Turbine blade with a reduced mass

Details Turbine blade with a reduced mass Turbine blade with a reduced mass

2007-06-12

2007-06-12

Denion, Thomas (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Laminated, embedded member or encased material

C416S24100B

Reexamination Certificate

active

10501723

ABSTRACT:
The invention relates to a turbine comprising at least four stages and to the use of a rotor blade with a reduced mass. In prior art, rotor blades in the fourth stage of a gas turbine, which exceed 50 cm in length, cause problems relating to mechanical strength, as centrifugal forces of too great a magnitude occur during the rotation of the rotor blades. An inventive rotor blade in the fourth row of a gas turbine has a reduced density as a result of a high proportion of a ceramic, thus reducing the centrifugal force.

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Department of Defense Composite Materials Handbook vol. 5 Ceramic Matrix Composites, p. 63 and 227.

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