Pratt-whitney Canada Corp

Other

Hanwha Aerospace Co., Ltd.

Pratt & Withney Canada Corp.

Guy Lefebvre

Remy Synnott

Eric Durocher

John Pietrobon

Christopher Gover

Philippe Savard

Francois Doyon

Rene Paquet

Jocelyn Bisson

Nicolas Grivas

Franco Di Paola

Richard Bouchard

Denis Leclair

François Doyon

Hervé Turcotte

Vincent Paradis

Ian Alexander MacFarlane

Lorenzo Sanzari

Gavin Rohiteshwar Kisun

René Paquet

Jacob Biernat

Claude Giardetti

Patrick L'Esperance

Gabriel Emard-Parent

Eugene Gekht

Daniel Lecuyer

Gabriel Naccache

Samuel Panero

Yves Martin

Michael Paolucci

Gerard Theriault

Young Jung Joo

Eric Langevin

David Pyra

Michael Fryer

Jagdeep Singh Jhinger

Ruoxin Huang

John Walter Pietrobon

An aircraft engine, has: a turbine; a scroll case connected to a source of combustion gases and to the turbine, and a conduit extending around a central axis; a bearing housing including a support flange; a turbine support case secured to the bearing housing, the turbine support case having spokes extending through the scroll case and radially supported by the bearing housing, a spoke of the spokes having a distal end secured to the support flange via one or more fasteners; and ribs secured to the support flange and distributed around the central axis, a rib of the ribs circumferentially and axially overlapping the distal end of the spoke, the rib having a rib face in radially opposed facing relationship to a spoke face of the spoke, a projection of the rib face in a circumferential direction relative to the central axis intersecting the spoke face.

Turbine support case supported by stopping ribs

A compressor assembly has: an impeller rotatable about a central axis, the impeller mounted on a shaft; a bearing housing extending around the central axis and radially supporting the shaft; and a diffuser downstream of the impeller, the diffuser having: an annular member extending circumferentially around the central axis, vanes circumferentially distributed around the central axis and protruding from one of the annular member and the bearing housing, the vanes extending from bases at the one of the annular member and the bearing housing to tips at the other of the annular member and the bearing housing, and lug and slot connections defined between the annular member and the bearing housing to secure the annular member to the bearing housing.

Aircraft engine including diffuser secured to a bearing housing

A mechanical dissuasion device includes a sleeve body forming a cylindrical body portion, a first tab, a second tab, and opposing fastener mounts. The cylindrical body portion extends circumferentially about a center axis between and to a first circumferential end and a second circumferential end. The cylindrical body portion extends axially between and to a first axial end and a second axial end. The first tab is disposed at the first axial end and extends radially inward from the cylindrical body portion. The second tab is axially spaced from the first axial end and the second axial end and extends radially inward from the cylindrical body portion. The opposing fastener mount portions include a first fastener mount portion and a second fastener mount portion. The first fastener mount portion is disposed at the first circumferential end. The second fastener mount portion is disposed at the second circumferential end.

Mechanical dissuasion device for a fluid assembly joint

A turbine exhaust case has an inner ring structurally connected to an outer ring via a plurality of struts. An outer flange projects outwardly from the outer case. The outer flange is made of a material different from that of the outer case and includes a ring portion having an inner diameter surface joined to an outer diameter surface of the outer case at a first axial location corresponding to a junction of a leading edge of the plurality of struts and the outer case. The outer flange further includes a tubular portion projecting axially from the ring portion to a second axial location disposed upstream of the struts, and an annular mounting portion projecting outwardly from an outer surface of the tubular portion at the second axial location.

Turbine exhaust case structural flange

A gas turbine engine includes a turbine section, a turbine case, an inner case, and a damping seal baffle. The turbine section extends along a rotational axis of the gas turbine engine. The turbine case includes a cantilevered inner wall. The cantilevered inner wall extends circumferentially about the rotational axis. The cantilevered inner wall extends between and to an upstream axial end and a downstream axial end. The upstream axial end is disposed at and downstream of the turbine section. The cantilevered inner wall forms a first sealing surface and a second sealing surface. The inner case extends and the damping seal baffle extend circumferentially about the rotational axis. The damping seal baffle is mounted to the inner case. The damping seal baffle is disposed in contact with one or both of the first sealing surface or the second sealing surface.

Turbine case structure for an aircraft propulsion system engine

An aircraft engine, comprising a thermal engine, an axial turbine having a turbine inlet, and an exhaust assembly fluidly connecting the thermal engine to the axial turbine. The exhaust assembly includes a housing and a deflector removably mounted within the housing. The deflector has circumferentially distributed vanes. The deflector is a first deflector, having a first set of geometric characteristics, that is removable from the housing and replaceable by a second deflector having a second set of geometric characteristics different from the first set of geometric characteristics. The first deflector is one of a first class of deflectors and the second deflector is one of a second class of deflectors, the first and second class of deflectors respectively defining first and second exhaust flow profiles that differ from each other.

