A gas turbine engine includes a radial compressor with first and second blades. The first and second blades have tuned leading edges that prevent natural frequencies from exciting at speeds within an expected operating speed range.
A gas turbine engine includes a radial compressor having first and second blades. The first blade has a tuned leading edge that prevents either blade from exciting at a natural frequency at speeds within an expected operating speed range.
A rotor blade suitable for use in a gas turbine engine includes an attachment section which defines at least one internal cooling passage along a passage axis through the attachment section.
A method and system for determining the reliability of a rotating component compares a normalized stress curve with a normalized strength curve. The resulting overlap corresponds with the reliability of the rotating component.
