Abstract: An apparatus for stabilizing a shaft in an essentially horizontal position while an anchoring object at one end of the shaft is replaced without removal of an object at the opposite end of the shaft that would otherwise tend to destabilize the shaft from its essentially horizontal position includes a half-spool member configured to clamp above and around the shaft to resist torque around the rotor, under supports configured to attach to the half-spool member and clamp an underside of the shaft below the half-spool member, and a hydraulic or mechanical brake configured to resist torque on the shaft when the brake is engaged.

Abstract: A gas turbine engine component is disclosed having a construction that permits a working fluid to flow from one side of the component to the other. In one embodiment the construction includes multiple layers, and in one particular embodiment the construction includes three layers. One or more layers can have different properties. Additionally, one or more layers of the construction can include a cellular structure. In one embodiment the component is a gas turbine engine combustor liner.

Abstract: A disc valve hydraulic motor assembly is disclosed that includes a rotary valve that rotates in accordance with the motor output shaft and in which a two-pole bolt magnet is mounted in alignment with the center of the rotating valve to rotate with the rotating valve. The end housing of the disc valve hydraulic motor that is spaced from and disposed beyond the rotating valve is provided with a central opening aligned with the magnet. A stainless steel plug is interposed between the sensor and the interior of the motor so that the sensor is separated from the high pressure hydraulic fluid.

Abstract: An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.

Abstract: A Helmholtz damper for a combustor of a gas turbine includes first and second damping volumes. The combustor has a combustion chamber disposed in a housing and closed off by a front plate at which a plurality of burners are exchangeably fastened. The burners are supplied with fuel via fuel lances which extend from outside the housing through a bushing of the housing to the associated burner. The first damping volume has a first end and a second end, the first end of the first damping volume being configured to attach a connecting passage extending to a front panel such that the Helmholtz damper is connectable with the front plate of the combustion chamber in place of one of the burners. The second damping volume has a first end and a second end and is arranged in series with the first damping volume along an axis of the Helmholtz damper with the first end of the second damping volume being detachably connected to the second end of the first damping volume so as to form a combined larger damping volume.

Abstract: An Oldham-style coupling assembly wherein a driving shaft (12) is rotatably coupled to a driven shaft (32) using a reduced-lash flexible coupling assembly. The coupling assembly includes an intermediate coupling plate (38) stationed between the driven (32) and driving (12) shafts. A driven lug (34) associated with the driven shaft (32) has tapered contact faces (36) and engages a driving slot (40) in the center of the coupling plate (38). Likewise, a pair of diametrically opposed half-lugs (18) associated with the driving shaft (12) engage in respective half slots (42) through a similar tapered interface. Springs (28) backing each of the half lugs (18) establish a continuous axial compression force within the coupling plate (38) to urge seating of the tapered interfaces but without frustrating transverse sliding in the respective slots (40, 42), thereby taking up lash from the system. The lugs (18, 34) are oriented perpendicular relative to each other, so as to simulate a traditional Oldham-style coupling.

Abstract: An arrangement including a turbine blade is provided. The turbine blade includes at least a root, an airfoil and a tip which is mounted to a rotor by means of the root. The rotor extends along a machine axis. The arrangement also includes a circumferential casing segment which includes a surface. The surface faces tips of the blades, wherein the surface is structured. A method to produce a casing segment is also provided. In order to increase efficiency without limiting the operational range of the turbine, the surface is provided at least partially with an at least partially ceramic coating. The method includes machining a first structure into the surface and providing the surface with a ceramic coating.

Abstract: A nickel-based superalloy particularly suitable for the fabrication of mechanical components for a piece of turbomachinery that it comprises the following elements in percentage by weight: chromium between 3% and 7%; tungsten between 3% and 15%; tantalum between 4% and 6%; aluminium between 4% and 8%; carbon less than 0.8%; the remaining percentage of nickel plus impurities.

Abstract: A system for enclosing a portion of a wind turbine with an enclosure system and a method of enclosing a wind turbine with the system are described. An inner seal plate is positioned in an inner interface area between a hub of the wind turbine a pitch assembly. An opening is formed in the inner seal plate and is covered with a first access cover when in a closed position. An outer seal plate is positioned in an outer interface area between a pitch assembly and a rotor blade. An opening is formed in the outer seal plate and is covered with a second access cover when in a closed position. The access covers restricts access to the respective openings formed in the seal plates when in the closed position.

