Methods and apparatus for designing gas turbine engine rotor...

Details Methods and apparatus for designing gas turbine engine rotor... Methods and apparatus for designing gas turbine engine rotor...

2005-09-20

2005-09-20

Nguyen, Ninh H. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific working member mount

Blade received in well or slot

C416S248000

Reexamination Certificate

active

06945754

ABSTRACT:
A method enables a rotor assembly for a gas turbine engine to be designed. The method comprises providing a plurality of rotor blades that each include a dovetail that includes a pair of blade pressure faces and a dovetail bottom that extends arcuately between the pair of blade pressure faces, providing at least one of a rotor disk and a rotor spool that includes a circumferential dovetail slot that is sized to receive the plurality of rotor blades therein, and coupling the plurality of rotor blades to the at least one of a rotor disk and a rotor spool using each respective rotor blade dovetail.

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