Process for machining axial blade slots in turbine disks for jet engines
AssigneeUnited Technologies Corporation
InventorsAllan B. Packman, Bernard D. Vaillette
Life of this patent
Estimating the term…
Abstract
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.
Claims5
A process for machining axial blade slots in a turbine disk for an engine comprising the steps of:
- providing a turbine disk;
- forming a roughened slot having a plurality of joined rectangular areas in said turbine disk;
- machining the roughened slot to a finished slot;
- said forming step comprising forming said roughened slot using at least one superabrasive grinding wheel;
- and
- said forming step further comprising providing a plurality of grinding wheels each having a diameter in the range of six to twelve inches and a single layer of carbon boron nitride grit and sequentially using said wheels to form said roughened slot having said joined rectangular areas.
A process for machining axial blade slots in a turbine disk for an engine comprising the steps of:
- forming a roughened slot having a plurality of joined rectangular areas in said turbine disk;
- machining the roughened slot to a finished slot;
- and
- said machining step comprising providing a quill having a diameter less than a width of the finished slot and a profile identical to a profile of the finished slot, offsetting the quill in a first direction relative to a centerline of said roughened slot to form a first side of the finished slot, and offsetting the quill in a second direction opposed to said first direction to form a second side of the finished slot.
A process for machining axial blade slots in a turbine disk for an engine comprising the steps of:
- providing a turbine disk;
- forming a roughened slot having a plurality of joined rectangular areas in said turbine disk;
- machining the roughened slot to a finished slot;
- said machining step comprising machining a semi-finished slot and machining said semi-finished slot into said finished slot;
- and
- said semi-finished slot machining step comprising machining a semi-finished slot using a quill having a grit size in the range of 60 to 120 and the finished slot machining step comprising machining a finished slot using a quill having a grit size in the range of 170 to 340.
A process for machining axial blade slots in a turbine disk for an engine comprising the steps of:
- providing a turbine disk;
- forming a roughened slot having a plurality of joined rectangular areas in said turbine disk;
- machining the roughened slot to a finished slot;
- and
- said machining step comprising aligning a semi-finish tool having dimensions less than the dimensions of the finished slot, creating a semi-finished slot in a single pass using said semi-finish tool, aligning a finish tool on a centerline of the semi-finished slot, and creating said finished slot in a single pass using said finish tool.
Dependencies are inferred from the claim text.