Abstract: A spherical flange assembly is disclosed. The spherical flange assembly comprises a seat member, a heel member, a seal gland and at least one nut and bold assembly. The seat member includes a concave portion. The heel member includes a convex portion and a seal gland opening. The seal gland is disposed within the seal gland opening.

Abstract: Embodiments of the invention provide a method, device, and turbopump configured to suppress higher order cavitations at an inducer tip in a turbopump. An inducer having a tip is rotated, and a first flow is induced axially through the inducer at a first velocity. A second fluid flow is introduced toward a tip of the inducer substantially parallel to the first fluid flow at a second velocity that is greater than the first velocity, such that back flow through the tip of the inducer is reduced.

Abstract: In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed. The two inner conformal throat support sections are formed around the outside surface of the coolant liner to form a closed inner conformal throat outside surface. The inner conformal throat support sections are joined at inner throat seam lines. At least two outer conformal throat support sections are assembled around the closed inner conformal throat outside surface so as to cover the inner throat seam lines, to form a liner throat support assembly. An inlet manifold and an outlet manifold are assembled around the liner throat support assembly to form a hot isostatic press (HIP) assembly. A HIP'ed assembly is formed by HIP'ing the HIP assembly.

Abstract: In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed. The two inner conformal throat support sections are formed around the outside surface of the coolant liner to form a closed inner conformal throat outside surface. The inner conformal throat support sections are joined at inner throat seam lines. At least two outer conformal throat support sections are assembled around the closed inner conformal throat outside surface so as to cover the inner throat seam lines, to form a liner throat support assembly. An inlet manifold and an outlet manifold are assembled around the liner throat support assembly to form a hot isostatic press (HIP) assembly. A HIP'ed assembly is formed by HIP'ing the HIP assembly.

Abstract: A damper for reducing vibrations in an integrally bladed turbine disk is provided. The damper includes an annular member and a plurality of fingers. The annular member is configured so that it is coupled to a face of the integrally bladed turbine disk. The plurality of fingers are circumferentially spaced around the annular member. Each of the fingers includes a base portion which is coupled to the annular member and extends radially therefrom. Each of the fingers is tangentially movable relative to the annular member when the turbine disk vibrates in a diametral mode shape such that the plurality of fingers contacts a surface of the turbine disk to absorb vibrations.

Abstract: A turbine disk assembly having an integrally bladed turbine disk and a plurality of captured damper members. The integrally bladed turbine disk includes a plurality of turbine blades that terminate at an integral tip shroud. A damper aperture is formed between each pair of adjacent integral tip shrouds and includes a first slotted portion and a second slotted portion. The first slotted portion is formed concentric to the two adjacent integral tip shrouds, extending circumferentially and axially through the two adjacent integral tip shrouds. The second slotted portion extends radially outwardly between the two adjacent integral tip shrouds. One of the damper members is disposed in the first slotted portion of the an associated damper aperture and frictionally engages at least one surface of each of the two adjacent tip shrouds to dissipate energy when relative motion occurs between the two adjacent integral tip shrouds to dampen vibration.

Abstract: A method of fabricating a rocket engine combustion chamber comprising assembling a liner having cooling channels, a plurality of throat support sections, and a structural jacket having inlet and outlet manifolds. Then heating the assembly in a pressurized furnace to bond the assembled parts to each other.

Abstract: A turbopump assembly comprises first pump section housing, a second pump section housing, and a common rotatable shaft positioned within said housings which further define First and second pump sections. The housings and rotatable shaft also define internal manifolds selectably positioned in the first pump section and second pump section whereby said first pump section, second pump, and internal manifolds form an integrated turbine and dual pump configuration.

Abstract: The flying wedge clutch assembly is a speed actuated coupling device that provides low speed axial load and torque transmission and disengages for increased shaft motion at higher speeds. The flying wedge clutch assembly is a compact and lightweight design, roughly equivalent to a conventional ball bearing assembly in a typical turbopump application. Advantageously, the flying wedge clutch assembly can be used in high speed rotating machines with radial hydrostatic bearings eliminating the speed and life limitations normally attributed to rolling element bearings.

Abstract: This invention relates to a hydrostatic bearing having a journal 3 annularly circumscribed by a bearing 2 wherein a high pressure fluid is forced between the bearing and the journal axially. The high pressure fluid flowing axially along the journal in the bearing keeps the journal centered. A roughened or diamond knurled 11 inside surface interrupts the circumferential and axial flow of the fluid for improved rotor stability and less leakage. Other features include a tapered inner bore 9 to increase the bearing stiffness and a sharp edged inlet for greater control of the bearing stiffness and damping. The axially fed hydrostatic bearing combines the seal function and the bearing function for annular fluid flows along a journal.

Abstract: A bearing assembly includes a bearing characterized by a gradated composition such that the bearing transitions from a metallic substrate such as high strength steel to an inner layer of silver, ceramics, or diamond-like material wherein the thermal coefficient of expansion as between the bearing and a rolling element or shaft is matched.

Abstract: A bearing assembly including an inner race element and an outer race element each having raceways therein, the gradated race matrixes making up the composition of the race elements such that each race element transitions from a metallic substrate such as steel to an outer wear resistant layer such as silicon nitride.

Abstract: A variable inlet for a marine jet propulsion system comprising a movable lip, a center splitter serving to divide said inlet into upper and lower passages and coupled for movement proportional to that of said lip to assure equality of the areas of said upper and lower passages, and apparatus for varying the outward projection of said splitter to vary the diffusion ratio of said upper and lower passages.

Abstract: This device comprises a flexible sheet member having cross convolutions oriented 45.degree. to the shear vector with spherical reliefs at the convolution junctions. The spherical reliefs are essential to the shear flexibility by interrupting the principal stress lines that act along the ridges of the convolutions. The spherical reliefs provide convolutions in both directions in the plane of the cross-convolution ridges.

Abstract: An internal thrust reverser duct is utilized in a waterjet pump design which comprises a center pintle body concentric with an outer housing forming an annular passage thereby downstream of an inducer. To divert the flow upstream of the nozzle plane in this configuration passage, a simple device that does not cause a significant loss in efficiency is required. A nozzle plate is axially moved closer to the pintle which simultaneously diverts the flow into an annularly exposed volute positioned upstream of the movable nozzle. The flow is diverted symmetrically and uniformly into the internal reversing duct. The velocity head is not lost in either of the flow that enters the volute or the flow that continues to pass through the movable nozzle.

Abstract: This device comprises a flexible sheet member having cross convolutions oriented 45.degree. to the shear vector with spherical reliefs at the convolution junctions. The spherical reliefs are essential to the shear flexibility by interrupting the principal stress lines that act along the ridges of the convolutions. The spherical reliefs provide convolutions in both directions in the plane of the cross-convolution ridges.

Abstract: A damper for reducing vibrations in an integrally bladed turbine disk is provided. The damper includes an annular member and a plurality of fingers. The annular member is configured so that it is coupled to a face of the integrally bladed turbine disk. The plurality of fingers are circumferentially spaced around the annular member. Each of the fingers includes a base portion which is coupled to the annular member and extends radially therefrom. Each of the fingers is tangentially movable relative to the annular member when the turbine disk vibrates in a diametral mode shape such that the plurality of fingers contacts a surface of the turbine disk to absorb vibrations.