Abstract: A system for arranging wind turbine blades includes first and second root cradles and a first tip cradle proximate to the second root cradle, wherein the first tip cradle is angled approximately 30 to 60 degrees with respect to a horizontal line. The system also includes a second tip cradle proximate to the first root cradle, wherein the second tip cradle is angled approximately 30 to 60 degrees with respect to the horizontal line. A method for arranging wind turbine blades includes transferring a first wind turbine blade to a first root cradle and transferring a second wind turbine blade to a second root cradle. The method further includes rotating at least a portion of the first wind turbine blade about at least a portion of the second wind turbine blade.

Abstract: A joined rotor that includes a primary join and a locking device and a method for joining thereof is disclosed. The primary join includes a threaded boss that is inserted in a tapped cavity formed in an adjacent rotor section. The primary join is locked, so as to prevent unscrewing, by at least one locking member that is located partially in both first and second rotor sections. This arrangement enables the join to be locked at a desired torque point.

Abstract: A thermal machine is provided, in particular a gas turbine, which includes an annular combustion chamber which is bounded on the outside by an outer shell and an inner shell. The outer shell and the inner shell are each split on a separating plane into an upper half and a lower half, which are mechanically interlocked by welding one to the other on the separating plane. Increased mechanical robustness and a longer life of the combustion chamber are achieved in that an additional mechanical interlock is provided on the separating planes in order to absorb tensile and shear forces acting on the separating planes.

Abstract: A method of assembling a fuel nozzle assembly for a gas turbine engine having a natural operating frequency includes providing a flange and providing a premix tube. The flange is fabricated from a first alloy such that the flange is configured to exhibit a first frequency that is different than the natural operating frequency of the gas turbine engine. The premix tube is fabricated from a second alloy such that the premix tube is configured to exhibit a second frequency that is different from the natural operating frequency of the gas turbine engine. The premix tube is coupled to the flange.

Abstract: A method for repairing an ex-service gas turbine component (10) includes the steps of: removing a damaged section (13) from the gas turbine component (10), manufacturing a 3-D article, which fits in the gas turbine component (10) to replace the removed damaged section (13), and joining the gas turbine component (10) and the 3-D article inserted therein. Reduced cost, improved flexibility and productivity, and simplified handling are achieved by removing the damaged section (13) in the form of a cut-out section along a split line (14) as one single cut-out piece (15), measuring the cut-out piece (15) to obtain the actual non-parametric geometry data set of the cut-out piece (15), and manufacturing the 3-D article based on the geometry data set of the cut-out piece (15).

Abstract: A method of making a turbomachine part, wherein the can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can also include forming a bridge in the channel between the blades, and forming a cover on the tops of the blades and over the channel, such that the base, the blades, and the cover form a single substantially homogenous turbomachine part once the bridge is removed.

Abstract: A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10).

Abstract: In a brazing repair material 3 which is charged into a repairing portion of base material 1 in which a failure such as a crack 2 and corrosion is generated, diffusion heat treatment is carried out, the brazing repair material 3 is integrally bonded to the repairing portion to repair the repairing portion, the brazing repair material 3 comprises a mixture of non-molten alloy powder having a composition similar to that of the base material 1 and molten alloy powder which is melted at a temperature of the diffusion heat treatment, and the molten alloy powder is brazing repairing alloy consisting of 0.001 to 0.05 mass % of C, 2 to 5 mass % of Si, 10 to 25 mass % of Cr, 15 to 25 mass % of Co, 1 to 5 mass % of B, and balance of Ni, and excluding Al. With this configuration, a part having a failure such as a crack can restore original characteristics like the inherent base material.

Abstract: A secondary fuel nozzle includes a plurality of tubes axially extending downstream within the secondary fuel nozzle, the tubes defining passages operable to allow a flow of fluid to flow through each of the passages, the passages including an outermost tertiary passage and a radially inner secondary fuel passage. The secondary fuel nozzle also includes a fuel peg extending radially outward from the axially extending tubes, the fuel peg operable to emit a fluid radially outward therefrom. The secondary fuel nozzle further includes a crossover manifold attached to the fuel peg and in fluid communication with the radially inner secondary fuel passage and the fuel peg, wherein the crossover manifold is attached to the corresponding tubes that define the tertiary passage and the radially inner secondary passage by butt welds.

