includes an oil tank, an engine component in fluid communication with the oil tank, a scavenge pump, and a manifold disposed inside the scavenge pump housing and fluidly connecting the engine component to the scavenge pump. The manifold includes a fluid passage, extending between a manifold inlet and a manifold outlet, and including a first bend, upstream, and a second bend. The first bend includes an oil isolator and the second bend includes an air offtake. The oil isolator separates an oil fraction from the fluid received from the engine component at the first bend and directs the oil fraction to the scavenge pump, and the air offtake separates an air fraction from the fluid at the second bend and directs the air fraction away from the scavenge pump.

Aircraft engine fluid separation system and method

A deaeration rotor for an aircraft engine lubrication system comprising: an internal ring about an axis having a radially outer internal ring surface defining an inner boundary of an inner passage of the deaeration rotor; an external ring about the axis having a radially inner external ring surface defining an outer boundary of an outer passage of the deaeration rotor; a disc about the axis radially between the internal ring and the external ring, the disc having a radially inner disc surface defining an outer boundary of the inner passage and a radially outer disc surface defining an inner boundary of the outer passage; and blades circumferentially spaced from one another relative to the axis extending in the outer passage from at least one of the external ring and the disc, the blades located radially inward of an annular portion of the outer passage immediately downstream of the blades.

Dynamic deaeration system

Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

Emergency power unit for electric aircraft

A gas turbine engine rotor assembly is provided that includes a shaft, a rotor, and a seal assembly. The seal assembly is configured to seal between a first and second rotor compartments on opposite sides of the seal assembly. The seal assembly includes a seal groove and a split piston ring seal. The split piston ring seal is configured such that air in the first rotor compartment at Pproduces a radial force acting on the split piston ring seal, and air in the second rotor compartment at Pproduces a second force acting on the split piston ring seal, wherein the second force is directed radially inward and the first force is directed radially outward, and the second force is greater than the first force.

Split piston ring seal for a rotating assembly and method of sealing

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a case, a housing, a component and a spring element. The case includes an aperture that extends axially along an axis through the case. The housing is attached to the case with a cavity formed by and axially between the housing and the case. The component includes a base and a projection. The base is disposed within the cavity and axially engages the case. The projection projects out from the base and axially through the aperture. The spring element is disposed within the cavity. The spring element is compressed axially between and engages the base and the housing.

Joint between gas turbine engine components with a spring element

The de-aerator can be used to separate air from oil in an aircraft engine lubrication system. The de-aerator can include a swirler cavity extending circumferentially around axis and axially between a proximal wall and a distal wall, a separation path dividing within the swirler cavity into a radially outer oil segment leading to an oil outlet and a radially inner air segment leading to an air outlet, and a swirling conduit portion having a length turning around the axis upstream of an opening in the proximal wall along the separation path.

Deaerator for aircraft engine and associated method of operation

A fluid cooler for installation in a bypass duct of a turbofan gas turbine engine and associated methods are provided. The fluid cooler includes an inlet duct, a heat exchanger and an outlet duct. The inlet duct includes an inlet protruding into the bypass duct to receive a portion of the bypass air into the inlet duct. The heat exchanger is in fluid communication with the inlet duct. The heat exchanger facilitates heat transfer between a fluid and the portion of bypass air received into the inlet duct. The heat exchanger defines a general flow direction for the portion of bypass air that is different from the main flow direction of bypass air inside the bypass duct. The outlet duct conveys the portion of bypass air from the heat exchanger back to the bypass duct.

Fluid cooler installation and method for turbofan engine

A deaeration system for an engine lubrication system, the deaeration system comprising: a deaeration rotor rotatable about an axis and including: a rotor inlet extending circumferentially around the axis, a first and a second rotor outlet, a first rotor passage in fluid communication between the rotor inlet and the first rotor outlet, and a second rotor passage in fluid communication between the rotor inlet and the second rotor outlet in parallel to the first rotor passage; and a deaeration conduit including: a conduit inlet, a splitter downstream of the conduit inlet relative to a flow of lubricant through the deaeration conduit, a first conduit outlet and a second conduit outlet downstream of the splitter, the first conduit outlet in fluid communication with the rotor inlet, the conduit inlet having a curved portion extending away from the splitter.

