Abstract: A stirrup mounting device includes a stirrup attachment bar adapted for attachment to a stirrup strap loop extending from a saddle and a stirrup mounting bracket attached to a stirrup. The stirrup mounting bracket may be pivotally attached to the stirrup attachment bar so that the stirrup can rotate with respect to the stirrup strap loop about a vertical pivot axis. The vertical pivot axis is offset with respect to at least one of a vertical axis extending centrally through the stirrup strap loop and a vertical axis extending centrally through the stirrup so that the stirrup is offset toward the rear end of the stirrup attachment bar when the stirrup is rotated to a riding position. The stirrup mounting device can be used alone, or can be combined as part of a stirrup extender device where both the stirrup extender and the stirrup mounting device share a common stirrup attachment arm.

Abstract: The present invention relates to an air cleaner element holding structure for an air cleaner device for use in filtering intake air for an engine. The air cleaner device includes an air cleaner element and an element holder, provided in an air cleaner case. The air cleaner element includes at least a pair of element support plates and the element holder includes at least a pair of circular plates. The air cleaner case includes an intake duct facing an inner circumferential side of the air cleaner element for conducting air thereto. Each of the support plates has an outer diameter that is larger than that of the air cleaner element. The element support plates support the air cleaner element in such a manner that both ends, in the axial direction, of the element holder contact an inside surface, in the axial direction, of the element support plates.

Abstract: A retrofit installation kit for use with such as an exteriorly located air conditioner condensing unit. The kit includes a flexible filtration screen and a set of customized fasteners which substitute for existing fasteners used to hold together the outer sheathing of the unit frame. The substitution of fasteners for the typical mounting screws utilized in the original unit construction precludes the possibility of such as damaging the unit due to drilling new fastener holes, this running the risk of rupturing fluid coils within the unit, or damaging other sensitive electrical or mechanical components.

Abstract: A hybrid electric lawnmower is described which includes a first and a second electric motor operating blades and the ability to drive the motors from either 120 VAC line voltage or from a battery pack. There is a user selectable power selection switch for switching between DC or AC power and also a boost and conserve feature which allows for increased speed of the blade as necessary. Running the mower at the conserve setting prolongs battery pack duration per charge. Power supply and control systems allow the user to select operation of the motors in either series or parallel configuration depending on the power source.

Abstract: A plant clearing-grinding device has a front deflector inclined upward and bending plants during movements of the device, the front edge of deflector having two separate curved parts with radii centered respectively on two vertical axes of rotation of two rotors with blades so that the plants contacting each curved part penetrate into a zone of action of the blades.

Abstract: A header has a feed drum with a tapered ends that extends forward of the back sheets of the header to engage cut crop material.

Abstract: A mower blade assembly (10) is disclosed which includes an elongated blade bar (11) having two oppositely disposed cutting ends (13). A pair of removable bottom blades (22) and a pair of removable top blades (23) are removably mounted to the blade bar. The bottom blade has two oppositely disposed serrated cutting edges (27) so that either of the two cutting edges may be utilized for cutting purposes. Each top blade has a forward portion (31) which includes a series of blade segments (32) with serrated cutting edges (33) and a series of mulching blades (34) with serrated cutting edges (35). The top blade also has an elongated rear portion (37) that is oriented at an angle with respect to the cutting blades and blade bar. The angle of the rear portion creates or defines an airfoil deflector which increases the vacuum effect of the rotating blades.

Abstract: A method and apparatus for production of a yarn, by plying, twisting or covering several staple yarns, subjected to a prior transformation, is provided. At least one of the staple yarns is different from the others and/or is subjected to a different prior transformation. The prior transformation may be carried out in parallel in the same machine, by independent transformation members able to be independently controlled. A slackening of yarn tension resulting from the prior transformation to give the desired tension at an assembly point is carried out on yarn feeding devices. Routing of the yarns is achieved by guide members towards the point of assembly, where the staple yarns are combined and arranged in parallel. A bobbin receives the assembled yarns in a device, constituting or associated with a positive feed device operating without slippage with relation to the yarn.

