Turbo Machine Blading

The field of this invention is turbo machine blading and methods. More particularly, this invention relates to fluid energy reactive blading for a rotatable blade wheel of a combustion turbine engine.

The most pertinent conventional turbo machine blading known to the applicant is illustrated in U.S. Pat. Nos. 2,971,743; 3,185,441; and 3,479,009. Because the last of these patents is perhaps the most relevant to this invention, a brief discussion of the blading illustrated by this patent follows in order to afford the reader with an understanding of a few of the deficiencies of conventional turbo machine blading.

Upon examination of the turbo machine blading illustrated in U.S. Pat. No. 3,479,009, it will be noted that each of the blades includes a circumferentially extending shroud section which is generally S-shaped to define axially and radially extending curvilinear abutment surfaces. The abutment surfaces of each shroud section interlock with the matching abutment surfaces of next adjacent blades so that a substantially continuous shroud is defined by the interlocking shroud sections. Because the curvilinear abutment surfaces of the shroud sections extend axially, a radial projection of these shroud surfaces toward the axis of blade wheel rotation intersects with the platform or base of the respective blades. Consequently, when these abutment surfaces are formed during manufacture of a blade, the forming tool must be advanced to form the abutment surfaces and then be retracted before the tool engages and damages the blade platform. For example, if the curvilinear abutment surfaces are formed by the use of a grinding wheel dressed to a matching shape, the grinding wheel must be passed radially inwardly relative to the shroud section to generate the abutment surfaces thereon, be stopped, and then be retracted radially outwardly. Such an advance-stop-retract type of machining operation is time consuming and costly. Thus, because turbo machines usually contain many blades, the cost of machining the blading can be a significant portion of the total manufacturing cost for the turbo machine. Further, such a machining operation has the potential for damaging a blade if the machining tool is advanced too far and cuts into the blade platform.

A further aspect of manufacturing conventional turbo machinery blading involves obtaining a reference position of a blade preparatory to performing machining operations on the blade. Conventionally, a fixture is used which supports the blade, at least in part, by engaging the airfoil or bucket portion of the blade. The blade may additionally be supported by the fixture engaging another portion of the blade. For example, the fixture may also engage the platform portion of the blade. In any case, fixturing which engages the airfoil or bucket portion of a blade is necessarily complex and expensive because of the complex nature of the airfoil or bucket surface which the fixture must engage. Additionally, this type of fixture may damage the airfoil or bucket portion of a blade so that the blade must be scrapped.

This invention provides turbo machinery blading and methods which by their nature greatly facilitate simplified and low-cost serial manufacturing of the blading. Specifically, the shroud section of each blade on a blade wheel defines end surfaces which confront complementary end surfaces of adjacent blades. The end surfaces define abutment surfaces engageable with like abutment surfaces on adjacent blades; and which cooperate to define a radially extending transverse plane relative to the rotational axis of the blade wheel. Consequently, a projection of the end surfaces radially inwardly does not intersect the platform of the blade. As a result, during manufacturing of a blade according to the invention, a forming tool for forming the end surfaces of the shroud section may be moved in a single direction relative to the blade. For example, if a shape-dressed grinding wheel is to be used to form the abutment surfaces, a pair of such wheels rotating in a common plane and separated by an appropriate distance may be used. By passing a blade between the grinding wheels in a single direction in the plane of the grinding wheels, the pair of grinding wheels will form the abutment surfaces precisely and quickly; and at a very low cost.

According to a specifically described preferred embodiment of the invention, a turbine blade for a combustion turbine engine includes three cooperating physical features at novel predetermined locations on the blade. The three physical features cooperate to define a reference plane coextensive with the blade. The three physical features are positioned on the blade so as to cooperate with a fixture in a novel way to hold the blade for machining of the shroud section end surfaces and of other surfaces of the blade. Because the three physical features are located on the blade in novel locations, a single fixture may be used to hold the blade during all required machining operations. Consequently, manufacturing costs are reduced by the invention while the expense of multiple fixtures is eliminated. Further, complex fixturing of the type which engages the airfoil portion of the blade is rendered unnecessary by the invention.

