United Technologies Corporation

Allan B Packman

Bernard D Vaillette

Brian J Schwartz

Krzysztof Barnat

Chung Y Wu

Jon C Hammett

James D Campbell, Jr

Timothy L Brown

Gennaro J Colacino

Richard S Larson

Robert N Davie, Jr

A process for machining axial blade slots in turbine disks used in jet engines is provided. The process broadly includes the steps of providing a turbine disk, forming a roughened slot having a plurality of joined rectangular areas in the turbine disk, and machining the roughened slot to a finished slot.

Process for machining axial blade slots in turbine disks for jet engines

A coolant nozzle is used in a machine tool having a rotating bit. The nozzle includes a through-aperture for accommodating the bit. The nozzle has a coolant inlet and a number of coolant outlets at more than one angular position about the through-aperture. Internal surface portions define one or more passageways between the inlet and the outlets.

Coolant nozzle

The present invention relates to a quill to be used to superabrasively machine complex shapes, such as airfoil shapes, into a substrate. The quill has a shaft portion, an enlarged head portion adjacent the shaft portion, and a tapered grinding portion adjacent the enlarged head portion. The tapered grinding portion has a layer of grit material selected from the group consisting of diamonds and cubic boron nitride thereon. In a preferred embodiment, the quill is a vitrified or plated cubic boron nitride quill on the grinding portion. A method of using the tool is also disclosed.

Flank superabrasive machining

A coolant nozzle is used on a machine tool having a rotating bit of convoluted longitudinal profile for cutting a number of slots in a disk. The nozzle includes at least one coolant inlet and at least one coolant outlet. The coolant outlet has a convoluted section and is positioned to direct a coolant stream tangentially at the bit in a direction of rotation of the bit. Internal surface portions of the nozzle define one or more passageways between the inlet and the outlet(s).

Noise generated in a coannular airstream where there are concentric spaced pipes discharging the flow and the outer pipe extends beyond the inner pipe as in the tail pipe configuration of a fan-jet engine is dissipated by discreetly locating tabs extending internally at the discharge end of the inner pipe. This serves to destroy the coherence of the unsteady pressure field occasioned when the coannular flow streams comingle.

Gas turbine noise suppressor

Jet noise generation occasioned from the gaseous streams in the coaxial streams of a turbofan engine when they as well as the ambient stream encounter is reduced by designing the engine so that the value of the true velocity of the outer stream is substantially higher than the value of the true velocity of the inner stream. It is contemplated that for a turbofan engine the fan stream and primary or engine core streams are inverted so that the higher velocity stream would be in the outer coaxial passage immediately upstream of the point where the streams discharge to ambient. A modified conventional lobe mixer is utilized to invert flow streams.

Growing community of inventors

West Hartford, CT, United States of America

Allan B Packman