Abstract: There is presented a casing arrangement for a gas turbine engine. The casing arrangement includes a plurality of tip treatment bars extending between a pair of spaced-apart annular supports, with each tip treatment bar being elongate and supported at each end by a respective support such that each end of the bar is received within an opening formed in the respective support. At least the ends of each tip treatment bar are tapered in transverse cross-section so as to have a wedge-shaped profile, and the openings in the supports have a complementary tapered shape for receipt and retention of the bar ends therein.

Abstract: An apparatus for investigating mechanical operational characteristics of a gas turbine variable vane actuation system includes coaxial inner and outer annular casings corresponding to inner and outer casings of a gas turbine engine. The apparatus includes a circumferential row of vane substitutes, each extending between an inner end at the inner casing and an outer end at the outer casing, and rotatable about an axis extending through its ends to emulate the rotation of a variable vane in the engine. The apparatus includes respective loading devices for the vane substitutes, each applying a mechanical load to its vane substitute between the inner and outer ends as the vane substitute rotates to emulate the aerodynamic loading on a variable vane in the engine and to generate resulting frictional loading at the inner and outer ends which emulates resulting the frictional loading at the ends of the variable vane in the engine.

Abstract: There is proposed a hinge arrangement (29) configured to hingedly interconnect a first component (26) and a second component (27). The hinge arrangement (29) incorporates a first part (37) of an electrical connector (38) which is formed as an integral feature of the hinge arrangement (29), said first part (37) of the electrical connector (38) being configured to releasably and electrically engage a second part (40) of the electrical connector (38) such that the second part (40) of the electrical connector is separable from the hinge arrangement (29).

Abstract: An apparatus for investigating mechanical operational characteristics of a gas turbine variable vane actuation system includes coaxial inner and outer annular casings corresponding to inner and outer casings of a gas turbine engine. The apparatus includes a circumferential row of vane substitutes, each extending between an inner end at the inner casing and an outer end at the outer casing, and rotatable about an axis extending through its ends to emulate the rotation of a variable vane in the engine. The apparatus includes respective loading devices for the vane substitutes, each applying a mechanical load to its vane substitute between the inner and outer ends as the vane substitute rotates to emulate the aerodynamic loading on a variable vane in the engine and to generate resulting frictional loading at the inner and outer ends which emulates resulting the frictional loading at the ends of the variable vane in the engine.

Abstract: There is presented a casing arrangement for a gas turbine engine. The casing arrangement includes a plurality of tip treatment bars extending between a pair of spaced-apart annular supports, with each tip treatment bar being elongate and supported at each end by a respective support such that each end of the bar is received within an opening formed in the respective support. At least the ends of each tip treatment bar are tapered in transverse cross-section so as to have a wedge-shaped profile, and the openings in the supports have a complementary tapered shape for receipt and retention of the bar ends therein.

Abstract: A variable guide vane assembly comprising a variable guide vane having an aerofoil and a spindle at one end of the aerofoil; wherein the vane further comprises a platform positioned between the aerofoil and the spindle, the platform having a surface facing in the direction of the spindle and at least one side face; the assembly also having a washer with an aperture through which the spindle extends, the washer having a portion which overhangs the at least one side face.

Abstract: A panel assembly of the kind found in the air intake of a gas turbine engine or a fan duct is designed to be demountable for maintenance purposes. Consequently there exists between the panels a gap to be sealed. Thus, the assembly has a deformable seal for such a purpose and has an elongated, hollow resilient member mounted on a flange at the edge of one of the panels and arranged to be pressed against a flange at the confronting edge of the adjacent panel. The flanges are shaped such that the hollow member when pressed between the flanges effectively seals the gap between the panels and a portion of the seal member lies flush between the panel edges.

Abstract: A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane 2 and the wall of the slot 8, 10. A restraint element 14, 34 is mounted in a recess 26, 28; 48 of the support structure 4, 6 and is engaged by a notch 30, 32 in the vane 2 to restrict axial displacement of the vane 2. Consequently, vibration of the vane in directions perpendicular to the lengthwise direction of the vane are damped by the elastomeric material 12 but bodily axial displacement of the vane 2 is prevented by the restraint elements 14, 34.

Abstract: A panel assembly of the kind found in the air intake of a gas turbine engine or a fan duct is designed to be demountable for maintenance purposes. Consequently there exists between the panels a gap to be sealed. The invention provides a deformable seal for the purpose comprising an elongate, hollow resilient member mounted on a flange at the edge of one of the panels and arranged to be pressed against a flange at the confronting edge of the adjacent panel. The flanges are shaped such that the hollow member when pressed between the flanges effectively seals the gap between the panels and a portion of the seal member lies flush between the panel edges.

Abstract: A fluid flow machine comprises an array of vanes (2) which are supported at their ends by inner and outer support structures 4, 6. The ends of the vanes are received in slots 8, 10, with resilient material 12 disposed between the vane 2 and the wall of the slot 8, 10. A restraint element 14, 34 is mounted in a recess 26, 28; 48 of the support structure 4, 6 and is engaged by a notch 30, 32 in the vane 2 to restrict axial displacement of the vane 2. Consequently, vibration of the vane in directions perpendicular to the lengthwise direction of the vane are damped by the elastomeric material 12 but bodily axial displacement of the vane 2 is prevented by the restraint elements 14, 34.

Abstract: A vane provided with at least one spindle, the at least one spindle configured to engage in operation with a support such that in operation the vane pivots about the at least one spindle. The vane is further provided with an electrically operable heater which is communicable with an electrical supply via an electrical connection node located in the at least one spindle. The electrical connection node comprises a female portion and a corresponding male portion. The support is defined by a casing.

Abstract: A vane provided with at least one spindle, said at least one spindle configured to engage in operation with a support means such that in operation said vane pivots about said at least one spindle. The vane is further provided with an electrically operable heater which is communicable with an electrical supply via an electrical connection node located in the said at least one spindle. The electrical connection node comprises a female portion and a corresponding male portion. The support means is defined by a casing.

Abstract: A gas turbine engine casing includes a tip treatment ring 20 which comprises end supports 18 which support tip treatment bars 16. Each tip treatment bar 16 is mounted at its ends within the respective end supports 18 by damping elements 22, which isolate the bar 16 from the end supports 18. The elements 22 damp vibrations induced in the tip treatment bars 16 so inhibiting the initiation of high cycle fatigue cracking.

Abstract: A gas turbine engine casing includes a tip treatment ring 20 which comprises end supports 18 which support tip treatment bars 16. Each tip treatment bar 16 is mounted at its ends within the respective end supports 18 by means of damping elements 22, which isolate the bar 16 from the end supports 18. The elements 22 damp vibrations induced in the tip treatment bars 16 so inhibiting the initiation of high cycle fatigue cracking.