330results about "Engineering emergency devices" patented technology

A gas turbine engine includes an epicyclic gear train that drives a turbo fan. The epicyclic gear train employs a one-piece carrier in which the spaced side walls are interconnected with circumferentially spaced apart mounts to form a unitary structure. Baffles are secured to the carrier near the mounts and provide lubrication passages that spray oil onto the sun gear and/or intermediate gears arranged between the baffles. The baffles can be constructed from a different material than the carrier since the baffles are not structural components in the gear train.

A cable safety barrier has means for disengagement of the cable from an anchor portion of the cable safety barrier when certain vehicle impact conditions are met. Disengaging of the cable may involve allowing a cable end fitting to escape from an open ended slot, when the cable is deflected upwards, or causing the cable fitting to fail.

A method of controlling variable extraction flow in a combustion turbine engine, wherein extraction flow comprises a supply of compressed air extracted from the compressor and supplied to the turbine through extraction conduits, and wherein the extraction conduits includes a variable extraction orifice, the method comprising the steps of: measuring a plurality of turbine engine operating parameters; monitoring, by a control unit, the measured operating parameters of the combustion turbine engine; setting the variable extraction orifices to a setting that allows an approximate maximum level of extraction flow; calculating, by the control unit, at least one calculated operating parameter based upon model-based control and the measured operating parameters, including at least a current turbine inlet temperature and a maximum turbine inlet temperature; and manipulating the setting for the supply of fuel to the combustor such that an increased and/or maximum level of engine output is determined by comparing the values for the current turbine inlet temperature and the maximum turbine inlet temperature.

An apparatus for use in a wellbore, the apparatus comprises a top body, a bottom body, and a sleeve mechanically connected to the top and bottom bodies. The sleeve movable between a first position to a second position, whereby in the first position, the top and bottom bodies rotate as one unit and in the second position, the top body rotates independent of the bottom body in a first direction and with the bottom body in a second direction. A method for completing a wellbore, wherein the method comprises running an assembly and a liner disposed on a drill string into the wellbore. The assembly includes an expander tool, a hydraulically actuated swivel, and a running tool mechanically connected to the liner. The method includes rotating the assembly and the liner as one rotationally locked unit. The method further includes activating the expander tool, expanding the liner into the existing casing, deactivating the expander, and then removing the drill string and running assembly from the wellbore.

An exhaust gas treatment apparatus (20) for reducing the concentration of NO_x, HC and CO in an exhaust gas stream (18) such as produced by a gas turbine engine (12) of a power generating station (10). The treatment apparatus includes a multifunction catalytic element (26) having an upstream reducing-only portion (28) and a downstream reducing-plus-oxidizing portion (30) that is located downstream of an ammonia injection apparatus (24). The selective catalytic reduction (SCR) of NO_x is promoted in the upstream portion of the catalytic element by the injection of ammonia in excess of the stoichiometric concentration, with the resulting ammonia slip being oxidized in the downstream portion of the catalytic element. Any additional NO_x generated by the oxidation of the ammonia is further reduced in the downstream portion before being passed to the atmosphere (22).

A turbomachine combustion chamber has primary and dilution air inlet orifices formed by die stamping to have edges that project into the inside of the combustion chamber, and stress relaxation and/or reduction means in the edges or in the vicinity of the edges of said orifices, said means comprising, for each orifice, one, two, or three slots formed in the edge or around a fraction of the edge of said orifice.

A method of forming an internal combustion engine component having a multi-panel outer wall. The multi-panel outer wall has an inner panel (16) with an inner surface (18) and an outer surface (37). The inner panel outer surface (37) has discrete pockets (23) formed by integral structural ribs (38). Each pocket (23) has a film cooling hole (31) between the pocket (23) and the plenum (20). The method includes: forming dimples (40) in the intermediate panel (22), at least one dimple (40) having a nozzle (29); securing the intermediate panel (22) to the inner panel outer surface (37), thereby enclosing at least one pocket (23); and ensuring a respective dimple (40) having a nozzle (29) protrudes into a respective enclosed pocket (24) and a respective nozzle (29) is configured to direct a respective jet (35) of cooling fluid onto the inner panel outer surface within the respective enclosed pocket (23).

