Abstract: A method of grinding the tip of a blade which forms part of a rotor for a gas turbine engine is provided. The method includes mounting a plurality of blades in a disc to provide a blade assembly; mounting the blade assembly in a grinding apparatus; aligning the plurality of blades in a predetermined position using compressed fluid; and, grinding the blade tips.

Abstract: A method of grinding the tip of a blade which forms part of a rotor for a gas turbine engine is provided. The method includes mounting a plurality of blades in a disc to provide a blade assembly; mounting the blade assembly in a grinding apparatus; aligning the plurality of blades in a predetermined position using compressed fluid; and, grinding the blade tips.

Abstract: The present invention relates to a sealing arrangement between a stator assembly and a rotor 12 of a gas turbine engine, the rotor 12 being rotatable about an engine axis, the stator assembly comprising vanes 22 provided at their radially inner ends with a vane support structure 28 which comprises an annular platform 30 supporting the vanes and a radial flange 32 which extends radially inwardly from the platform, the sealing arrangement comprising an array of leaves 36 which extend inwardly from the radially inner periphery of the flange 32, towards a circumferential sealing surface 13 of the rotor 12.

Abstract: A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating temperatures of the casing. The tube (2) is located at one end in a steel holder (3). In the middle of the tube (2) is arranged a metal rod (9), which is fixed to the holder (3). At the opposite end of the tube (2) is an insert (7), which has an apertures through which passes the metal rod (9). Within the insert (7) the metal rod (9) is screw threaded so it can be turned to provide always enough tension at all operating temperatures and the metal tube (9) is held tight, secure, and has minimal vibration.

Abstract: A support (1) for a reflective target to be mounted on a turbine casing, which is used in casing bending measurements. The support (1) comprises a tube (2), which was chosen to ensure a thermal expansion coefficient near zero at the operating temperatures of the casing. The tube (2) is located at one end in a steel holder (3). In the middle of the tube (2) is arranged a metal rod (9), which is fixed to the holder (3). At the opposite end of the tube (2) is an insert (7), which has an apertures through which passes the metal rod (9). Within the insert (7) the metal rod (9) is screw threaded so it can be turned to provide always enough tension at all operating temperatures and the metal tube (9) is held tight, secure, and has minimal vibration.

Abstract: A gas turbine engine core casing comprises axially adjacent portions (20,21) that are flanged to receive bolts (28) that attach the portions (20,21) to each other. One of the casing portions (20) is provided with flange (23) that is of L-shape cross-section to provide local enhancement of the rigidity of the casing portion (20). Such rigidity enhancement provides improved debris containment in the event of the failure of rotor components within the casing.