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 2925-00-139-8309
NSN 6105-01-634-0322
NSN 6620-01-282-6446
NSN 7035-01-604-3032
NSN 6145-00-921-0754
NSN 5930-00-396-2733
NSN 5920-01-010-4855
NSN 5915-01-515-0156
NSN 6145-00-057-2483
NSN 5915-01-555-8081
NSN 6240-01-633-9357
NSN 5920-01-491-9914