Pratt-Whitney Canada Corp

Pratt & Whitney Canada Corp.

Michel Labbe

Daniel Alecu

Victor Sa Melo

Tibor Urac

Pierre-Yves Legare

Ahmad Cheikhzen

Penny Nicolaidis

Vittorio Bruno

Pierre Gauvin

Darragh McGrath

Sean Powers

Marcin Rejman

Simon Baker-Ostiguy

Alessandro Ciampa

Rose-Elizabeth Banville

Hugo Quintin

Simon Cartier

Ho-Wing Edmund Leung

Edward Dusza

Lukasz Pokrzywa

Steve Fett

Stuart Hodgson

Daniel Poirier

Stephane Gignac

Sebastien Gagne

Cedric Chan Chuen

An apparatus for an aircraft powerplant includes an impeller rotor and a seal runner. The impeller rotor includes a plurality of fluid circuits. Each of the fluid circuits includes a first outlet passage, a second outlet passage and an inlet passage fluidly coupled to the first outlet passage and the second outlet passage in parallel. The seal runner includes a bore, an inner guide surface and an outer land surface. The seal runner extends circumferentially about the axis and radially between the inner guide surface and the outer land surface. The bore is fluidly coupled to the first outlet passage of each fluid circuit. The inner guide surface forms a radial outer peripheral boundary of the bore. The inner guide surface radially diverges away from the axis as the inner guide surface extends axially away from the impeller rotor and to a distal end of the seal runner.

Impeller rotor seal runner with divergent guide surface

An assembly includes a rotating seal land, a seal element, a stationary seal support and a mating plate. The seal element axially overlaps, circumscribes and radially sealingly engages the rotating seal land. The stationary seal support axially overlaps and circumscribes the rotating seal land and the seal element. The stationary seal support includes a support notch, a support shoulder, a support inner interior surface and a support outer interior surface. The support notch projects axially into the stationary seal support from a distal end of the stationary seal support to the support shoulder. The support notch projects radially outward away from an axis into the stationary seal support from the support inner interior surface to the support outer interior surface. The mating plate is seated in the support notch and mounted to the stationary seal support. The mating plate axially contacts the support shoulder and the seal element.

Seal assembly mating plate for aircraft powerplant

An oil filler assembly, has: a filler tube extending from a bottom end to a top end; a non-return valve having a tube side and a tank side; a cap assembly including a cap removably secured to the filler tube and a dipstick projecting from the cap; a vent having an inlet connected to the tank side and an outlet connected to the tube side, the vent defining a flow path bypassing the non-return valve; and a safety valve connected to the vent and having an open configuration in which fluid flow is permitted and a closed configuration in which fluid flow is prevented, the safety valve being engageable by the cap assembly to bias the safety valve in the open configuration when the cap is secured to the top end, the safety valve being in the closed configuration when the cap assembly is detached from the top end.

Filler-cap activated valve in filler-neck oil vent

An oil filler assembly for an aircraft engine, has: a filler tube extending from a bottom end to a top end; a valve having a tube side fluidly connected to the filler tube and a tank side; a cap removably secured to the top end; a dipstick secured to the cap and extending into the filler tube; and a piston secured to the dipstick, the piston having: a sealing configuration in which the piston sealingly engages the filler tube to fluidly disconnect the top end from the valve, the piston being in the sealing configuration when the cap is secured to the top end of the filler tube; and a venting configuration in which the piston permits fluid communication between the top end and the valve, the piston being in the venting configuration when the cap is moved away from the top end of the filler tube.

Oil filler tube assembly for aircraft engine

A method of monitoring a sealing component of a gas turbine engine, comprising: collecting oil leaked from the component; detecting a volume of the collected oil upstream of an oil return path of the gas turbine engine; and signalling for inspection of the component when the volume of the collected oil exceeds a threshold volume. Also disclosed is an oil leakage monitoring system for a gas turbine engine, comprising: one or more sealing components to be lubricated by oil; a valve downstream of the one or more components and fluidly connected to an oil system; a reservoir downstream of the one or more components to collect oil, the reservoir upstream of the valve; and a volume measurement device configured to detect the oil collected in the reservoir, and to signal for inspection of the one or more components when the oil collected in the reservoir exceeds a threshold volume.

