Abstract: A device and method for reducing swirl in a gas compressor is provided. The device can include a tubular or annular seal body having an abradable interior surface for use in forming a seal. The tubular body can further have a plurality of swirl teeth arranged on a high pressure side of the seal body. The swirl teeth are disposed so as to form swirl slots between the adjacent swirl teeth. The swirl teeth can have a brake chord and a brake pitch describing the length and separation of each adjacent swirl tooth. The ratio of the brake pitch to the brake chord can be optimized in order to maximize creation of free vortices between the swirl teeth as the compressor rotates for swirl reduction.

Abstract: A device and method for reducing swirl in a gas compressors is provided. The device can include a tubular or annular seal body having an abradable interior surface for use in forming a seal. The tubular body can further have a plurality of swirl teeth arranged on a high pressure side of the seal body. The swirl teeth are disposed so as to form swirl slots between the adjacent swirl teeth. The swirl teeth can have a brake chord and a brake pitch describing the length and separation of each adjacent swirl tooth. The ratio of the brake pitch to the brake chord can be optimized in order to maximize creation of free vortices between the swirl teeth as the compressor rotates to for swirl reduction.

Abstract: A synthetic jet for a stationary vane for a turbo-machine is disclosed. The synthetic jet includes a backside cavity and a jet cavity. The jet cavity includes a frontside cavity adjoining the backside cavity and a jet passage extending from a fluid stream interfacing surface of the airfoil towards the frontside cavity. The jet passage is in flow communication with the frontside cavity. The synthetic jet also includes a disk located between the backside cavity and the frontside cavity. The disk includes a cylindrical disk and a coating on each side of the cylindrical disk. The coating is a piezo electric ceramic material.

Abstract: A synthetic jet for a stationary vane for a turbo-machine is disclosed. The synthetic jet includes a backside cavity and a jet cavity. The jet cavity includes a frontside cavity adjoining the backside cavity and a jet passage extending from a fluid stream interfacing surface of the airfoil towards the frontside cavity. The jet passage is in flow communication with the frontside cavity. The synthetic jet also includes a disk located between the backside cavity and the frontside cavity. The disk includes a cylindrical disk and a coating on each side of the cylindrical disk. The coating is a piezo electric ceramic material.