Pratt-whitney Canada Corp

Hugues Pellerin

An aircraft fluid control valve is provided that includes a sleeve, a cap, first and second pistons, and first and second springs. The sleeve includes first and second inner chambers. Fluid inlet and outlet ports are disposed in the first sleeve wall. A high pressure reference port is in fluid communication with the base end and a low pressure reference port is in communication adjacent the cap end. The first piston has a center post, a base flange, and a piston head. The piston head is attached to the center post. The second piston (SP) has a SP center flange and a SP side wall. The SP side wall extends axially between a base end and a cap end. The first spring is disposed between the SP center flange and the cap. The second spring is disposed between the PH base flange and the SP center flange.

Multi-function fluid control valve

A rotating component assembly of a gas turbine engine of an aircraft including a first rotating component, a second rotating component located at an external surface of the first rotating component, and a retention assembly configured to axially retain the second rotating component relative to the first rotating component. The retention assembly includes a cup installed to the first rotating component configured to axially abut the second rotating component and one or more external retaining rings installed to the first rotating component to axially retain the cup and the second rotating component. One or more washers are installed radially between the cup and the one or more external retaining rings, and one or more internal retaining rings installed to the cup to axially retain the one or more washers relative to the cup.

Retaining ring centrifugal growth limiter

A fluid system for an aircraft engine can include a pumped fluid circulation circuit including a fluid tank, the fluid circulation circuit configured to circulate a fluid through at least a part of the aircraft engine and means, in the fluid circulation circuit, for selectively directing the fluid of the fluid circulation circuit as a function of a pressure of fluid in the fluid circulation circuit to one of: a part of the aircraft engine, and a fluid bypass in the fluid circulation circuit that is fluidly upstream of the part.

Bypass valve

A multi-adjustable valve for a flow of fluid within a lubrication system is provided, having a longitudinal axis. The valve includes a biasing member, a housing, first and second adjustable pistons, and a spool. The housing has an interior cavity and inlet and outlet fluid ports. The first adjustable piston is disposed in the housing interior cavity and is positionally adjustable within the housing interior cavity and is configured to produce a pressure adjusting effect on the flow of fluid. The biasing member is axially disposed between the second adjustable piston and the spool. The second adjustable piston is disposed within the housing interior cavity and is attached to the first adjustable piston and is positionally adjustable relative to the first adjustable piston, wherein the second adjustable piston, the biasing member, and the spool are configured to produce a pressure regulating effect on the flow of fluid.

Multi-adjustable valve for a lubrication system

An aircraft engine lubrication system for an aircraft engine having a first component (FC) and a second component (SC) is provided. The system includes a lubricant tank (LT), a first pump (FP), a second pump (SP), and a de-aerator (DA). The LT outlet is in fluid communication with a FP inlet. The FP outlet is in fluid communication with a SP inlet. The SP outlet is in fluid communication with a FC inlet and the SC inlet. The SC outlet is in fluid communication with a LT first inlet. The DA gas outlet is in fluid communication with a LT second inlet. The DA liquid outlet is in fluid communication with a SP inlet.

Lubrication system with pump feed from de-aerator

A referenced pressure valve for a fluid system having a housing including: an inner wall enclosing a cavity providing fluid communication between the inlet and the outlet; a rim in the cavity defining a bypass passage circumscribed outwardly by the inner wall and inwardly by the rim, an upstream passage located between an upstream end of the cavity and the rim, and a downstream passage located between the rim and a downstream end of the cavity. A rib extends outwardly from the rim to the inner wall through the bypass passage, and a piston assembly, received within a chamber circumscribed outwardly by the rim, includes a piston movable relative to the rim between a position in which the piston obstructs the flow path at the upstream passage and a position in which the piston is at least partially clear of the path to permit flow along the path.

Pressure referenced valve

A rotating assembly for a gas turbine engine has a balancing ring mounted to a first rotating component having a rotating unbalance about an axis of rotation. The ring is clocked at a circumferential position about the axis to counteract the rotating unbalance. A spacer is axially abutted against the first rotating component to set an axial position of the first rotating component relative to a second rotating component. The balancing ring is locked against rotation relative to the first rotating component in its circumferential position by the dual use spacer.

Balancing ring anti-rotation spacer

An annular parts assembly for mounting onto a shaft of an aircraft engine is provided. The assembly comprises a first annular body having a surface defining a plurality of pulling features extending from a remainder of the surface, the pulling features circumferentially spaced apart on the surface. The assembly comprises a second annular body defining a balancing ring, the balancing ring concentric with the first annular body, the balancing ring having a plurality of protrusions and circumferential spaces between adjacent ones of the plurality of protrusions, the circumferential spaces accommodating the pulling features such that the pulling features of the first annular body and the protrusions intercalate.

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Montreal, Canada

Hugues Pellerin