Abstract: A method of assembling an inlet air filter assembly for use with a turbine engine system. The method includes coupling an inlet hood to an air filter enclosure, such that an airflow path is defined between the inlet hood and the air filter enclosure. A pre-filter is coupled to the inlet hood, such that the pre-filter is positioned within the airflow path. A filter bypass assembly is coupled to the pre-filter for moving the pre-filter from an operating position to a bypass position during operation of the turbine engine system.

Abstract: The invention relates to a method for manufacturing at least a portion of a metal part of a turbine engine having a width L. The method is characterised in that said portion is manufactured by metal deposition using a MIG welding apparatus including a pulsed current generator and a pulsed deposition-wire flow, and used for varying said current and said flow, the manufacture being carried out in the form of metal beads (10) in several consecutive layers.

Abstract: A technique for refurbishing nozzle diaphragm sections of a gas turbine replaces an eroded section of the nozzle diaphragm with a replacement part designed to engage a slot machined in the nozzle diaphragm. The replacement part is formed of a material with capable of sustained exposure to higher temperature than the original eroded section, and with a similar coefficient of expansion as the material used for manufacture the original nozzle diaphragm. The combination of the nozzle diaphragm and the replacement part conform to the original manufacturer's dimensional specifications for the nozzle diaphragm.

Abstract: The present invention provides a Stirling engine employing a segmented, rotary displacer for producing mechanical energy from a heat source. The engine includes a rotor shaft rotatably positioned in the interior toroidal cavity with a segmented displacer mounted to the rotor shaft within the interior toroidal cavity.

Abstract: A pumping system comprising a membrane pump (1) for pumping a medium into or out of a vessel (6), the membrane pump comprising an actuating member (13) for moving a membrane (3) in a first direction from a first end position to a second end position against the action of a spring (12), the membrane being movable in the opposite direction from the second end position to the first end position under the action of the spring. The pumping system comprises sensing means (14) for generating a measuring value representing the location of said first end position of the membrane (3), and processing means (17) for establishing a pressure value representing the pressure inside a vessel (6) connected to an inlet (5) or outlet (24) of a pump chamber (4), the processing means (17) being adapted to establish said pressure value based on said measuring value.

Abstract: A multi-rate torsional coupling (20) features parallel first and second drive connections (82 and 84) between input (24) and output (22) members. The first drive connection (82) extends through a first resilient coupling (38), and the second drive connection (84) extends through a second resilient coupling (40). An angular play coupling (70) engages the second drive connection (84) at a particular torque load for transmitting additional torque through the torsional coupling (20) at a higher spring rate.

Abstract: A method for manufacturing a micropump, which may be for the metered delivery of insulin, multiple layers being situated on the front side of a first carrier layer, which has a front side and a rear side, and microfluidic functional elements being formed by structuring at least one of the layers. It is provided that the structuring of the at least one layer for manufacturing all microfluidic functional elements is exclusively performed by front side structuring. Furthermore, a micropump is disclosed.

Abstract: The present invention provides a method of producing a common rail having a common rail body and a holder which include chemical components of 0.01-0.3 mass % of C, 0.01-0.5 mass % of Si, 0.01-3.0 mass % of Mn, 0.0003-0.01 mass % of B, 0.001-0.01 mass % of N, over 0.01-0.5 mass % of Al, 0.01-0.05 mass % of Ti, P limited to 0.03 mass % or less, S limited to 0.01 mass % or less, O limited to 0.01 mass % or less, a total content of As, Sn, Sb, Pb, and Zn limited to 0.015 mass % or less, the balance including Fe and inevitable impurities, in which the TLB value is 0.001% or more, the method including: inserting an insert metal; performing liquid phase diffusion bonding; performing laser-peening; and removing a surface layer.

Abstract: A method of assembling a gas turbine engine is provided. The method includes coupling a combustor in flow communication with a compressor such that the combustor receives at least some of the air discharged by the compressor. A fuel nozzle assembly is coupled to the combustor and includes at least one fuel nozzle that includes a plurality of interior surfaces, wherein a thermal barrier coating is applied across at least one of the plurality of interior surfaces to facilitate shielding the interior surfaces from combustion gases.

