FIELD: engines and pumps.
SUBSTANCE: proposed joint comprises compressor and low-pressure turbine shafts jointed axially by intermediate shaft and coupling sleeve fitted inside said intermediate shaft and screwed on low-pressure turbine shaft, and, radially, via splined joint. It comprises also radial thrust bearing with its outer race fitted on high-pressure turbine shaft inner surface and inner race fitted on intermediate shaft outer surface. There is the nut on coupling sleeve that stays in contact with low-pressure compressor rotor jointed with low-pressure compressor shaft by means of additional splined joint.
EFFECT: possibility to localise compressor shaft breakage inside engine thus preventing destruction of engine and aircraft proper.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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RU2614018C1 |