Aircraft engine with exhaust having removable deflector

A bearing assembly for a turbomachine includes a bearing inner race, a bearing outer race located radially outwardly from the bearing inner race, and one or more bearing elements located radially between the bearing inner race and the bearing outer race. A bearing sleeve is positioned radially inboard of the bearing inner race and is configured for engagement with a rotating component. The bearing sleeve includes a sleeve body located radially between the bearing inner race and the rotating component, and a puller feature extending from the sleeve body at a first axial end of the bearing sleeve. The puller feature is configured for application of a removal force thereto to remove the bearing from an installed position in the turbomachine.

Bearing inner race with sleeve and integrated puller

An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet connected to a source of combustion gases and an outlet fluidly connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing; a turbine support case secured to the bearing housing, the scroll case disposed axially between the turbine support case and the bearing housing, the turbine support case having spokes extending through the scroll case and radially supported by the bearing housing; and heat shields distributed around the central axis in circumferential alignment with the spokes and extending axially through the scroll case for thermally shielding the spokes, a heat shield of the heat shields disposed around a spoke of the spokes, the heat shield defining an air gap surrounding the spoke inside the scroll case.

Turbine support case with axial spokes and heat shields

A containment ring for a turbine casing assembly, including: a main body portion, the main body portion having an outer periphery and an inner periphery and a forward end and an aft end each extending between the outer periphery and the inner periphery, the main body portion also including an outer containment zone and an inner containment zone, the inner containment zone is integrally formed with the outer containment zone in order to provide a single unitary structure and the inner containment zone being radially inward from the outer containment zone, the inner containment zone extending radially outward from the inner periphery and having a plurality of ribs extending between the forward end and the aft end.

Containment ring for gas turbine engine

An aircraft engine, has: a turbine; a scroll case having an inlet connected to a source of combustion gases and an outlet connected to the turbine, and a conduit extending from the inlet to the outlet; a bearing housing including a support flange; an exhaust case downstream of the turbine; and a turbine support case secured to the bearing housing and to the exhaust case, the turbine support case having spokes extending along a direction having an axial component, the spokes extending through the scroll case and radially supported by the bearing housing, a spoke having a distal end secured to the support flange via: one or more fasteners, and a retaining member at the distal end, the retaining member defining an abutment face facing an axial direction and circumferentially overlapping the support flange, a portion of the support flange located axially between the distal end and the abutment face.

Turbine support case with axial spokes and retaining members

A containment ring assembly for a turbine casing assembly, including: a first inner containment ring; a second inner containment ring; an outer containment ring, the first inner containment ring and the second inner containment ring being radially inward from the outer containment ring, wherein a radial space is located between the outer containment ring and the first inner containment ring and the second inner containment ring, the radial space allowing deformation of the first inner containment ring and the second inner containment ring.

A centrifugal compressor is provided that includes an impeller, a diffuser, a compressor scroll, a bearing housing structure, and a coupling ring. The impeller is configured to rotate about a rotational axis. The diffuser is disposed radially outside of the impeller. The coupling ring is connected to the compressor scroll by a plurality of first fasteners and connected to the bearing housing structure by a plurality of second fasteners. The compressor is configured such that the compressor scroll will decouple from the bearing housing structure as a result of an impeller failure.

Compressor frangible containment structure

A containment ring assembly for a turbine casing assembly, including: a first containment ring; a second containment ring, the first containment ring being radially inward from the second containment ring, wherein a radial space is located between the first containment ring and the second containment ring, the radial space allowing deformation of the first containment ring prior to the first containment ring contacting the second containment ring.

A rotor assembly comprises an internal snap ring seated in a groove defined in an inner diameter surface of a rotor component. The snap ring has centrifugal weights to centrifugally expand enough to compensate for a difference in thermal growth between the rotor component and the snap ring.

Internal retaining ring arrangement for a rotor assembly

An aircraft fuel system comprises a fuel manifold adapter interchangeably connectable between respective fuel manifolds and flow divider valves of different aircraft engine platforms. The adapter has a body having an input interface and an output interface. The input interface is rigidly connectable via a rigid supply line to the flow divider valve of a given one of the different engine platforms so as to locate the output interface in axial alignment with a nozzle-input interface of the fuel manifold of the given one of the engine platforms. The output interface is axially slidably engaged with an upstream-tube end of a linear transfer tube having a downstream-tube end slidably engaged with the nozzle-input interface. The output interface of the adapter and the nozzle-input interface are slidably engaged and thermally decoupled via the linear transfer tube.

Growing community of inventors

St-Bruno-de-Montarville, Canada

Guy Lefebvre