Pratt-Whitney Canada Corp

Pratt & Whitney Canada Corp.

Hien Duong

Vijay Kandasamy

Jason Nichols

Peter Townsend

Thomas Veitch

Krishna Prasad Balike

Hong Yu

Raman Warikoo

Keegan Lobo

Karan Anand

Alexandre Capron

Gavin Rohiteshwar Kisun

Tammy Yam

Koundinya Upadrasta

Madhusudhan Keragodu

Grigory Rukin

Guiherme Watson

Saurabh S Nair

Rakesh Munlyappa

Tsukasa Yoshinaka

Christopher Chiang

Guilherme Watson

A compressor diffuser for an aircraft propulsion system includes a plurality of diffuser pipes. Each diffuser pipe includes a pipe body. The pipe body extends between and to an inlet end and an outlet end. The pipe body includes a suction lateral wall and a pressure lateral wall. The pipe body further includes a transition body portion. The suction lateral wall and the pressure lateral wall extend between and to the inlet end and the outlet end to form a fluid passage. The fluid passage extends along a center position from a passage inlet at the inlet end to a passage outlet at the outlet end. The fluid passage has a cross-sectional area. The transition body portion is disposed at the outlet end. The transition body portion includes a diverging sub-portion and a converging sub-portion. The cross-sectional area increases in the diverging sub-portion. The cross-sectional area decreases in the converging sub-portion.

Diffuser pipe for an aircraft propulsion system

A vane array structure for a gas turbine engine includes a first platform, a second platform, a plurality of vanes and a flowpath. Each of the vanes extends across the flowpath between the first platform and the second platform. The vanes include a first vane and a second vane disposed longitudinally next to the first vane along the flowpath. The first vane includes a first airfoil and a first recess. The first airfoil extends spanwise between a first end at the first platform and a second end at the second platform. The first airfoil extends chordwise between a leading edge and a trailing edge. The first airfoil extends laterally between a first side and a second side. The first recess projects spanwise into the first airfoil from the first end. The first recess projects chordwise into the first airfoil from the trailing edge.

Vane array structure with recessed stator vanes

A turbine engine assembly includes at least one rotor that has a plurality of blades, each of the blades includes an airfoil that has a pressure side and a suction side that each extend between a leading edge, a trailing edge, a tip and a base. The airfoil has a thickness between the pressure side and the suction side perpendicular to a camber line that varies between the leading edge and the trailing edge. The thickness includes a suction side thickness between the camber line and the suction side and a pressure side thickness between the camber line and the pressure side. A maximum ratio of the pressure side thickness to the suction side thickness is between 3 and 7.

Airfoil thickness profile for minimizing tip leakage flow

An air intake plenum for a gas turbine engine is provided that includes an axial centerline, first and second gas path surfaces, and a plurality of struts. The gas path surfaces are spaced apart from one another and define at least a portion of a plenum interior. The struts extend lengthwise between the gas path surfaces. Each strut has a cross-section geometry. The cross-section geometry has a center, and major and minor axes. The struts are circumferentially spaced apart from one another within the plenum. Each strut is oriented at a clocking angle theta. The clocking angle theta for each respective strut is disposed between the major axis of that strut and a line that intersects the cross-section geometry center of that strut and the axial centerline. At least one strut of the plurality of struts is oriented at a clocking angle theta that is greater than zero.

Air intake plenum with struts

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

A compressor has: a rotor and a stator having vanes, a vane of the vanes having an airfoil extending from a root proximate an inner hub to a radially outer tip, the airfoil having a leading edge, a trailing edge, and a chord extending between the leading edge and the trailing edge to define a chord length, the airfoil having a pressure side surface and a suction side surface, and a fillet disposed at the leading edge of the root of the airfoil and extending between the pressure side surface and the inner hub, the fillet having a radial height being maximum at the leading edge, the radial height decreasing from the leading edge to blend smoothly into a remainder of the airfoil, the fillet extending downstream from the leading edge a chord-wise distance of less than 50% of a chord length of the airfoil on the pressure side surface.

