Rockwell International Corporation

The Boeing Company

Pratt & Whitney Rocketdyne, Inc.

United Technologies Corporation

Boeing North American, Inc.

Borealis Technical Limited

Maynard Leo Stangeland

Ronald Urquidi

Gary Alan Davis

Eric J Krieg

Roger Eric Berenson

Jonathan Sidney Edelson

Clifford C Bampton

Robert F Beatty

Steven C Fisher

Donald Henry Morris

William R Bissell

Jeffry A Fint

Douglas S Ades

Michael B Hankins

Robert Lincoln Carman, Jr

William C Bowling, Jr

Brian W Lariviere

Paul R Winans

Jacob Rietdyk

Theodore C Adams

Roger E Berenson

A method for building a component for an electrical rotating machine is provided. The method includes providing a powdered magnetic material and an electrically conductive material, positioning these materials within a mold selected to produce the required dimensions in the materials after the application of a hot isostatic pressing (HIP) procedure, and applying at least one HIP procedure to the materials in the mold. Temperatures and pressures of the process are chosen to ensure that the electrically conducting and magnetic portions of the component are bonded without the materials seeping into each other. The method may be employed to build small compact motor systems using motor components formed as described to produce uniform grain structure and consistent magnetic and structural properties in the motor components that are useful in vehicle drive wheels.

Method for building a component of an electrical rotating machine

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.

Spherical flange assembly

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.

Turbine blisk rim friction finger damper

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.

Inducer tip vortex suppressor

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.

Rocket engine combustion chamber having multiple conformal throat supports

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.

Turbine blade tip shroud enclosed friction damper

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.

Method of making rocket engine combustion chamber utilizing 'slide in'

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.

Integrated turbine and pump assembly

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.

Flying wedge (centripetal retractor) assembly

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.

Axially fed hydrostatic bearing/seal

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.

Gradated hydrostatic bearing

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.

Growing community of inventors

Thousand Oaks, CA, United States of America

Maynard Leo Stangeland