Abstract: The invention relates to a method and a device for setting a timer circuit, especially in a fuse (1b), there being used a setting unit (1a) for the transfer of setting signal to the timer circuit which is housed in the fuse (1b). For the purpose of simplifying the communication between the fuse (1b) and the fuse setting unit (1a), both as regards to avoiding previous calibration of the timer reference of the system, and as regards a reduction of the electro-mechanical contact connection between the fuse (1b) and the setting unit (1a) to a minimum, it has according to the invention been suggested that there are provided setting signals such that the time to which the timer circuit is to be set, is transferred from the setting unit (1a) to the fuse (1b) by pulse width modulation of the power supply voltage. The setting signal can then be transferred via only two contacts (K1, K2) on the surface of the fuse.

Abstract: An arrangement in a remote-controllable subsea connector wherein the connector components may be locked together by the aid of a ring of collet fingers (5) cooperating with an actuator ring (17) controllable in the axial direction of said connector. In order to provide secure and efficient locking of said connector without the necessity of exerting very high pressures, and in order to permit compensation of tolerance variations in the connector said actuator ring (17) is provided with a maneuver ring (8) and an annular shaped retaining means which may consist of a ring member, for instance of titium alloy or carbon fibres, or a series of retaining members (7) placed in an annular shape on the inside of said maneuver ring (8), in contact with said fingers (5) in said collet finger ring. Said retaining members (7) cooperate with said maneuver ring (8) via conical surfaces (19, 13).

Abstract: A gas generator having a double entry low pressure centrifugal compressor, a single entry high pressure centrifugal compressor and a radial inflow turbine positioned coaxially and coupled for interdependent rotation by a single shaft assembly for the double entry compressor mounted to the generator frame using a plurality of rigid hollow cross-over ducts which also carry diffused compressed air to the high pressure compressor, where the single shaft assembly uses two shaft portions connected by an expansible coupling having a helical spline torque transmitting device to allow the double entry compressor rotor to "follow" compressor housing axial position changer and to maintain a close running clearance despite thermal expansion in the structure between the low pressure (LP) and high pressure (HP) compressor portions of the gas generator.

Abstract: A movable spike, variable entrance geometry annular pipe-type diffuser has, for prevention and suppression of flow-induced vibrations, a gear assembly for imparting rotational motion about the axis of a rod member supporting the spike in the diffuser channel, and damper guides fixed to the spike and cooperating with guide slots in the diffuser housing for opposing the rotational motion to create a biasing torque between the spike and housing to increase rigidity and damping.

Abstract: A compact, highly efficient single spool gas turbine gas generator uses a double-entry centrifugal first stage compressor, a single-entry centrifugal second stage compressor, and a radial inflow turbine to achieve an overall pressure ratio of greater than 15:1. The first stage pressure ratio is more than twice the second stage pressure ratio, and the first stage entrance Mach numbers are greater than about 1.4. The specific speed of each the compressors ranges from 0.65 to 0.85, and of the turbine from 0.50 to 0.75.

Abstract: A combustor for a gas turbine including a burner defining an axial fluid flow path between upstream and downstream ends, a burner casing coaxially surrounding the burner and defining an annular conduit for inlet gas flow from downstream to upstream ends of the burner, ports for introducing part of the inlet gas into the upstream end of the burner, a fuel nozzle introducing fuel into the upstream end of the burner, slots circumferentially disposed around the burner casing upstream of the ports and a conduit and valve arrangement for introducing external air to the annular conduit through the slots to generate an annular vortex to restrict inlet gas flow to the ports when the turbine is operating at predetermined operating conditions.

Abstract: A variable flow gas turbine engine of the type having a combustor for generating combustion gases and a turbine rotor for receiving and expanding the hot combustion gases, has an outer wall and an end wall defining a channel for directing the flow of combustion gases from the combustor to the rotor; a plurality of fixed guide vanes mounted in the channel, the space between adjacent vanes forming at least one throat; a winglet fixedly mounted in the throat for separating the gases flowing through the throat into first and second streams; and a passage through at least one of the vanes into the throat, the passage being in fluid communication with source of air under pressure for injecting high pressure into the throat for varying the flow of combustion gases through the second stream. A method for varying the effective flow area of combustion gases in a gas turbine engine is also disclosed.

Abstract: A toroidally shaped double-walled gas-cooled inlet manifold for a radial in-flow turbine has a plurality of can-type combustors mounted on one axially facing side of the torous, arrays of coolant gas inlet holes in the outer wall located midway between the individual combustors, coolant gas inlet slots distributed circumferentially along the torous on the axial face mounting the combustors, and coolant gas inlet impingement orifices proximate the annular manifold exit duct on both axial facing sides of the outer wall. Annular coolant gas exit ports are provided surrounding the circular combustion gas inlet ducts from the individual combustors to induce a blanketing flow of coolant gas over the entire inner wall.

Abstract: Aerodynamically tapered spike is positioned for controlled axial movement in the conical portion of a composite gas turbine engine diffuser controlling engine air mass flow rate by adjusting diffuser area ratio. Also, a straight pipe transition diffuser portion is positioned between the conical portion and a flat plate diffuser portion to flatten the velocity profile.

Abstract: A composite diffuser for a radial compressor has a straight pipe transition portion positioned between a conically diverging upstream portion and a downstream flat plate diffuser portion to flatten the velocity profile prior to entrance into the plate diffuser portion.