Abstract: The invention provides a ring, rotatable duct, shroud, fuselage or cylindrical external wall fabricated so as to have desirable strength even if its diameter exceeds about 2.7 meters by using arbitrary metallic and non-metallic materials. Such ring and others may be readily fabricated by laminating a thin sheet band made of metal, ceramics, cermet, fiber or synthetic resin of 0.01 mm to 5 mm thick or a thin sheet band made of rubber or silicon of 0.1 mm to 50 mm thick by winding around a giant spinning wheel by at least two rounds or more so as to form a longitudinal plate portion of 2 mm or more in radial thickness when the band is made of metal, ceramics, cermet, fiber or synthetic resin and to form such portion of 4 mm or more thick when the band is made of metal, ceramics, cermet, fiber, synthetic resin, rubber or silicon.

Abstract: A gas turbine includes a disk rotatable about a rotational axis, when turbine rotor blades for receiving combustion gas obtained by burning fuel are connected to the side periphery, and energy of the combustion gas received by the turbine rotor blades is transmitted, and a radial passage that, in a cross-section at a virtual curved plane that is a curved plane about the rotational axis and in which distances from all points on the curved plane to the rotational axis are all equal, is a hole formed to include a portion having a shape in which the length in the circumferential direction of the disk is longer than the length in the direction parallel to the rotational axis, and is formed in the disk from the side of the rotational axis toward the outside of the disk.

Abstract: A contribution is made to the assembly of a wind turbine intended to comprise, in a final assembly condition, a tower (2) surmounted by a nacelle (4) cooperating with a rotor (5) receiving a plurality of blades (3a-3c). To this end, a temporary association is made between at least some blades from said plurality of blades and the tower, so that said blades extend substantially in the longitudinal direction of the tower.

Abstract: A method and apparatus for removing and installing combustion liners in a combustion case of a turbine is provided. The apparatus includes an elongated handle having a pin disposed at one end, and a bracket attached to the elongated handle. A tower clamp, for attaching to a flange of a combustion case, includes a tower portion having a plurality of notches for receiving the pin of the elongated handle.

Abstract: A fiber-optic dynamic sensing module comprises a support member, a beam extending from the support member, and a pre-strained fiber Bragg grating sensor and a strain-free fiber Bragg grating sensor mounted on the beam. The pre-strained and strain-free fiber Bragg grating sensors each comprise a Bragg grating inscribed in a fiber. The Bragg grating of the pre-strained fiber Bragg grating sensor is packaged more tightly along a longitudinal direction of the beam than the Bragg grating of the strain-free fiber Bragg grating sensor.

Abstract: A method of assembling a steam turbine power system with a coolant source is provided. The method includes providing a first steam turbine train including a first high pressure turbine assembly, a first low pressure turbine assembly coupled in flow communication with the first high pressure turbine assembly, and a first condenser coupled in flow communication with the first low pressure turbine assembly. The method also includes providing a second steam turbine train including a second high pressure turbine assembly, a second low pressure turbine assembly coupled in flow communication with the second high pressure turbine assembly, and a second condenser coupled in flow communication with the second low pressure turbine assembly.

Abstract: A method for manufacturing a power transmitting apparatus by molding both the pressure-contact assist cam and back-torque limiting cam even though either one of the pressure-contact assist cam and back-torque limiting cam is molded as a reverse-draft surface. The power transmitting apparatus has a clutch housing (2) and a clutch member (4) connected to an output member (3). A plurality of driven clutch plates (7) alternately is arranged between the driving clutch plates (6) of the clutch housing. The pressure plate (5) and the clutch member (4) are, respectively, formed with through windows (5c) and (4c) at positions corresponding to the pressure-contact assist cams (4aa) and (5ba) and the back-torque limiting cams (4ab) and (5bb) to form reverse-draft surfaces of the pressure-contact assist cams (4aa) and (5ba) and the back-torque limiting cams (4ab) and (5bb) by inserting pin-shaped cores into the windows (5c) and (4c).

Abstract: A method for assembling a turbine engine to facilitate reducing an operating temperature of a lubrication fluid during engine operation, the gas turbine engine including a fan assembly, a booster downstream from the fan assembly, and a splitter circumscribing the booster. The method includes coupling a radially inner wall and a radially outer wall at a leading edge to form a splitter body, and coupling an inner support structure within the splitter body such that a cooling circuit is defined between at least a portion of the inner support structure and the inner and outer walls, said cooling circuit configured to circulate lubrication fluid therethrough such that as a temperature of the lubrication fluid is reduced and a temperature of at least a portion of the inner and outer walls is increased.

