发明名称 |
Turbine rotor |
摘要 |
A turbine rotor has composite ceramic blades each having a bulb-shaped root with planar flanks which define an angle of convergence between them not exceeding ten degrees, and by which the root is held in a dovetail section socket in the periphery of the rotor disc by means of wedge-shaped members also disposed in the socket on opposite sides of the root. Each wedge-shaped member is part of an element including a platform which is disposed adjacent the curved portion of the blade radially outwards of the socket and which is joined to the wedge-shaped member by an integral strut. The platforms of all of the elements extend in a circumferential direction and combine to define a continuous ring forming part of the inner boundary of the gas flow path through the turbine.
|
申请公布号 |
US4802824(A) |
申请公布日期 |
1989.02.07 |
申请号 |
US19870131725 |
申请日期 |
1987.12.11 |
申请人 |
SOCIETE NATIONALE D'ETUDE ET MOTEURS D'AVIATION "S.N.E.C.M.A." |
发明人 |
GASTEBOIS, PHILIPPE M. D.;IMBAULT, JEAN-FRANCOIS R. |
分类号 |
F01D5/28;F01D5/30;F01D11/00;(IPC1-7):F01D5/32 |
主分类号 |
F01D5/28 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|