FIELD: machine building.
SUBSTANCE: segment of guiding blades consists of profiled blade body positioned on platform and of fastening elements to fast segment of guiding blades in frame. The fastening elements are located on the side of the platform facing away from the blade body. At least one of the fastening elements is made in form of a separately fabricated item firmly jointed to the platform. The said fastening element is made out of material more ductile in comparison with the platform and/or the blade body and has a fixing hook distant from the platform, and a connecting element sunk with its bearing surface into the platform. Another invention of the group refers to the heat impeller machine, in particular, to a gas turbine, containing at least one the above said segment of the guiding blades. One more invention of the group refers to the procedure of fabrication of the said above segment of the guiding blades including fabrication of the fastening element with the fixing hook out of elongated profile blank by its bending in form of a fixing hook. Upon fabrication of the fastening element it is connected with a power and/or material lock with its bearing surface sunk in the platform.
EFFECT: reliable attachment of segment of guiding blades to frame and simplified fabrication.
14 cl, 3 dwg
Title | Year | Author | Number |
---|---|---|---|
TURBINE BLADE AND GAS TURBINE WITH SUCH BLADE | 2007 |
|
RU2372493C2 |
ANALYSIS OF SURFACE FOR DETECTION OF CLOSED HOLES, AND DEVICE | 2010 |
|
RU2532616C2 |
SEALING RING SEGMENT FOR STATOR OF TURBINE | 2014 |
|
RU2657390C2 |
METHOD OF TURBINE NOZZLE BLADE OR COMPRESSOR STATOR MANUFACTURING, MADE FROM COMPOSITE MATERIAL FOR TURBINE ENGINES AND TURBINE OR COMPRESSOR, INCLUDING NOZZLE BLADE OR STATOR CONSISTING OF SAID SECTORS | 2012 |
|
RU2608405C2 |
DETERMINATION OF IMPELLER MACHINE VANED ROTOR DIAMETER | 2011 |
|
RU2562928C2 |
METHOD OF PROFILING A REPLACEMENT SHOOT AS A REPLACEMENT PARTS FOR OLD PULLEY FOR A TURBOMACHINE WITH A TWO-DIRECTION OF THE FLOW | 2012 |
|
RU2629110C2 |
COMPRESSOR AND APPROPRIATE GAS TURBINE | 2011 |
|
RU2575956C2 |
TURBO COMPRESSOR DRIVEN BY ICE EXHAUST GASES | 2008 |
|
RU2450127C2 |
IMPELLER FOR AXIAL BLOWER | 2015 |
|
RU2645887C2 |
MEASURING METHOD OF LAYER THICKNESS BY LASER TRIANGULATION | 2010 |
|
RU2541440C2 |
Authors
Dates
2011-06-20—Published
2007-02-21—Filed