FIELD: engine building.
SUBSTANCE: gas turbine (10) device (66, 112) comprising: rotor disk part (68) comprising engaging portion (70); blade part (72) containing engaging portion (74), corresponding engaging portions (70, 74) engage for fixation around the circumference and in the radial direction of part (68) of the rotor disk and part (72) of the blade relative to each other; locking plate (96) connected to a part of the rotor disk and a part of the blade in order to fix in the axial direction a part of the blade relative to the part of the rotor disk, locking plate (96) is axially spaced a distance (D) from axial end (98) of engaging portions (70, 74) of rotor disk part (68) and/or blade part (70), leaving an empty space (V) in the axial direction between engaging portions (70, 74) and fixing plate (96).
EFFECT: cooling of the blades with increased reliability of their work.
14 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
RU2377421C2 |
| TURBOMACHINE ROTOR SECTION | 2010 |
|
RU2518749C2 |
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|
RU2377418C2 |
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|
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| FAN, IN PARTICULAR, FOR TURBINE ENGINE | 2014 |
|
RU2677769C1 |
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|
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| DEVICE FOR BALANCING OF ROTARY PART, IN PARTICULAR TURBOJET ENGINE ROTOR | 2005 |
|
RU2361090C2 |
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|
RU2438019C2 |
| SECTION OF ROTOR FOR TURBOMACHINE; ROTATING BLADE FOR TURBOMACHINE | 2010 |
|
RU2486348C2 |
| ROTARY DEVICE FOR TURBOMACHINE, TURBINE FOR TURBOMACHINE AND TURBOMACHINE | 2014 |
|
RU2676497C2 |
