Abstract: A platform motion restraint for freestanding blades having Christmas tree shaped roots comprising a plurality of L shaped members which fit in circumferential notches machined in the outer portion of rotor steeples, one leg of the L shaped member being forced into the groove under platform portions of the blade to move the blades radially outward and the other leg filling the gap between adjacent blades.

Abstract: An integral control stage blade group for use in a steam turbine having a rotor, the rotor including radially extending flanges provided with opened and smooth faces defining at least one pair of spaced annular grooves. The blade group comprises a plurality of blades attached to a unitary platform. Secondly, the blade group comprises a plurality of root portions depending from the platform in a direction opposite from the blades. The root portions extend along the platform in a circumferential direction when said blade group is mounted on the rotor. Each of the root portions fits within a respective one of the annular grooves in the rotor. Finally, the blade group comprises at least three spaced apertures formed in said root portion and arranged to align with corresponding apertures in the rotor flanges when the blade group is mounted on the rotor.

Abstract: Machine parts are connected together to form an assembly by means of pins which form an interference fit with passages in the parts and whose ends are flush with two opposed surfaces of the assembly. Each pin is provided with an annular groove spaced from one end of the pin by a distance equal to the distance between the opposed surfaces. A positioning member is seated in the groove and the pin is inserted into an associated passage so that the positioning member bears against one opposed surface. After a tight fit is achieved, the protruding portion of the pin is broken away.A device is provided for testing the tightness of an inserted pin. The device may engage the annular groove and apply a tensile test force. Alternatively, after the end of the pin has been broken away, the device may bear against the end of the remaining pin portion and apply a compressive test force.

Abstract: A method of assembling side entry control stage blades in a rotor of a steam turbine, each blade including a cover, an airfoil, a platform and a root. The cover and the platform of each blade include leading and trailing surfaces which abut mating surfaces of the cover and the platform of an adjacent blade. The blades are installed in the turbine rotor, each blade centerline aligned along a radial line of the rotor. To establish tight contact between adjacent covers and between adjacent platforms, a wedge is inserted between the top of a rotor steeple and a bottom of a blade platform along one side of each blade. A shroud is riveted onto the covers of adjacent control stage blades which maintains the tight contact established by the wedges. The wedges are removed afer shroud attachment. The leading and trailing surfaces in one form may have an arcuate shape to provide better shock transfer in more than one direction.

Abstract: Method and apparatus for assembling integral platform blade groups to a rotor of a steam turbine in which the platform roots are skewed with respect to the axis of the turbine. The platform roots are formed to define a set of spaced grooves and steeples are formed on the rotor to mate with the platform roots. Grooves on the platform and in the rotor are alignable to accept a connecting member when the steeples are aligned in abutting relationship with platform roots. The connecting member joins the blade group to the rotor. In one form, the bearing surfaces of the steeples, roots and connecting member are formed to lie on one or more circles circumscribing the rotor axis.

Abstract: A turbine blade having a bilaterally symmetrical side entry blade root for attaching the blade to a rotor of a steam turbine. The rotor has a longitudinal rotational axis of symmetry about which the blades rotate. The blades have a foil portion and a platform interposed between the foil portion and the blade roots. The roots are positionable in one of a plurality of complementary shaped grooves circumferentially disposed about the turbine rotor. The root is characterized by at least one pair of lugs symmetrically arranged on opposite sides of the root with each of the lugs having an outer bearing surface for reacting against a complementary opposed mating surface formed in each of the rotor grooves. The bearing surfaces on the lugs are aligned along an arc of a circle centered on the rotor rotational axis.

Abstract: Apparatus and method for installing an array of rotatable turbine blades each having an integral shroud segment. A removable blade anchor for installing the turbine blades comprises a root portion positionable in registry with a turbine rotor blade groove, a support member extending from the root portion for supporting a first of the blades to be installed and an anchor support extending from the support member and positionable against the rotor to secure the support member against circumferential forces. The installation method comprises the steps of positioning the removable blade anchor in a rotor groove and then wedging a plurality of blades in place about the rotor so that the integral shroud segment of each blade abuts an adjacent integral shroud segment and all shroud segments are forced against the blade anchor. Next, a first portion of the blades are rewedged in order to force the first portion of blades away from the blade anchor.

Abstract: A steam turbine of the type employing axial entry blades is provided with a plurality of generally tangentially oriented slots in the rotor steeples. Resilient, deformable pins are driven into the slots under the blade platforms so as to urge the blade roots radially outward.

Abstract: A steam turbine of the type employing axial entry, integral shroud blades has a pin disposed between adjacent shrouds that extends into tangentially oriented holes in the opposing faces of adjacent shrouds. The pins reduce blade flop during turning gear operation and reduce blade vibration during operation under load.

Abstract: A method is provided for forming a circular array of rotatable blades from blades having an integral shroud with a leading planar surface and a trailing planar surface, the leading planar surface being generally parallel to an axial radial plane passing through the center of the root of the blade and the trailing surface, if extended, intersecting the axial radial plane passing through the center of the root of the blade to form an angle generally equal in degrees to 360 divided by the number of blades forming the circular array. Strict radial alignment is provided by assembling the complete blade row such that all blade center lines coincide with the groove center lines, with the shroud mating surfaces in complete contact and in tangential compression.

Abstract: A gage for determining alignment of a turbine rotor blade in an assembly position on a turbine rotor. The gage includes a precision base for positioning on the rotor surface adjacent a blade to establish a tangent line perpendicular to a rotor radial line through the center of a slot in which a blade is disposed. A standard extends from the base and carries a first contact for positioning against a low portion of the blade and a second measuring contact for positioning against an upper portion of the blade. The measuring contact provides an indication of blade misalignment.

Abstract: A circular array of rotatable blades formed from blades having an integral shroud with a leading planar surface and a trailing planar surface, the leading planar surface being generally parallel to an axial radial plane passing through the center of the root of the blade and the trailing planar surface, if extended, intersecting the axial radial plane passing through the center of the root of the blade to form an angle generally equal in degrees to 360 divided by the number of blades forming the circular array.

Abstract: A circular array of rotatable blades formed from blades having an integral shroud with a leading planar surface and a trailing planar surface, the leading planar surface being generally parallel to an axial radial plane passing through the center of the root of the blade and the trailing planar surface, if extended, intersecting the axial radial plane passing through the center of the root of the blade to form an angle generally equal in degrees to 360 divided by the number of blades forming the circular array.

Abstract: A plurality of rotatable turbine blades are formed integral with a shroud and platform and a plurality of arcuate plate root portions which are received by circumferential grooves in a rotor and are fastened to the rotor by three pins extending axially through the root portions and the rotor, the shroud and platform portions having a protrusion on one corner to support the trailing edge of one of the blade portions and a notch in the shroud and the platform on the corner opposite the protrusion whereby the protrusions on one group of blades register with the notch on an adjacent group of blades when the groups of blades are disposed in a circular array on the rotor.

Abstract: A multiple number of rotatable, axial flow turbine blades having a common platform and shroud portion from which two arcuately separated, axially extending, side entry roots protrude radially inwardly toward the axis of rotation of a rotatable shaft.

Abstract: A plurality of rotatable turbine blades are formed integral with a shroud and platform and a plurality of arcuate plate root portions which are received by circumferential grooves in a rotor and are fastened to the rotor by three pins extending axially through the root portions and the rotor, the shroud and platform portions having a protrusion on one corner to support the trailing edge of one of the blade portions and a notch in the shroud and the platform on the corner opposite the protrusion whereby the protrusions on one group of blades register with the notch on an adjacent group of blades when the groups of blades are disposed in a circular array on the rotor.