FIELD: engines.
SUBSTANCE: invention relates to aircraft gas turbine engine compressor stator and rotors with rotating blades. Gas turbine engine compressor stator includes rotating guide blades installed external pins in detachable outer housing and internal-in detachable inner rings. Semi-ring internal rings in the plane of axial connector are interconnected by lock joint dovetail type, the middle part of z-shaped ledges along the length of locking compounds are removed. Length of not remote parts locking compounds does not exceed the value of allowable during assembly the engine axial shift of the outer case and not less than 1…2 mm less than the length of remote parts of z-shaped ledges locking compounds.
EFFECT: higher reliability and service life of compressor stator, due to exclusion of opening and displacement of joints semi-rings internal rings of rotating guide blades.
1 cl, 10 dwg
| Title | Year | Author | Number |
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