In the partial-regeneration cycle gas turbine system wherein part of the air compressed by a compressor 2 is extracted before a combustor 3, mixed with steam, and after the mixed gas is superheated by exhaust heat of a turbine, and the mixed gas is injected into the combustor, high-pressure steam is used as a fluid for driving a first mixer 22 that compresses extracted air, to increase the ratio of extracted air to steam, and then this mixed gas of extracted air and steam is further mixed with low-pressure steam from a low-pressure exhaust heat boiler, in a second mixer, and the mixture of gas is superheated in a superheater 6 by exhaust heat of the turbine, and injected into the combustor. Thus, the pressure of the driving steam can be raised, an exergy loss in an exhaust heat recovery portion can be reduced, and the efficiency of power generation can be increased without reducing the flow of generated steam.

In a process for protection of a gas turbine (1) from damage caused by pressure pulsations (P),

• • pressure pulsations (P) occurring during the operation of the gas turbine (1) are measured, from the measured pressure pulsations (P), a pulsation-time signal (PZS) is generated, the pulsation-time signal (PZS) is transformed into a pulsation-frequency signal (PFS),
  • from the pulsation-frequency signal (PFS), a pulsation level (PL) is determined for at least one specified monitoring frequency band (12), the pulsation level (PL) is monitored for the occurrence of at least one specified trigger condition, and,
  • when the at least one trigger condition occurs, a specified protective action (16) is carried out.

A joint assembly 80 is provided for limiting an extension of the joint 80 in the direction of a load path derived from an impact comprising. In its simplest form, the joint 80 comprises a first member 40 having a portion 82 and a second member 50 having a portion 84, the portions 82, 84 overlapping one another and arranged generally parallel to one another and secured together via securing means 78. The securing means 78 is disposed through corresponding holes 92, 94 defined by portions 82 and 84. At least one of the overlapping portions 82 or 84 further defines, sequentially in the direction of extension a pocket 102. The securing means 78 comprises a deformable member 152, 178 and at least one of the overlapping portions 82, 84 comprises a wedge-shaped portion 74. In the event of a worst-case impact load the securing means 78 is forced through the pocket 106 while the wedge-shaped portion 74 causes the deformable member 152 to deform and thereby increase the clamping force, in a progressive manner, to limit the extension of the joint assembly 80 and retain an integral joint assembly 80.

Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exo-skeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation over traditional gas turbine technology today. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions. With bypass fan(s), compressor stages and turbine segments controlled electrically in a shaftless turbine design, the S-MAGJET maximizes the propulsion efficiencies over a broader range of operating conditions compared to current art of turbine technology and at much higher thermodynamic and aerodynamic efficiencies.

In the aerospace field spacecraft components are held together by separation systems until a specific time when they must be separated or deployed. Customarily a threaded joining bolt engages one of the components to be joined, and a threaded nut is placed on that bolt against the other component so they can be drawn together by a releasable locking assembly. The releasable locking assembly herein includes a plunger having one end coupled to one end of a plunger bolt. The other end is flanged to abut and compress a coil spring when the plunger is advanced toward the interface plane between the two components. When the plunger is so advanced toward the interface plane, the end of the plunger bolt can be connected to the joining bolt. Thus during retraction the joining bolt is drawn to one side of the interface plane by the force of the expanding spring.

An apparatus comprises a tubular body with a channel and a number of stiffeners that allow the tubular body to absorb additional mechanical energy through axial compression. The number of stiffeners is located on a number of locations for the tubular body.

A method and system for controlling fuel flow in a fuel metering system that includes a metering valve and a proportional bypass valve that produces a differential pressure error across the metering valve includes supplying a first fraction of fuel through the metering valve. A second fraction of the fuel is directed through the proportional bypass valve. The differential pressure error produced by the bypass valve is determined, and fuel flow through the supply line is controlled by adjusting the metering valve based at least in part on the determined differential pressure error, and by adjusting the proportional bypass valve to maintain a substantially constant metering valve differential pressure across the metering valve.