FIELD: mechanical engineering; gas-turbine engines of aircraft and ground application.
SUBSTANCE: according to invention in fan of gas-turbine engine with fan working blades and disk on L-shaped projection of which support ring flange is installed in which compressor intake fairing is secured by axial bolts and provided with conical ring projection, C-shaped sealing ring with inner and outer axial projections is installed between flange and root of blade. Said axial projections are in contact with root and lower flange of blade, respectively. In axial holes of sealing ring hollow heads of axial bolts are arranged. Ring clearance is made between sealing ring and projection of intake fairing at 
where d is diameter of axial hole in sealing ring; 
is diameter of circumference described around bolt head; 
is diameter of inner space of bolt head; h is axial length of radial slot clearance; L is axial length of bolt head.
EFFECT: improved reliability of design owing to prevention of getting of fastening members into gas-air duct of engine, facilitated assembling process.
3 dwg
| Title | Year | Author | Number |
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| 0 |
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| GAS-TURBINE ENGINE | 2003 |
|
RU2255234C2 |
