GOVERNMENT CONTRACT The United States Government has rights in this invention pursuant to Contract No. N00024-79-C-4175 between Westinghouse Electric Corporation and the Department of Defense.

TECHNICAL FIELD

This invention relates to steam turbine blades and more particularly to a method of making side entry turbine blade roots, grooves and steeples. Side entry turbine blades have roots which fit into similar shaped grooves in disc which form the turbine rotor. A unique geometry has been developed which helps minimize the stress concentration due to centrifugal and bending loads as the blades and the design can be scaled up or down over a range of sizes.

BACKGROUND ART Examples of turbine blade configuration are available in German Patent Document 3236-021 dated May, 1983, Russian Patent Document 445-853 of June, 1974 and U.S. Patent Nos. 3,887,987; 4,191,509 and 4,260,331. These documents fail to teach that turbine blade roots, steeples and grooves can be built from a proportional, dimensional model so that the stress concentration in each blade root and steeple are equal.

DESCRIPTION OF THE INVENTION

The principle object of the invention is the manufacture of turbine blade roots, steeples, and grooves so that the stress concentration in each blade root and steeple are equal. With this object in view, the present invention resides in a method of making turbine blade roots, steeples and grooves so that the stress concentra- tions in each blade root and steeple is equal characterized by the steps of forming the blade roots, grooves, and steeples so that they have the same shape; forming the blade roots and steeples to have inclined surfaces which provide the only contact area between the blades and the steeples; providing a proportional dimensional model of a blade root, groove and steeple whereby any size blade root, steeple and groove can be scaled from the dimensional model by multiplying all the dimensions on said model by a constant.

BRIEF DESCRIPTION OF THE DRAWINGS The objects and advantages of this invention will become more apparent by reading the following detailed description in conjunction with the accompanying drawings, in which:

Figure 1 is a partial sectional view of a turbine disc showing turbine blade roots, grooves and steeples made in accordance with this invention; and

Figure 2 is a partial dimensioned view of a dimensional proportional model of a blade root and steeple made in accordance with this invention.

BEST MODE FOR CARRYING OUT THE INVENTION Referring now to Figure 1 in detail, there is shown, a root portion 3 of a turbine blade and a pσrtion of a rotor disc 5 having a blade groove 7 disposed therein. The blade roots 3 have two tangs 9 and 11 on each side thereof. The tangs 9 and 11 have inclined surfaces 13 and 15, respectively, disposed thereon. The grooves 7 which are shaped like the blade roots 3 form steeples 17 which are also shaped like the blade roots 3. The steeple 17

have two tangs 19 and 21 on each side thereof, the tangs 19 and 21 have inclined surfaces 23 and 25, respectively, which engage the inclined surfaces 13 and 15. This engage¬ ment being the only areas of contact between the blade roots 3 and the steeples 17.

The blade roots 3, groove 7 and steeples 17 are the same shape being designed to help minimize stress concentrations due to centrifugal and bending loads. The design is made scalable over a range of sizes. The scal- able two tang side entry turbine blade root geometry herein described significantly reduces stress concentrations due to centrifugal and bending loads as compared to existing designs. An important improvement being due to the ratio of the inner versus outer radii contiguous with the in- clined surfaces which is two in this design as opposed to

*one in previous designs. This ratio results in a more efficient use of material by equalizing the stress at all points of stress concentration. Finite element stress analysis has shown reductions., in the maximum stress up to 28% for centrifugal loads and up "to 30% for bending ^" loads.

The method of making the side entry turbine blade root 3, groove 7 and steeple 17 comprises the steps of: forming the blade roots 3, groove 7 and steeples

17 so that they all have the same shape; forming the blade roots 3 and steeple 17 so that they each have two tangs 9 and 11 and 19 and 21, respec¬ tively on each side with an incline surface 13 and 15 and 23 and 25, respectively, on each tang, these inclined surfaces being the only contact area between the blade roots 3 and the steeples 17 and being generally disposed at an angle of 25° with respect to a line normal to the center line of the blade root; providing the proportional dimensioned model shown in Figure 2 to form a blade root and steeple wherein the stresses are equalized at all points of stress concen¬ tration within the blade root and steeple;

setting the radial distance between the center of the inclined contact surfaces on the blade roots as C, a constant, setting the center of the radially outer inclined contact surface at 0.6203C from the central axis of the root, setting the center of the radially inner contact surface at 0.3797C from the central axis of the root, setting the center of the radially inner inclined surface

0.4990C from the radially inner end of the blade root and setting the other dimension at C times the numbers shown in Figure 2 to produce a set of blade roots, grooves and steeples in which all points of stress concentration are equalized within each set of blade roots, and steeples as they are scaled up or down by varying the constant C which is equal to the distance between the central portion of the inclined surfaces projected at right angles to the center line of the blade root and generally equal to the distance between the center line of the steeple and the center line-. of the blade root at the location of the central portion of

^• the radially inner inclined surfaces. The specific dimen- sions indicted above and in Figure 2 have been identified as providing optimum stress characteristics during the operation of a turbine blade manufactured according to the teachings of my invention.