초록 ▼

An air duct assembly for a gas turbine compressor rotor in a gas turbine engine is described. The rotor includes a compressor spool shaft and at least one stage disk, and the air duct assembly includes an elongate hollow cylindrical air duct configured to couple to a stage disk at a first end of the

An air duct assembly for a gas turbine compressor rotor in a gas turbine engine is described. The rotor includes a compressor spool shaft and at least one stage disk, and the air duct assembly includes an elongate hollow cylindrical air duct configured to couple to a stage disk at a first end of the air duct. The second end of the air duct is configured to couple to the spool shaft. The second end of the air duct includes a plurality of lobes depending radially inward, a spool shaft insert configured to fit into an opening in the spool shaft, and a plurality of pins coupled to the spool shaft insert and configured to extend from the insert and to engage the lobes of the second end of the air duct.

대표청구항 ▼

[ We claim:] [1.] An air duct assembly for a turbine compressor rotor, the rotor including a compressor spool shaft and at least one stage disk, said air duct assembly comprising:an elongate hollow cylindrical air duct having a first end and a second end, said first end configured to couple to a sta

[ We claim:] [1.] An air duct assembly for a turbine compressor rotor, the rotor including a compressor spool shaft and at least one stage disk, said air duct assembly comprising:an elongate hollow cylindrical air duct having a first end and a second end, said first end configured to couple to a stage disk, said second end configured to couple to the spool shaft, said second end of said air duct comprising a plurality of lobes depending radially inward;a spool shaft insert configured to fit into an opening in the spool shaft; anda plurality of pins coupled to said spool shaft insert and configured to extend from said insert and to engage said lobes.