Abstract: A fixture includes a housing assembly defined along an axis. A pressure bar assembly is mounted to the housing assembly for movement relative the axis. A bladder assembly is mounted at least partially within the housing assembly such that pressurization of the bladder assembly is operable to exert a force on a workpiece along the axis with the pressure bar assembly.

Abstract: The present invention provides an apparatus and method for an adaptive machining and weld repair process useful for repairing airfoils, particularly damage to an airfoil leading edge and tip. The process first machines away damaged portions of the airfoil. Next, the actual profile of the airfoil subsequent to the removal of the damaged material is measured using a Coordinate Measuring Machine. The data is then used to generate a deformation profile. Filler material is then added to the machined area using the data of the deformation profile to produce an airfoil that approximates the ideal shape of a restored airfoil. At this point, the actual profile of the welded airfoil is measured using the Coordinate Measuring Machine. The data is then used to generate a deformation profile and the airfoil is machined using the date of the deformation profile to produce that shape. The adaptive technology minimizes the amount of stock on material that needs to be removed by hand.

Abstract: A method for manufacturing a hardened casing for a vane pump is disclosed. The method includes providing a vane pump casing; hardening the casing by (i) cleaning the casing with a high pressure fluid containing abrasive material, (ii) loading the casing in a furnace, (iii) purging the furnace with an inert gas followed by purging the furnace with ammonia, (iv) conducting a first heating of the casing in the furnace at a first temperature of about 1200° F. for a time period of about 4 hours, (v) conducting a second heating of the casing in the furnace at a second temperature of about 1000° F. for a time period of about 4 hours, and (vi) cooling the casing and purging the furnace with an inert gas before removing the casing.

Abstract: A linear compressor and a method of producing the linear compressor which do not generate eddy currents in an inside stator of a linear motor thereof, thus preventing an eddy current loss, caused by an electrical contact between a plurality of thin metal sheets of the inside stator. The linear compressor includes a cylinder having a piston therein, a magnet arranged around the cylinder to actuate the piston, and the inside stator arranged around the cylinder to be placed inside the magnet. The inside stator has the thin metal sheets arranged in a cylindrical arrangement, and a holder which is made of a nonconductive resin material and to which the thin metal sheets are insert-molded to be held in positions thereof in the cylindrical arrangement. Due to the nonconductive holder, the thin metal sheets are prevented from being in electrical contact with each other, and the linear compressor does not generate any eddy currents in the inside stator, and prevents an eddy current loss.

Abstract: Gas of a predetermined pressure, which is equal to or higher than the atmospheric pressure, is filled in a damper chamber of a damper member that includes first and second-side diaphragms. A first-side limiting portion of a first-side cover member and a second-side limiting portion of a second-side cover member are engageable with a first-side concave portion of the first-side diaphragm and a second-side concave portion of the second-side diaphragm, respectively, to limit bulging of the damper member when a pressure of a fluid chamber is equal to or less than the predetermined pressure.

Abstract: An element which generates a magnetic field for securing a compressor wheel to a turboshaft of an exhaust-gas turbocharger, includes a base body that receives an annular-shaped magnet that rotates with the turboshaft. In order to provide an element which generates a magnetic field for securing a compressor wheel to a turboshaft of an exhaust-gas turbocharger, where the magnet is securely fixed and no change in the distribution of mass in the magnetic field occurs even when the magnet breaks, the magnet is connected in a force-fitting manner to the base body.

Abstract: A combustor liner assembly support is provided that is used to axially and radially position combustor liners in a gas turbine engine. The combustor liner support includes, in one embodiment, a support bracket that is coupled to a diffuser located upstream in the gas turbine engine; a support spool coupled to the support bracket; and a mount stake coupled to the support spool. The mount stake is connected to the combustor liners and maintains the spaced relation therebetween. An alignment device can be used between the support bracket and the support spool.

Abstract: A method for preventing cracking of a turbine engine case includes the steps of disposing at least two rails upon an exterior surface of a turbine engine case; and securing a first rail to a first means for attaching at least one fan exit guide vane to the turbine engine case and securing a second rail to a second means for attaching the at least one fan exit guide vane to the turbine engine case.