Compressor stator with leading edge fillet

A compressor for an aircraft engine, has: a gaspath extending around a central axis between a radially-inner wall and a radially-outer wall; a rotor having blades circumferentially distributed around the central axis, the blades having airfoils extending from roots to tips along a span and extending from leading edges to trailing edges along a chord, the airfoils extending across the gaspath; grooves defined in an inner face of the radially-outer wall, circumferentially distributed around the central axis, and having groove lengths extending in a first direction having a circumferential component relative to the central axis, the grooves located between the leading edges and the trailing edges of the airfoils; and slots defined in the inner face of the radially-outer wall, circumferentially distributed around the central axis, and having slot lengths extending in a second direction having an axial component relative to the central axis, the slots projecting from the grooves.

Compressor casing with slots and grooves

A strut includes a strut body extending in a radial direction and defining an airfoil shape in cross-section perpendicular to the radial direction. The airfoil shape includes a leading edge and a trailing edge. An extraction inlet is defined through an exterior surface of the strut body, in fluid communication with an internal conduit of the strut body. An injection outlet is defined through the exterior surface of the strut body, in fluid communication with the internal conduit for fluid communication through the internal conduit from the extraction inlet to the injection outlet.

Engine strut flow control

An impeller having a hub, blades extending from the hub along respective spans from roots to tips, the blades extending along respective chords from leading edges to trailing edges, the leading edge of at least one of the blades having a cutback section defining a sweep at the root, the cutback section extending in a spanwise direction from the hub to a location at least about 5% of the span from the hub of the at least one of the blades, and the cutback section extending in a chordwise direction along at least about 5% of the chord of the at least one of the blades.

Impeller with hub sweep

A fluid machine for an aircraft engine has: first and second walls; a gaspath defined between the first wall and the second wall; a rotor having blades rotatable about the central axis; and a stator having: a row of vanes having airfoils including leading edges, trailing edges, pressure sides and suction sides opposed the pressure sides, and depressions defined in the first wall, the depressions extending from a baseline surface of the first wall away from the second wall, a depression of the depressions located circumferentially between a pressure side of the pressure sides and a suction side of the suction sides, the depression axially overlapping the airfoils and located closer to the suction side than to the pressure side, an upstream end of the depression located closer to a leading edge of the leading edges than to a trailing edge of the trailing edges.

Stator with depressions in gaspath wall adjacent leading edges

A casing treatment for a compressor includes one or more cavities in a casing disposed radially outwardly of tips of the compressor rotor blades. A liner is moveable relative to the casing between a first position and a second position. The liner is shaped to add a volume to the tip clearance gap when moving from the second position toward the first position. The liner is displaceable between the first and second positions in coordination with at least the rotation of inlet guide vanes (IGVs) between IGV positions.

Compressor with casing treatment

There is disclosed a fan assembly including a fan rotor including a hub and fan blades. The fan blades have a leading edge and a trailing edge. A fan stator downstream of the fan rotor relative to a direction of an airflow through the fan assembly. The fan stator includes vanes extending between radially inner ends and radially outer ends. A flow recirculation circuit has an inlet downstream of the vanes of the fan stator and an outlet upstream of the vanes. A recirculation rotor has a plurality of airfoils circumferentially distributed around the axis and located in the flow recirculation circuit. The recirculation rotor is rotatable about the axis within the recirculation circuit. A method of operating the fan assembly is also disclosed.

Fan assembly having flow recirculation circuit with rotating airfoils

A compressor diffuser for a gas turbine engine includes diffuser pipes having a tubular body including a generally radial portion, a bend portion and a generally axial portion. The generally axial portion has an exit segment extending parallel to the center axis and terminating at a pipe outlet. The bend portion is disposed radially further from the center axis than the exit segment.

Diffuser pipe with axially-directed exit

A fluid machine has: first and second walls; a gaspath defined between the first wall and the second wall; a rotor having blades rotatable about the central axis; and a tandem having: a first row of first vanes having first airfoils including first leading edges, first trailing edges, first pressure sides and first suction sides opposed the first pressure sides, and a second row of second vanes downstream of the first vanes and having second airfoils including second leading edges, second trailing edges, second pressure sides and second suction sides opposed the second pressure sides, the first vanes being circumferentially offset from the second vanes; and depressions defined in the first wall, a depression of the depressions located circumferentially between a pressure side of the first pressure sides and a suction side of the second suction sides, the depressions axially overlapping the first airfoils and the second airfoils.

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Mississauga, Canada

Hien Duong