Oil leakage monitoring system

The contact seal assembly for a shaft of a gas turbine engine includes a carbon seal mounted in a fixed position within a seal housing, and an annular seal runner adapted to be connected to the shaft of the gas turbine engine and rotatable relative to the carbon ring segments. The seal runner is disposed adjacent to and radially inwardly from the carbon ring segments to form a contact interface between the seal runner and the carbon ring segments which forms a substantially fluid tight seal. The seal runner includes a coolant scoop disposed in a cavity defined by the seal housing, a first slinger disposed between the coolant scoop and the contact interface, a second slinger disposed between the first slinger and the contact interface, and a coolant collector groove disposed between the first slinger and the second slinger.

Seal runner and method

There is disclosed an aircraft engine having: an engine shaft; a first transmission shaft in driving engagement with the engine shaft and a second transmission shaft concentric with the first transmission shaft and in driving engagement with the first transmission shaft, the second transmission shaft drivingly engageable to an engine accessory, the first and second transmission shafts rotatable about an axis; and at least two axially spaced apart annular ring seals disposed radially between the first and second transmission shafts, the at least two annular ring seals biased against both of the first and second transmission shafts.

Shaft assembly for aircraft engine

A controlled gap radial oil sealing assembly in a gas turbine engine having a centre rotational axis defining an axial direction, the controlled gap radial sealing assembly comprises a seal element located around a cooperating seal runner and sized to define a controlled sealing gap between them, the seal runner having an axial length extending beyond an axial width of the seal element into an oiled region of the engine. A first annular surface radially outwardly spaced from and extending substantially along the axial length of the seal runner, the first annular surface sealingly cooperating with a seal housing of the seal element, and a second annular surface axially extending to overlap at least a portion of the first annular surface, the second annular surface radially outwardly spaced from the first annular surface relative to the center axis.

Sealing assembly for a gas turbine engine

The seal runner has an annular body secured to a rotating shaft of the gas turbine engine whereas ring segments are secured to a case of the gas turbine, with the seal runner having a radially-outer surface having a contacting portion adapted to rubbingly receive ring segments of the contact seal assembly during use, the seal runner having a radially-inner surface opposite to the radially-outer surface. The method includes rotating the seal runner relative to the ring segments and generating heat from the rubbing engagement therebetween; and feeding a flow of cooling fluid against the radially-inner surface to cool the seal runner from said generated heat including maintaining a pool of cooling fluid having a given depth against the radially-inner surface.

Internally cooled seal runner and method of cooling seal runner of a gas turbine engine

A seal and bearing assembly of a gas turbine engine having an engine case with a cooling fluid nozzle located between a bearing outer ring and ring segments, and a rotary shaft for rotation in the engine case around a main axis, the seal and bearing assembly can be assembled by positioning the engine case and the rotary shaft in axial alignment, and axially moving the engine case relative to the rotary shaft including moving the bearing outer ring across the axial location of the runner portion and into an assembled condition. The rotary shaft having mounted thereon a bearing inner ring and a runner assembly having a runner portion, a sleeve portion being concentric and radially internal to the runner portion, and a cooling fluid passage having a radial segment leading from an outgoing segment to a returning segment extending in a direction leading back toward the bearing inner ring.

Seal and bearing assembly for a gas turbine engine and method of assembling same

A tank defines an inner cavity and at least an opening. A filler tube device comprises a tube passing through the opening in the tank, the tube forming a joint with at least one degree of freedom with the tank such that the tube is displaceable relative to the tank. The tube has an open end in the inner cavity of the tank, and an opposite open end outside of the tank, whereby the tube defines a passage for filling the tank. A sealing component is in the inner cavity of the tank, the sealing component configured for collaborating with the open end of the tube when the tube is moved into engagement therewith to close the open end of the tube inside the tank in a protective position.

Tank and filler tube device with protective arrangement

An integral tandem bearing assembly for supporting a main shaft in a gas turbine engine is provided. The tandem bearing assembly comprises two bearing assemblies connected by integrated inner ring.

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Montreal, Canada

Michel Labbe