Abstract: An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.

Abstract: An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.

Abstract: A gas turbine engine, has: an annular gaspath extending around a central axis, the annular gaspath defined between a first casing and a second casing, the first casing defining pockets; and a variable guide vane assembly having: variable guide vanes circumferentially distributed around the central axis, the variable guide vanes having airfoils extending into the annular gaspath and extending between first and second pivot members at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes, bushings received within the pockets of the first casing, the first pivot members of the variable guide vanes rollingly engaged to the bushings, and resilient members disposed radially between surfaces of the first casing and the bushings relative to the spanwise axes, the resilient members in abutment against both of the surfaces of the first casing and the bushings.

Abstract: A gas turbine engine, has: an annular gaspath extending around a central axis, the annular gaspath defined between a first casing and a second casing, the first casing defining pockets; and a variable guide vane assembly having: variable guide vanes circumferentially distributed around the central axis, the variable guide vanes having airfoils extending into the annular gaspath and extending between first and second pivot members at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes, bushings received within the pockets of the first casing, the first pivot members of the variable guide vanes rollingly engaged to the bushings, and resilient members disposed radially between surfaces of the first casing and the bushings relative to the spanwise axes, the resilient members in abutment against both of the surfaces of the first casing and the bushings.

Abstract: A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.

Abstract: A gas turbine engine having an engine core defining a core flow path delimited by an engine casing, a washing device having a spraying member defining a conduit in fluid communication with a source of washing fluid, the spraying member having a spraying section for outputting the washing fluid from the conduit, the spraying member movable relative to the engine casing from a retracted position in which the spraying section is flush with a surface of the engine casing defining said core flow path, and an expanded position in which the spraying section protrudes beyond the surface of the engine casing into the core flow path

Abstract: A method of heating a fan blade of a gas turbine engine for anti-icing includes emitting jets of heated air from a radial fin disposed upstream from a radially inward portion of a fan blade airfoil, the jets of heated air being directed by outlet orifices in a downstream direction substantially parallel to a flow of incoming air over the fan blade airfoil.

Abstract: A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.

Abstract: A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.

Abstract: A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.

Abstract: A method of heating a fan blade of a gas turbine engine for anti-icing includes emitting jets of heated air from a radial fin disposed upstream from a radially inward portion of a fan blade airfoil, the jets of heated air being directed by outlet orifices in a downstream direction substantially parallel to a flow of incoming air over the fan blade airfoil.

Abstract: A gas turbine engine having an engine core defining a core flow path delimited by an engine casing, a washing device having a spraying member defining a conduit in fluid communication with a source of washing fluid, the spraying member having a spraying section for outputting the washing fluid from the conduit, the spraying member movable relative to the engine casing from a retracted position in which the spraying section is flush with a surface of the engine casing defining said core flow path, and an expanded position in which the spraying section protrudes beyond the surface of the engine casing into the core flow path

Abstract: A balancing weight is disclosed. The balancing weight is engageable in a hole defined in a rotor, the hole having a predetermined cross-sectional dimension. The balancing weight comprises: a head having a predetermined weight, and a shank extending axially from the head. The shank includes at least two portions expandable in a direction transverse to a hole engagement direction between a first position in which a cross-sectional dimension of the shank is less than the predetermined cross-sectional dimension of the hole and a second position in which the cross-sectional dimension of the shank is greater than the predetermined cross-sectional dimension of the hole in the rotor. A method for installing a balancing weight to an engine rotor is also disclosed.

Abstract: A multi-film oil damper for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall, a first radially extending side wall and a second radially extending side wall, the annular damper cavity having an oil inlet in the radially outward wall, the oil inlet being in communication with a source of pressurized oil; an inner damper ring having axial ends abutting the first and second radially extending side walls of the annular damper cavity; a plurality of outer damper rings coaxially nested between the inner damper ring and the radially outward wall, each outer damper ring having axial ends adjacent the first and second radially outward walls of the annular damper cavity, each outer damper ring having a first cylindrical surface and a second cylindrical surface; a spacer ring disposed at each axial end of the plurality of outer damper rings, a contact sur

Abstract: A multi-film oil damper has a housing defining an annular damper cavity having an oil inlet in communication with a source of pressurized oil. A plurality of nested damper rings is disposed within the annular damper cavity, the plurality of nested damper rings defining a plurality of squeeze film annuli. Spacer rings are disposed adjacent opposed ends of the damper rings. A contact surface of the spacer rings extends radially beyond a first cylindrical surface of an associated damper ring for engaging a second cylindrical surface of an adjacent damper ring. Recesses are defined in the second cylindrical surface of the damper rings, the recesses fluidly communicating between the squeeze film annuli and the oil inlet.

Abstract: A fancase surrounds a set of fan blades mounted for rotation about a central axis of a turbine engine. The fancase has an annular casing structure having an inner wall defining an outer flow boundary surface of a gaspath. An annular recess is defined in the inner wall. A metallic bumper is disposed in the annular recess and bonded to the annular casing structure for limiting fan orbiting during fan unbalanced conditions.

Abstract: A multi-film oil damper for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall, a first radially extending side wall and a second radially extending side wall, the annular damper cavity having an oil inlet in the radially outward wall, the oil inlet being in communication with a source of pressurized oil; an inner damper ring having axial ends abutting the first and second radially extending side walls of the annular damper cavity; a plurality of outer damper rings coaxially nested between the inner damper ring and the radially outward wall, each outer damper ring having axial ends adjacent the first and second radially outward walls of the annular damper cavity, each outer damper ring having a first cylindrical surface and a second cylindrical surface; a plurality of spacer bosses circumferentially spaced apart at each axial end of the plurality

Abstract: A multi-film oil damper has a housing defining an annular damper cavity having an oil inlet in communication with a source of pressurized oil. A plurality of nested damper rings is disposed within the annular damper cavity, the plurality of nested damper rings defining a plurality of squeeze film annuli. Spacer rings are disposed adjacent opposed ends of the damper rings. A contact surface of the spacer rings extends radially beyond a first cylindrical surface of an associated damper ring for engaging a second cylindrical surface of an adjacent damper ring. Recesses are defined in the second cylindrical surface of the damper rings, the recesses fluidly communicating between the squeeze film annuli and the oil inlet.

Abstract: A multi-film oil damper for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall, a first radially extending side wall and a second radially extending side wall, the annular damper cavity having an oil inlet in the radially outward wall, the oil inlet being in communication with a source of pressurized oil; an inner damper ring having axial ends abutting the first and second radially extending side walls of the annular damper cavity; a plurality of outer damper rings coaxially nested between the inner damper ring and the radially outward wall, each outer damper ring having axial ends adjacent the first and second radially outward walls of the annular damper cavity, each outer damper ring having a first cylindrical surface and a second cylindrical surface; a spacer ring disposed at each axial end of the plurality of outer damper rings, a contact sur

Abstract: A multi-film oil damper for accommodating radial movement of a rotary shaft bearing relative to a bearing housing, the multi-film oil damper comprising: an annular damper cavity defined within the bearing housing between a radially outward wall, a first radially extending side wall and a second radially extending side wall, the annular damper cavity having an oil inlet in the radially outward wall, the oil inlet being in communication with a source of pressurized oil; an inner damper ring having axial ends abutting the first and second radially extending side walls of the annular damper cavity; a plurality of outer damper rings coaxially nested between the inner damper ring and the radially outward wall, each outer damper ring having axial ends adjacent the first and second radially outward walls of the annular damper cavity, each outer damper ring having a first cylindrical surface and a second cylindrical surface; a plurality of spacer bosses circumferentially spaced apart at each axial end of the plurality