In the light of the above, it is easily appreciated that this invention provides turbo machine blading and methods which significantly reduce the manufacturing costs of such turbo machines. Consequently, the invention may make the advantages of turbo machines, such as combustion turbine engines, available to the public at a lower cost than has heretofore been possible.

FIG. 1 depicts a fragmentary view of a blade wheel of a combustion turbine engine; viewed radially inwardly toward the rotational axis of the blade wheel;

FIG. 2, depicts an isolated perspective view of one of the blades carried by the blade wheel illustrated by FIG. 1; and

FIG. 3 is an enlarged fragmentary cross sectional view taken along line 3--3 of FIG. 1.

FIG. 1 illustrates a preferred embodiment of the invention wherein a combustion turbine engine 10 includes a blade wheel 12 (only a rim portion of which is visible in FIG. 1). The blade wheel 12 is rotational about an axis (represented by lines A--A) and defines a multitude of axially and circumferentially extending slots 14 which receive a multitude of circumferentially adjacent blades 16 extending radially outwardly on the blade wheel 14 (only one complete blade 16 being visible in FIG. 1).

Viewing FIGS. 1 and 2 it will be seen that each blade 16 includes a platform section 18. When the blade 16 is received in a slot 14 of the blade wheel 12, a radially outer arcuate surface 20 of the platform section aligns with a peripheral surface 22 of the blade wheel. The platform section 18 includes a radially inwardly and axially extending root section 24 of the "fir tree" type. A number of axially extending surfaces 26 are defined by the root section 24 for interlocking engagement with the blade wheel 12 at a slot 14. A generally airfoil-shaped portion 28 extends radially outwardly span-wise from the platform section 18. The airfoil portion 28 is span-wise twisted and defines a leading edge 30, a trailing edge 32, and convex and concave surfaces 34 and 36, respectively, extending between the leading and trailing edges.

Of course, it will be understood that the portion 28 of blade 16 may be airfoil-shaped, as illustrated, to operate according to reaction principles or may be shaped to operate according to impulse principles. Alternatively, the portion 28 may be shaped to operate according to a combination of both reaction and impulse principles. Regardless of the shape of the portion 28, it is designed to operate in energy-transfer relation with a fluid in the engine 10 so that the blade portion 28 is fluid energy reactive.

Each blade 16 includes a circumferentially extending integral tip shroud segment 38. Viewing FIG. 1, it will be seen that the tip shroud segments of circumferentially adjacent blades 16 cooperate to define a substantially continuous annular tip shroud which is spaced radially outwardly of the blade wheel periphery 22. A pair of circumferentially extending and axially spaced apart integral knife-edge elements 40 and 42 are carried by the shroud segments 38. The knife-edge elements 40 and 42 extend radially outwardly to sealingly cooperate with other structure (not shown) of the turbine engine 10 so as to prevent fluid leakage radially outwardly of the shroud segments 38.

Each shroud segment 38 defines oppositely circumferentially disposed end surfaces 44 and 46 which are somewhat similarly S-shaped (albeit, a backwards `S` viewing FIG. 1). The end surfaces 44 and 46 extend axially and radially to confront one another and define a clearance `C` therebetween, viewing FIGS. 1 and 3. However, portions 48 and 50 of the end surfaces 44 and 46, respectively, extend circumferentially to define an abutment surface engageable with the corresponding surface of the next adjacent blade. The abutment surfaces 48 and 50 cooperate to define a radially extending transverse plane (as represented by line P--P, viewing FIG. 1) relative to the rotational axis A--A.

Viewing the figures, it will be noted that each of the platform sections 18 defines a pair of oppositely disposed cone-shaped protrusions 52 and 54 extending substantially axially therefrom. Further, the tip shroud segment 38 defines a radially extending cone-shaped protrusion 56 between the knife-edge elements 40 and 42. The protrusions 52-56 cooperate to define a reference plane coextensive with the blade 16.

During operation of the turbine engine 10, the blade wheel 12 rotates at a high rate of speed. Consequently, the blades 16 are subjected to a strong centrifugal force. As a result of the centrifugal force, the air foil portion 28 of each blade attempts to untwist, imposing a clockwise torque on each of the shroud segments 38 (represented by arrows `T`, viewing FIG. 1). Because of the torques T on the shroud segments 38, the abutment surfaces 48 and 50 of circumferentially adjacent shroud segments are biased into engagement. In this way, the torque on each shroud segment 38 is counterbalanced by the torque of the adjacent shroud segments. Additionally, the engaging surfaces 48 and 50 act to frictionally damp any blade vibrations in a circumferential direction.

