发明名称 |
METHOD AND APPARATUS FOR REDUCING TURBINE BLADE TIP REGION TEMPERATURES |
摘要 |
A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.
|
申请公布号 |
US2003223870(A1) |
申请公布日期 |
2003.12.04 |
申请号 |
US20020160527 |
申请日期 |
2002.05.31 |
申请人 |
KEITH SEAN ROBERT;DEMARCHE THOMAS EDWARD;STAKER JOHN ROBERT;TRESSLER JUDD DODGE |
发明人 |
KEITH SEAN ROBERT;DEMARCHE THOMAS EDWARD;STAKER JOHN ROBERT;TRESSLER JUDD DODGE |
分类号 |
F01D5/14;F01D5/18;F01D5/20;(IPC1-7):F01D5/18 |
主分类号 |
F01D5/14 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|