Abstract: A cup shaped disc (13) consisting of a central portion (20) having radially extending blades (18) is attached with its central portion to the protruding hub portion (12) of a radial flow turbine wheel (2) consisting of a backing plate (10) extending transversely to its rotational axis (7) and having axially protruding turbine blades (11) in addition to the protruding hub. At high rotational speeds this disc (13) will tend to straighten out, whereby the effective portion of the turbine blades will be reduced and the increase in the rotational speed restricted. This is of importance in ram air turbines for missiles.

Abstract: Gas turbine engine starting method and apparatus includes the engine turbine and rotary compressor components coupled for dependent rotation; a compressor plate diffuser with an integral, floating plate one-way valve; a housing receiving diffused compressed air for channeling to the combustor; and a source of pressurized air connected for admission to the housing during startup at a point upstream of combustor and downstream of one-way valve for initiating rotation of the turbine and coupled compressor.

Abstract: The improved dual-entry radial compressor rotor of the present invention has two sets of alternating full length and partial length blades on a symmetrical hub, with the partial length blades on one hub side terminating at the rotor high velocity exit coincident with the full length blades on the other hub side, to smooth the gas velocity profile in the tangential direction. Aerodynamically shaped sawtooth-profiled reliefs are provided in the hub radial portion between the blade tips to allow induced pressure differentials between the flow paths to smooth the axial velocity profile.

Abstract: Acoustically sized bleed passages are provided in the shroud wall of a rotary compressor to admit expansion waves to the suction-sides of successive passing blades to control the boundary layer. The expansion waves are generated by reflecting compression waves formed in the passages by the pressure sides of passing blades. The passages are oriented to receive high pressure bleed gas at maximum gas particle velocity, and the passages are configured to diffuse the gas to increase static bleed pressure.

Abstract: In a fluid flow machine comprising a compressor including a compressor diffuser and a turbine including an exhaust gas diffuser compressed air from boundary layers or vortex flows in the compressor diffuser, or leakage air from the compressor, is bled off and used as a driving medium for removing exhaust gas from boundary layers or vortex flows in the exhaust gas diffuser. Since the pressure of the exhaust gas to be removed from the exhaust gas diffuser is below the ambient pressure a suction has to be established to remove the desired gas from the boundary layers or vortex flows. This suction is established by an ejector or a pump which is driven by the energy of the compressed air bled from the compressor regions.

Abstract: Two concentric, partially overlapping annular plates mounted on a parallel support plate are provided for partly defining the gas flow path and for shielding bearings, etc. from hot combustion gases in a radial flow gas turbine. The radially outer plate is cooled by compressed air channeled past the plate surface opposite the combustion gases. The compressed air is metered to achieve a temperature distribution decreasing in the radially inward direction for providing sealing contact between the outer edge and the support plate. The radially inner plate is cooled by film cooling using the compressed air exiting the outer plate channel in the vicinity of the overlap.

Abstract: Two sets of guide vanes are positioned in the combustion air flow path in the inlet duct of a rotary compressor of a gas turbine engine for controllably varying the air mass flow rate according to turbine load conditions. The upstream set which provides a fixed, initial degree of swirl relative to compressor rotational direction and axis and the controllably moveable downstream set which provides a final degree of swirl cooperate to provide controllable swirl over the range of about 0.degree. to 32.degree. in the inlet air incident upon the turbine blades. The two guide vane sets are separated by a distance sufficient to allow turbulence induced by the first set to fully decay before the second set is encountered.

Abstract: Delicate equipment is mounted on a carrier such as a vessel or a vehicle by means of shock absorbers which are spring biased to an accurately defined position in which the equipment is rigidly fastened to the carrier. When the carrier is subjected to a shock force exceeding the biasing of the shock absorbers, the rigid connection is released and the equipment thus protected against damaging forces.Each shock absorber has a single compression spring which is compressed by an axial force on the shock absorber regardless of the direction of the force.At least three parallel, vertical shock absorbers carry the equipment. Horizontal shocks are absorbed due to the tilting movement of the equipment relative to the shock absorbers, which are thus subjected to vertical movements in opposite directions.

Abstract: The nose portion of a missile having a ram air turbine for driving an electric generator for supplying electric power to the electric circuits of the missile, especially of its fuse, is designed in a special manner in order to provide, at high missile speeds, a throttling of the air flow, whereby the speed of rotation of the turbine may be kept within reasonable limits. Thus, the air inlet is divided in a plurality of inlet ducts arranged as a wreath around the foward end of the missile. Further, the outlet openings are forwardly directed and co-operate with the shock waves from the acute forward end of the missile and from an annular edge surrounding the wreath of inlets but lying radially inside the outlet openings.

Abstract: Two sets of guide vanes are positioned in the combustion air flow path in the inlet duct of a rotary compressor of a gas turbine engine for controllably varying the air mass flow rate according to turbine load conditions. The upstream set which provides a fixed, initial degree of swirl relative to compressor rotational direction and axis and the controllably moveable downstream set which provides a final degree of swirl cooperate to provide controllable swirl over the range of about 0.degree. to 32.degree. in the inlet air incident upon the turbine blades. The two guide vane sets are separated by a distance sufficient to allow turbulence induced by the first set to fully decay before the second set is encountered.