Aluminum alloy, ams 4141; 11.422 in. Min 11.447 in. Max lg, 9.655 in. Min 9.675 in. Max w, 0.271 in. Min 0.278 in. Max diameter of 10 holes, 0.338 in. Min 0.345 in. Max diameter of 2 holes
A component of a vane assembly, compressor, aircraft gas turbine engine. It is designed to receive air from the preceding compressor blades and deliver it to the succeeding row of compressor blades, diffuser, or combustion area at correct pressure, velocity and direction.
Classification: Parts of gas turbine aircraft engines, other than for use in civil aircraft
NSN 6685-01-122-7471
NSN 5945-01-523-5579
NSN 5925-01-046-4918
NSN 6135-01-382-1980
NSN 5945-01-624-5630
NSN 5920-01-414-6983
NSN 5960-01-219-5504
NSN 7035-01-026-1171
NSN 6220-01-283-3963
NSN 6620-00-663-8962
NSN 5996-01-313-3930
NSN 5950-00-080-5796