Pratt-whitney Canada Corp

Alexandre Capron

Hien Duong

Peter Townsend

Karan Anand

Tammy Yam

Krishna Prasad Balike

Sylvain Claude

Ali Azmi

Bernard Chow

Prakul Mittal

Anthony Robert Bruni

Juan Ignacio Ruiz-Gopegui Gonzalez

Ignacio Javier Ucin Jarne

César Carlos Valbuena Merino

Cesar Valbuena Merino

Device and methods for guiding bleed air in a turbofan gas turbine engine are disclosed. The devices provided include louvers and baffles that guide bleed air toward a bypass duct of the turbofan engine. The louvers and baffles have a geometric configuration that promotes desirable flow conditions and reduced energy loss.

Devices and methods for guiding bleed air in a turbofan engine

An aircraft engine, has: an upstream stator having upstream stator vanes distributed about a central axis; and a downstream stator having downstream stator vanes distributed about the central axis, the downstream stator located downstream of the upstream stator, a number of the upstream stator vanes different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes; and a second vane differing from the first vane by a geometric parameter, the geometric parameter causing the second vane to have one or more of: a stiffness greater than that of the first vane, and a major portion of a leading edge of the second vane circumferentially overlapped by another one of the upstream stator vanes.

Aircraft engine with stator having varying geometry

An aircraft engine, has: an upstream stator having upstream stator vanes circumferentially distributed about a central axis; and a downstream stator having downstream stator vanes circumferentially distributed about the central axis, the downstream stator located downstream of the upstream stator relative to an airflow flowing within a core gaspath of the aircraft engine, a number of the upstream stator vanes being different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane made of a first material, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes, and a second vane made of a second material having a greater stiffness, strength, and/or ductility than that of the first material, a major portion of a leading edge of the second vane exposed via a spacing defined between two of the upstream stator vanes.

Aircraft engine having stator vanes made of different materials

A shroud configured to be disposed around an impeller of a centrifugal compressor, the shroud has a wall extending circumferentially around a central axis, the wall having an inner face oriented toward a gaspath and an outer face opposed to the inner face, a bleed slot defined in the wall and extending along at least a portion of a circumference thereof, the bleed slot defining a bleed direction from the inner face and away from the gaspath, the bleed direction at the inner face of the wall being either parallel to the central axis or oriented toward the central axis. A method of manufacturing a shroud is provided.

Impeller shroud and method of manufacturing thereof

A stator that has vanes extending between a first end and a second end along a span and from a leading edge to a trailing edge along a chord length, the vanes having a first end portion extending from the first end to about 30% of the span to a first location, a chord ratio of the chord length at the first end to the chord length at the first location greater than or equal to 1.1, a throat ratio of a width of a throat between two adjacent vanes at the first location to a width of the throat at the first end is greater than or equal to 1.3, a sweep angle difference between a maximum sweep angle of the leading edge along the first end portion and a minimum sweep angle of the leading edge along the first end portion is at least 15 degrees.

Compressor stator

A shroud configured to be disposed around an impeller of a centrifugal compressor, the shroud has a wall extending around a central axis of the centrifugal compressor, the wall having an inner face oriented toward a gaspath and an outer face oriented away from the gaspath, a slot extending all around the central axis and from the inner face to the outer face of the wall, bridges secured to the wall, the bridges circumferentially distributed around the central axis and spanning across the slot, the bridges extending from roots to tips, the tips of the bridges circumferentially offset from the roots relative to the central axis.

Growing community of inventors

Toronto, Canada

Alexandre Capron