Having observed the structure and operation of the engine 10, attention may now be directed to the way in which the structure of the blades 16 results in many manufacturing simplifications and economies. The blades 16 are made from inventment castings which require machining to form the surfaces 26 on the root section 24 and to form the surfaces 44-50 on the shroud segment 38. Accordingly, viewing FIG. 2 a fixture (not shown) may be employed to engage the protrusions 52-56 of the blade 16 so that the blade is restrained from movement in all directions relative to the fixture. In order to form the surfaces 26, the fixture with blade 16 therein is passed between a first pair of coplanar shape-dressed grinding wheels in a first direction along a fixed reference line B, which may be visualized as fixed in space. The reference line B is coincident with the protrusions 52 and 54, as the blade is oriented viewing FIG. 2. The first pair of grinding wheels lie in a plane defined by the cooperation of the line B and a mutually perpendicular line C, which may be visualized as having a fixed orientation in space while being movable along line B. Thus, the line C is substantially perpendicular to the reference plane defined by protrusions 52-56, recalling that protrusions 52, 54 are coincident with line B. When the blade 16 is passed between the first pair of grinding wheels they engage the blade to form the surfaces 26. Subsequently, the fixture and blade 16 continue in the first direction along the line B while being rotated approximately 90 degrees in the reference plane defined by protrusions 52-56 about the line C, which is substantially perpendicular to the reference plane, viewing FIG. 2. As a result, the shroud segment 38 is brought into the plane of lines B-C. The blade of FIG. 2 will thus be tipped substantially 90.degree. toward the viewer about line C. Thereafter, the fixture and blade 16 is passed in the first direction along line B between a second pair of shape-dressed grinding wheels which form the surfaces 44 and 46.

Accordingly, it will be understood that the surfaces 44, 46 are generated individually by mutually parallel straight line segments which extend substantially radially, as is best depicted viewing FIG. 3

Observing FIG. 1, it will be seen that a projection of the surfaces 44 and 46 toward the platform 18 does not intersect the platform 18. More particularly, FIG. 2 illustrates that radially inward projections of the surfaces 44, 46 parallel to the radially extending straight line segments which define these surfaces do not intersect with the platform 18. Viewing FIG. 2, the intersections of the radially projected surfaces 44, 46 with a transverse plane at the widest circumferential extension of platform 18 are depicted by phantom lines 44' and 46', respectively. The lines 44', 46' are spaces circumferentially away from and do not intersect the platform 18. Therefore, the fixture and blade 16 may continue in the first direction along line B with the second pair of grinding wheels passing clear of the platform 18. Thus, it is easily perceived that all of the machined surfaces on the blade 16 may be formed during a substantially continuous motion of the blade in a first direction along the line B. Further, it will be understood that the only portions of the surfaces 44 and 46 which are truely radial when the blade 18 is installed upon the blade wheel 12 are the abutable portions 48 and 50. That is, all of the confronting surfaces 44,46, save abutting portions 48,50 of adjacent tip shroud segments 38 are nonparallel when the blades 16 are installed upon blade wheel 12. However, such nonparallelism of surfaces 44,46 is of no detrimental effect because these nonparallel surfaces are spaced apart by clearances C. The abutting surface portions 48, 50 are truly parallel and are engageable to define an area contact for frictional vibration damping and torque resistive interaction between adjacent blades 16. Such is the case, of course, because the surfaces 48, 50 lie on the transverse radial plane P--P, viewing FIG. 1. As pointed out supra, the abutable portions 48 and 50 cooperate to define a transverse radial plane relative to the rotational axis of blade wheel 12.

In light of the above, it is apparent that this invention relates to both turbo machinery blading structure and methods. While this invention has been described with reference to a specific preferred embodiment thereof, no limitation upon the invention should be implied because of such reference. The invention is intended to be limited only by the scope and spirit of the appended claims which alone define the invention.