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

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.

BACKGROUND OF THE INVENTION

The present invention relates to a process for machining axial blade slots in turbine disks for jet engines.

Retention slots are a design feature of turbine disks. The slots are used to hold or retain turbine blades around the periphery of the disk. Current practice in the aerospace industry is to machine these slots into the disk by use of a broaching machine, which is a linear cutting machine that drives successively larger cutters through the disk slot, with the final cutters having the fir tree or other appropriate shape of the finished slot. One technique which employs broaching is illustrated in U.S. Pat. No. 5,430,936 to Yadzik, Jr. et al. Broaching presents a number of issues, including costly cutter tools, very long tooling lead-time, very long tooling set-ups, and a very large single-purpose machine requiring a special concrete base and other infrastructure to support it.

Another method for producing profiled parts is illustrated in U.S. Pat. No. 5,330,326 to Kuehne et al. The method involves pre-shaping and finish grinding a blank in one chucking position with at least one profiled grinding wheel. The blank is translated and rotated relative to the at least one profiled grinding wheel during the pre-shaping step for giving the blank approximately a desired profile. The finished grinding step is performed at least partially after the pre-shaping step for smoothing surfaces and producing the final profile. The Kuehne et al. method may be used for external surfaces, such as the cutting of blades, and not internal surfaces. Thus, Kuehne et al.'s method is not applicable to the creation of internal slots.

There remains a need for a better approach to form the axial blade slots in a turbine disk.

SUMMARY OF THE INVENTION

Accordingly, it is an object of the present invention to provide an improved process for machining axial blade slots in turbine disks used in jet engines.

The foregoing object is attained by the process of the present invention.

In accordance with the present invention, a process for machining axial blade slots in a turbine disk is provided. The process broadly comprises 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 into a finished slot.

Other details of the process for machining axial blade slots in turbine disks for jet engines, as well as other objects and advantages attendant thereto, are set forth in the following detailed description and the accompanying drawings wherein like reference numeral depict like elements.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT(S)

The present invention relates to a process for machining axial blade slots, such as those designated by the reference numeral10inFIG. 1, in turbine disks12for use in jet engines. The process initially involves the step of providing a blank turbine disk12. The blank turbine disk12may be formed from a nickel based superalloy, a titanium based superalloy, steel, or another suitable material.

The next step in the process is to form a series of roughened slots14in the blank disk12. Each of the roughened slots14has a plurality of joined rectangular areas such as2,3, or4joined rectangular areas.FIG. 2Billustrates a roughened slot having three rectangular areas16,18, and20. The rectangular areas16,18and20may be formed using a grinding machine22such as that shown inFIG. 2A and aseries of superabrasive grinding wheels24connected to a spindle26. A superabrasive grinding wheel is a class of wheels where the abrasive material is diamond or cubic boron nitride.

To form a roughened slot such as that shown inFIG. 2B, a first superabrasive grinding wheel24having a first thickness is used to form the rectangular area20. After the rectangular area20has been formed, a second superabrasive grinding wheel having a second thickness less than the first thickness is connected to the spindle26and used to form the rectangular area18. Thereafter, a third superabrasive grinding wheel having a third thickness less than the second thickness is connected to the spindle26and used to form the rectangular area16. Each of the grinding wheels preferably has a diameter in the range of six inches to twelve inches, is formed from tool steel, and preferably has a single layer carbon boron nitride thereon to form the wheel grinding surfaces. The carbon boron nitride may be electroplated or brazed to the underlying tool steel. During formation of each roughened slot14, a coolant, such as an oil coolant, may be used to reduce excessive heat.

After the roughened slot14has been formed, a finished slot30is formed. The finished slot30may be formed using one of two different processes. In a first process, the finished slot30is formed in two steps using two quills having a diameter less than a width W of the finished slot and a profile identical to the profile of the finished slot. In this process, a semi-finished slot32is formed using a first quill36. The first quill is offset in a first direction relative to the centerline34of the roughened slot14and then offset in a second direction opposite to the first direction. The first quill is then removed and a second quill is used to form the finished slot30. The second quill is also offset in one direction relative to the centerline34to finish a first side and then offset in a second direction, opposed to the first direction, to finish a second side. Preferably, each of the quills has a diameter in the range of 0.020 to 0.030 inches less than the width of the finished slot. If desired, a single quill could be used to form the semi-finished and finished slots instead of two different quills.

In an alternative or second process, the finished slot30is formed using two quills. The first quill has a dimension slightly less than that of the finished slot30. The second quill has the same dimension as the finished slot30. In such an approach, the first quill is aligned with the centerline34of the roughened slot and used to form a semi-finish slot in a single pass and the second quill is aligned with the centerline of the semi-finished slot to form the finish cut in one pass, cutting both sides of the slot simultaneously.

Each of the quills used to perform the cuts has a single layer of carbon boron nitride electroplated or brazed on a tool steel form. During machining of the semi-finished and/or finished slots, a coolant, such as an oil coolant, may be used to avoid excessive heat.

The finishing quill should have proper abrasive grit size and distribution to form slot walls with a roughness under65Ra. Typically, a semi-finishing quill will have a grit size in the range of 60 to 120, while the finishing quill will have a grit size in the range of 170 to 340.

It is apparent that there has been provided in accordance with the present invention a process for machining axial blade slots in turbine disks for jet engines which fully satisfies the objects, means, and advantages set forth hereinbefore. While the present invention has been described in the context of specific embodiments thereof, other alternatives, modifications, and variations will become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations to embrace those alternatives, modifications, and variations which fall within the broad scope of the appended claims.