| 摘要 |
PROBLEM TO BE SOLVED: To provide an assembly and method for sealing a compressor in a gas turbine engine to avoid leakage of gas past tips of blades and between the blade tips and a surrounding engine casing.SOLUTION: The method comprises forming an annular groove 64, 65, 66 in a compressor casing 36 such that the groove 64, 65, 66 extends circumferentially about a rotor blade 32 that is housed within the compressor casing 36. The compressor casing 36 is then coupled to the rotor blade 32 such that the compressor casing 36 extends circumferentially about the rotor blade 32. A plurality of arcuate seal segments 40 are then inserted into the annular groove 64, 65, 66 without removing the rotor blade 32 from the compressor casing 36 such that the plurality of seal segments 40 extend circumferentially about the rotor blade 32 to facilitate sealing a gap 35 that is defined between the rotor blade 32 and the compressor casing 36. |
