Rolls-Royce Patente

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A method of monitoring turbine blade creep in a gas turbine engine is provided. The method includes: receiving stereo images of a turbine blade of a row of turbine blades, the images having been obtained using a stereo borescope located in the engine adjacent the row of turbine blades; identifying same features of the blade in each of the stereo images; mapping each of the identified features by triangulation onto a 3D space to produce a 3D depth map of at least part of the blade; providing a 3D reference model of the blade; and comparing the 3D reference model with the 3D depth map to measure one or more deviations in shape of the blade to determine an amount of creep-induced distortion of the blade.

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A vane cooling system for a gas turbine engine comprises a vane (21) arranged on a stator and having a chamber (23) extending continuously from a radially inner end to a radially outer end of the vane. The vane (21) has; a radially inner inlet (24) and a radially outer inlet (25), a first cooling fluid feed (39) in communication with the radially inner inlet (24) and a second cooling fluid feed (28) in communication with the radially outer inlet (25), The first cooling fluid feed (39) has a higher pressure than the second cooling feed (28). A flow adjustment device (30) is arranged for adjusting a flow of the second cooling fluid feed into the radially outer inlet (25).

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A brush seal (400, 600, 700, 900, 900-1, 1000) includes an annular plate assembly (402, 602, 702, 902, 902-1, 1002) defining a radially inner diameter (D2, D2-1, D2-2, D2-4, D2-5, D2-6, D2-7) having an inner central axis (A2, A2-1, A2-2, A2-4, A2-5, A2-6, A2-7) and a radially outer diameter (D3, D3-1, D3-2, D3-4, D3-5, D3-6, D3-7) having an outer central axis (A3, A3-1, A3-2, A3-4, A3-5, A3-6, A3-7). The inner central axis (A2, A2-1, A2-2, A2-4, A2-5, A2-6, A2-7) and the outer central axis (A3, A3-1, A3-2, A3-4, A3-5, A3-6, A3-7) are spaced apart from each other by an offset (O1, O2, O3, O4, O5, O6, O7), such that the radially inner diameter (D2, D2-1, D2-2, D2-4, D2-5, D2-6, D2-7) and the radially outer diameter (D3, D3-1, D3-2, D3-4, D3-5, D3-6, D3-7) are eccentric with respect to each other. The brush seal (400, 600, 700, 900, 900-1, 1000) further includes a bristle pack (408, 608, 708, 908, 908-1, 1008). The bristle pack (408, 608, 708, 908, 908-1, 1008) includes a plurality of bristles (410, 610, 710, 910, 910-1, 1010) defining a bristle bore (412, 612, 712, 912, 912-2, 1012) having a bristle bore central axis (A4, A4-1, A4-2, A4-4, A4-5, A4-6). The bristle bore central axis (A4, A4-1, A4-2, A4-4, A4-5, A4-6) is aligned with the inner central axis (A2, A2-1, A2-2, A2-4, A2-5, A2-6, A2-7) and the bristle bore central axis (A4, A4-1, A4-2, A4-4, A4-5, A4-6) is offset from the outer central axis (A3, A3-1, A3-2, A3-4, A3-5, A3-6, A3-7). Moreover, the brush seal (400, 600, 700, 900, 900-1, 1000) is disposed around a rotating component (106). The bristle bore central axis (A4, A4-1, A4-2, A4-4, A4-5, A4-6) is aligned with a component axis (A1) of the rotating component (106) and the bristle pack (408, 608, 708, 908, 908-1, 1008) engages with the rotating component (106).

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A gas turbine engine (10) comprises a fan (23); an engine core (11) comprising a compressor (14), a combustor (16), and a turbine (19) coupled to the compressor (14) through a shaft (26); a reduction gearbox (30); an Engine Section Stator (ESS) (24) comprising a plurality of ESS vanes (42) with an external surface (S) washed by the core airflow; an ESS heating system (44) adapted to heat the ESS vanes (42), and a temperature sensor (48) adapted to detect the temperature of the external surface (S) of the ESS vanes (42) and send a signal to the ESS heating system (44) when said temperature is below a reference temperature. Upon detection and/or inference of ice crystal conditions and receiving from the temperature sensor (48) the signal that the temperature is below the reference temperature, the ESS heating system (44) is activated to heat at least a portion (S1) of the external surface (S) of the ESS vanes (42) and promote melting and adhering of ice crystals thereto.

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The second unison ring portion(140) is co-axial with the first unison ring portion (110). The first unison ring portion comprises a first unison ring (120) and a first bearing location portion (130), and the second unison ring portion comprises a second unison ring (150) and a second bearing location portion (160). The first bearing location portion is co-axial with the first unison ring and projects axially from the first unison ring, while the second bearing location portion is co-axial with the second unison ring and projects axially from the second unison ring. The first bearing location portion comprises a radially outwardly opening groove (132), and the second bearing location portion comprising a radially inwardly opening groove 162). The first unison ring portion and the second unison ring portion are positioned with the first bearing location portion being concentric with the second bearing location portion thereby defining an annular cavity (190) therebetween.

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