FIELD: engines and pumps.
SUBSTANCE: invention relates to repair of turbojet fan rotor disc. Engine rim has at least one outer radial leg to retain blade platform with drilled axial bore corresponding to wear of zone accommodating axial fastener. The latter comprises the head and rod with partial thread. Note here that said fastener fit in axial bore so that its head thrust against the leg first surface by nut tightening at rod threaded part at the leg opposite side. Note here that said fastener makes the means of radial retention of led rigidly secured to the rim. Said first surface of said leg is chamfered around drilled bore corresponding to wear zone. Replacement fastener is fitted in place and comprises fillet resting on said chamfered area and features diameter larger than that of the head. Its thickness is smaller than or equal the chamfer depth.
EFFECT: decreased cracking at the led at bore entrance.
10 cl, 6 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| FAN ROTOR AND TURBOJET ENGINE | 2012 |
|
RU2594037C2 |
| TURBOMACHINE ROTOR AND TURBOJET ENGINE | 2012 |
|
RU2607986C2 |
| GAS TURBINE ENGINE ROTOR, TURBOJET AND PLUG FOR GAS TURBINE ENGINE ROTOR | 2009 |
|
RU2496988C2 |
| TURBOJET ENGINE FAN ROTOR | 2002 |
|
RU2221169C2 |
| FAN, IN PARTICULAR, FOR TURBINE ENGINE | 2014 |
|
RU2677769C1 |
| TURBOJET ENGINE BLOWER ROTOR, BLOWER AND AIRCRAFT TURBOJET ENGINE | 2006 |
|
RU2396470C2 |
| CYCLOIDAL REDUCER, FAN MODULE OF DUAL-FLOW TURBOJET ENGINE AND DUAL-FLOW TURBOJET ENGINE | 2013 |
|
RU2627990C2 |
| ROTOR OF AVIATION TURBOJET ENGINE COMPRESSOR, COMPRESSOR AND TURBOJET ENGINE | 2007 |
|
RU2423624C2 |
| FAN OF GAS-TURBINE ENGINE | 2011 |
|
RU2555099C2 |
| DEVICE FOR BALANCING OF ROTARY PART, IN PARTICULAR TURBOJET ENGINE ROTOR | 2005 |
|
RU2361090C2 |