Deaeration conduit

A seal assembly for an aircraft engine includes a first seal having an upstream end exposed to a first pressure area, and a downstream end exposed to a second pressure area, the first seal at least partially defining an intermediate pressure area and a chamber being fluidly connected to the second pressure area and to the intermediate pressure area through passages defined in the first seal, the chamber allowing for a mixing of a first portion of a stream of air with air from the second pressure area, and a second seal connected to the first seal, the second seal biasing the first portion of the stream of air toward the passages, and allowing a second portion of the stream of air from flowing therethrough toward the second pressure area. A method of flowing air through an aircraft seal assembly is also described.

Seal assembly for aircraft engine

An orifice pack is provided for delivering pressurized air to a compressor bleed valve of a gas turbine engine. The orifice pack has a diffusion chamber in serial flow communication with a tapering passage and a first outlet passage for venting a first portion of the pressurized air from the diffusion chamber. A second outlet passage branches off from the diffusion chamber at an axial location between the inlet and the tapering passage. The second outlet passage is fluidly connected to the compressor bleed valve for directing a second portion of the pressurized air from the diffusion chamber to the compressor bleed valve.

Orifice pack for compressor bleed valve

Methods and systems for filtering pressurized air used to control a compressor bleed valve of a gas turbine engine are provided. One method comprises receiving the pressurized air in a conduit via an inlet of the conduit, releasing a first portion of the pressurized air out of the conduit via an outlet of the conduit, releasing a second portion of the pressurized air from the conduit via a port disposed between the inlet and the outlet of the conduit, directing the second portion of the pressurized air from the port to a filter along an upward flow path, filtering the second portion of the pressurized air using the filter, and directing the second portion of the pressurized air from the filter toward the compressor bleed valve.

Air filtration system and method for compressor bleed valve

The gas turbine engine can have a pneumatic actuator; an intake device secured to a gas path wall delimiting the gas path, the intake device having a tubular body protruding from the gas path wall into the gas path and an inlet aperture formed in the tubular body, the inlet aperture spaced-apart from the gas path wall and facing downstream relative a flow orientation of the gas path, the intake device having an internal conduit extending from the inlet aperture, along the tubular body, to an outlet across the gas path wall; and a fluid line fluidly connecting the outlet of the intake device to the pneumatic actuator.

Intake device for gas turbine engine

A gas turbine engine, has: a compressor; a turbine having a rotor; and an inertial particle separator located upstream of the turbine downstream of the compressor, the inertial particle separator having: an intake conduit in fluid flow communication with the compressor and defining an elbow, a splitter, a leading edge of the splitter located downstream of the elbow, the splitter located to divide a flow into a particle flow and an air flow, and an inlet conduit and a bypass conduit located on respective opposite sides of the splitter, the inlet conduit receiving the air flow, the inlet conduit in fluid flow communication with a cavity containing the rotor for cooling the rotor of the turbine section, the bypass conduit receiving the particle flow, the bypass conduit in fluid flow communication with an environment outside the gas turbine engine while bypassing the cavity containing the rotor.

Inertial particle separator for a turbine section of a gas turbine engine

A duct for a gas turbine engine, the duct has a wall defining a flow passage for an airflow, the wall defining a baseline surface, the duct comprising an off-take port for drawing a portion of the airflow out of the duct, the off-take port including a projected portion projecting away from the baseline surface into the flow passage, a conduit opening defined within the projected portion for receiving the portion of the airflow, and an off-take conduit communicating with the conduit opening for directing the portion of the airflow away from the duct, the projected portion having a hump upstream of the conduit opening relative to a direction of the airflow and a scoop downstream of the opening relative to the direction of the airflow.

Growing community of inventors

Toronto, Canada

Ivan Sidorovich Paradiso