FIELD: machine building.
SUBSTANCE: blade of an impeller machine includes a shaped body, a root, as well as a shank of dovetail type, and is made of oriented layers of composite material, which are connected to each other by means of binding agent. Shank is made with side contact surfaces dished on each side into the blade body. Side contact surfaces of the shank are curved as parts of outer or inner surface of toroid and restricted with convex surface located at the bottom in the form of some part of the toroid surface. In upper part the side contact surfaces of the shank are connected through side surfaces of the root to shaped surfaces of the body.
EFFECT: invention allows reducing stress of a blade in a transition zone of a body to a shank, increasing the blade strength and reducing shear stresses in the blade shank.
4 dwg
Title | Year | Author | Number |
---|---|---|---|
TURBOJET ENGINE LOW-PRESSURE COMPRESSOR SECOND STAGE ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603383C1 |
TURBOJET ENGINE LOW-PRESSURE COMPRESSOR THIRD STAGE ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603384C1 |
GAS TURBINE ENGINE LOW-PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2611497C1 |
ROTOR ASSEMBLY FOR GAS TURBINE ENGINE | 2009 |
|
RU2439337C2 |
GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603380C1 |
AXIAL-FLOW COMPRESSOR BLADES | 2001 |
|
RU2210009C1 |
GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603377C1 |
GAS TURBINE ENGINE LOW PRESSURE COMPRESSOR ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603379C1 |
TURBOJET ENGINE LOW-PRESSURE COMPRESSOR FIRST STAGE ROTOR IMPELLER (VERSIONS) | 2015 |
|
RU2603382C1 |
TURBOJET LOW-PRESSURE COMPRESSOR ROTOR FOURTH-STAGE IMPELLER | 2015 |
|
RU2612282C1 |
Authors
Dates
2013-10-10—Published
2012-01-13—Filed