초록 ▼

A method for cutting a blade root retention slot in a turbine engine disk element includes forming a precursor slot in the element. The precursor slot has first and second sidewalls and a base. A rotating bit is passed through the precursor slot to machine the base. The bit rotates about an axis of

A method for cutting a blade root retention slot in a turbine engine disk element includes forming a precursor slot in the element. The precursor slot has first and second sidewalls and a base. A rotating bit is passed through the precursor slot to machine the base. The bit rotates about an axis off-normal to a direction of passing.

대표청구항 ▼

What is claimed is: 1. A method for cutting a blade root retention slot in a turbine engine disk element, the method comprising: forming a precursor slot in the element, the precursor slot having first and second sidewalls and a base; subsequent to said forming, machining a convoluted profile into

What is claimed is: 1. A method for cutting a blade root retention slot in a turbine engine disk element, the method comprising: forming a precursor slot in the element, the precursor slot having first and second sidewalls and a base; subsequent to said forming, machining a convoluted profile into the first and second sidewalls; and subsequent to said machining, passing a rotating bit through the precursor slot to machine said base, the bit rotating about an axis off-normal to a direction of said passing. 2. The method of claim 1 wherein said machining broadens and deepens the base. 3. The method claim 1 wherein the machining leaves at least a first portion of the base intact. 4. The method of claim 1 wherein the forming comprises machining with a grinding wheel rotating about a wheel axis essentially perpendicular to a direction of passing said grinding wheel and essentially circumferential to a central longitudinal axis of the disk element. 5. The method of claim 1 wherein the machining comprises machining with a profiling bit having a convoluted longitudinal profile complementary to said convoluted profile of said slot sidewalls. 6. The method of claim 1 wherein the passing smooths transitions between said first and second sidewalls and said base. 7. The method of claim 1 wherein during the passing, the bit axis essentially lies along a radial plane of the element at an angle of between 60째 and 85째 relative to said direction of said passing. 8. The method of claim 7 wherein during the passing the bit axis is inclined relative to said direction of said passing. 9. The method of claim 1 wherein the forming comprises machining with a grinding wheel having portions of different diameters for forming the precursor slot with said first and second sidewalls as stepped sidewalls. 10. The method of claim 1 wherein the passing increases an outward concavity of the base. 11. A method for cutting a blade root retention slot in a turbine engine disk element, the method comprising: forming a precursor slot in the element, the precursor slot having first and second sidewalls and a base; subsequent to said forming, passing a rotating bit through the precursor slot to machine said base, the bit rotating about an axis off-normal to a direction of said passing. 12. The method of claim 11 wherein: the bit is an abrasive bit. 13. The method of claim 11 wherein: the bit is an abrasive bit having a doubly convex surface portion used to machine said base. 14. The method of claim 11 wherein: the forming comprises grinding with a grinding wheel. 15. The method of claim 11 wherein: the forming comprises grinding with a series of grinding wheels of differing widths. 16. The method of claim 11 wherein: the axis is between 5째 and 30째 off-normal to the direction of the passing. 17. The method of claim 16 wherein: the axis is inclined relative to the direction of the passing.