FIELD: mechanical engineering.
SUBSTANCE: invention relates to a turbomachine assembly device designed to center shaft (4) of the second module relatively to longitudinal axis (X) of hollow central hub (21) located in front of first module (5). Specified first module (5) has longitudinal cavity (20) passing along specified axis (X), passing from the front into specified hollow hub (21) and passing through first module (5) along longitudinal axis (X) to the rear end. Specified shaft (4) must be inserted into specified longitudinal cavity (20) through the specified rear end containing centering element (25) of the central axis, made with the possibility of installation in specified hollow hub (21) by inserting through first end (26') and interacting with the hub, so that its central axis coincides with specified longitudinal axis (X). In addition, the device contains guide tube (36) capable of entering at least one part of longitudinal cavity (20) of first module (5) behind hollow hub (21). The device is made in such a way that guide tube (36) slides inside centering element (25) along the specified central axis between the first position, in which guide tube (36) is completely in front of centering element (25) relatively to specified first end (26'), and the rear position, in which guide tube (36) protrudes beyond specified first end (26'), penetrating into longitudinal cavity (20) when centering element (25) is placed in hollow hub (21). The invention also relates to a system consisting of a device and a calibration device, as well as to an assembly method, in which it is used.
EFFECT: invention makes it possible to ensure the coupling of mazes, manipulations are noticeably simplified, which makes it possible to do without systematic alignment checks.
10 cl, 17 dwg
Title | Year | Author | Number |
---|---|---|---|
SHAFT SYSTEM FOR AVIATION TURBOMACHINE | 2018 |
|
RU2772757C2 |
METHOD OF DISMOUNTING TURBOJET ENGINE, DEVICE FOR HEATING | 2013 |
|
RU2635741C2 |
TURBOMACHINE WITH GEARBOX FOR AIRCRAFT | 2018 |
|
RU2774134C2 |
TURBOMACHINE AND TORQUE TRANSMISSION SYSTEM FOR TURBOMACHINE | 2015 |
|
RU2694106C2 |
TOOL FOR UNSCREWING COUPLING NUT OF GAS TURBINE ENGINE MODULAR ROTOR | 2013 |
|
RU2645874C2 |
DISC WITH FAN BLADES FOR TURBOMACHINE, TURBOMACHINE FAN AND AIRCRAFT ENGINE | 2016 |
|
RU2716953C2 |
TURBOMACHINE PROPELLER BLADE, IN PARTICULAR OF THE UNDUCTED-TYPE FAN ENGINE, THE CORRESPONDING PROPELLER AND TURBOMACHINE | 2015 |
|
RU2667555C1 |
ASSEMBLY METHOD OF GAS-TURBINE ENGINE, AND DEVICE FOR ITS IMPLEMENTATION | 2006 |
|
RU2415275C2 |
COUPLER OF EQUIPMENT, SUCH AS AGRICULTURAL EQUIPMENT, ON LIFTING SYSTEM OF VEHICLE, SUCH AS AGRICULTURAL TRACTOR | 2015 |
|
RU2672488C2 |
RADIAL-FLOW TURBINE DIRECTIVE NOZZLE DIAPHRAGM WITH VARIABLE INCIDENCE, IN PARTICULAR TURBINES OF ADDITIONAL POWER SOURCE | 2012 |
|
RU2632061C2 |
Authors
Dates
2022-04-15—Published
2018-09-24—Filed