Abstract: A method for forming an impeller for a pump provides a reliable protective barrier that prevents or eliminates the ingress of pumped fluid that might otherwise attack the magnetic assembly of the impeller. An inner barrier is hermetically connected to an internal impeller section at one or more seams to cover at least part of a first magnetic assembly. Filler is introduced into a spatial volume of the first magnet assembly associated with the internal impeller section. The remainder of an impeller is molded over or in association with the internal impeller section to form the impeller with the inner barrier and an outer barrier overlying the inner barrier for protection of the first magnet assembly from the pumped fluid.

Abstract: A plenum air regulating system includes a housing and a blower deck assembly. The housing having at least one side-panel removably mounted on the housing and a door assembly mounted on one end of the housing. The door assembly is coupled with a wire guard and is capable for air circulation. The blower deck assembly is mounted inside the housing. The blower deck includes a blower deck mount, a blower housing, and heating elements. The blower housing is mounted on a first side of the blower deck mount. An internal motor is removably coupled within the blower housing. The blower deck mount is disposed at an angle inside the housing, such that the blower housing is at an angle relative to the bottom of the housing. The blower deck mount is tilted at an angle between 95 to 135 degrees. The blower deck mount is rotated at its midpoint by between 5 to 45 degrees.

Abstract: A centering mechanism for a hydraulic pump, a hydraulic pump assembly and a method of assembling a hydraulic pump assembly. The pump assembly generally includes a hydraulic pump, a control arm, and a centering mechanism. The pump generally includes a pump housing, a pump mechanism operable to control a flow of hydraulic fluid through the housing, the pump mechanism having a neutral condition in which fluid does not flow through the housing, a trunnion cap connectable to the housing, the trunnion cap and the housing cooperating to house the pump mechanism, and an input shaft extending along an axis and through the trunnion cap, the shaft being rotatable to operate the pump mechanism. The control arm is connected to the shaft, and movement of the control arm causes rotation of the shaft.

Abstract: A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising: making a fiber preform (100) out of refractory fibers and having a shape corresponding to the shape of the lobed structure to be fabricated, from a plurality of component elements of fiber texture that are assembled together and shaped by means of tooling of a shape corresponding to the shape of the lobed structure to be fabricated so as to obtain an assembled fiber preform having a first preform portion (111) corresponding to the annular portion of the lobed structure and a second preform portion (112) corresponding to the multilobed skirt of the lobed structure, the component elements of the fiber preform being assembled together at least in part along connection lines (121) extending substantially in the flow direction of the flow past the lobes of the multilobed skirt preform portion; and densifying the assembled an

Abstract: At the time of manufacturing an inflator, a blocking body is first disposed at an opening so as to allow the interior and the exterior of a housing to communicate with each other. The blocking body is abutted against a peripheral edge of the opening so as to ensure sealability between the blocking body and the peripheral edge of the opening. A filling nozzle injecting a pressurized gas is then pressed against a periphery of an inlet port of the blocking body, and the pressurized gas is injected from the filling nozzle so as to fill the pressurized gas into the housing through a filling channel. Subsequently, to block the filling channel, the blocking body is energized with a resistance-welding current to resistance-weld an inner peripheral portion of the filling channel. At the same time, the blocking body is fixed to the peripheral edge of the opening by resistance-welding so as to maintain sealability, thereby manufacturing the inflator.

Abstract: A method of manufacturing a thin wall isogrid or the like casing by a machining process includes the steps of mating a casing with a support, the said support having a substantially continuous support surface engaging at least part of the inner or outer surface of the casing and machining a plurality of recessed pockets in the inner or outer surface of the casing opposite the surface engaged by the said support. The support reacts loads acting on the casing by a machining tool during machining, thereby minimizing distortion of the casing and tearing of the pockets being formed. During the mating process, the casing is deformed such that the support surface engages substantially the whole of the inner or outer surface of the casing.

Abstract: A method and a conversion kit are provided for assembling marine propulsion systems such as those comprised of a Mercruiser Alpha-One-type sterndrive unit, an OMC Cobra-type inboard engine and a transom assembly, and attaching the propulsion systems to marine vessels. The method and the kit use commercially available parts and minimal special hardware. The technique involves a modified transom assembly comprised of an inner transom plate, a gimbal housing, a gimbal ring equipped with machined custom-made hinge pins, two trim cylinders with corresponding trim pins, and a bell housing with specially designed bellows and adaptor nipple. The invention is also applicable to the assembling of other marine propulsion systems that are comprised of equivalent combinations of similar sterndrive units attached to other similar inboard engines by means of transom assemblies.