Abstract: A device for securing a dispensing nozzle to a fill tank includes a securing mechanism and a means for connecting the securing mechanism to fill tank's cap chain. After connected to a fuel tank cap chain and upon subsequent attachment to a dispensing nozzle, the device prevents the nozzle from dislodging from the fuel tank.

Abstract: A novel jewelry chain holder is described which is adapted to receive and hold a plurality of jewelry chains of varying lengths such that the chains will not be entangled or twisted in the storage container.

Abstract: A pulse detonation engine contains a mechanically driven timing device coupled with a stator device, where the timing device has both an opening portion and a blocking portion. The opening and blocking portions open and close air flow access to a detonation chamber of the pulse detonation engine at appropriate times during the pulse detonation cycle.

Abstract: The present invention is a constant volume rocket motor that uses a non-detonating constant-volume, bipropellant combustion process in pulse-mode operation. Opening and closing of the combustion chamber exhaust outlet is controlled by an actuated reciprocating thrust valve (RTV). Fuel enters the combustion chamber at low pressure with the RTV closed. The valve opens after or during combustion when combustion chamber pressure is at or near maximum. The motor has applications in reaction control systems and attitude control systems in spacecraft.

Abstract: A journal bearing provides lubrication to planetary gears during windmilling operation of a fan section. A primary oil pump provides oil from an oil supply during driven operation of the fan and a secondary oil pump driven by a generator provides oil during windmilling operation of the fan. The generator acts as a dynamic brake when the aircraft is grounded to prevent windmilling. A switch selects between the primary and secondary oil pump and controls the brake application.

Abstract: A method of assembling a gas turbine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a low-pressure turbine to the core gas turbine engine, coupling a booster compressor to a gearbox, and coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine.

Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a first fan assembly coupled to a low-pressure turbine, a second fan assembly disposed downstream from the first fan assembly, and a gearbox coupled between the second fan assembly and the low-pressure turbine. A method of assembling the above turbofan engine assembly is also described herein.

Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a counter-rotating fan assembly disposed upstream from the booster compressor, the counter-rotating fan assembly comprising a first fan configured to rotate in a first direction and a second fan configured to rotate in an opposite second direction, and an intermediate-pressure turbine disposed downstream from the core gas turbine engine, wherein the intermediate-pressure turbine drives the booster compressor and the second fan assembly. A method of assembling the above turbofan engine assembly is also described herein.

Abstract: A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor directly to the low-pressure turbine such that the booster compressor rotates in the first direction.

Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a counter-rotating fan assembly disposed upstream from the booster compressor, the counter-rotating fan assembly comprising a first fan configured to rotate in a first direction and a second fan configured to rotate in an opposite second direction, and a low-pressure turbine disposed downstream from the intermediate-pressure turbine, the low-pressure turbine configured to drive the counter-rotating fan assembly. A method of assembling the above turbofan engine assembly is also described herein.

Abstract: A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a low-pressure turbine coupled to said core gas turbine engine, a counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction, and a gearbox comprising an input and an output, said gearbox output coupled to at least one of said first and second rotor sections, said gearbox input coupled to said low-pressure turbine. A method of assembling the turbofan engine assembly described herein is also provided.

Abstract: Disclosed are propulsion systems 30 providing reduced fuel burn, weight and cost. A single gas generator core 38 drives multiple bladed propulsion elements 36 with a power train 48. The core 38 has a forward compressor 56 and a rearward turbine 40 and rotates about a longitudinal core axis 62. The bladed propulsion elements 36 rotate about bladed propulsion element axes 78 that are not coaxial with the core axis 62. The bladed propulsion elements 36 discharge an ambient air stream 50 rearward as a bypass stream 52 portion and a core stream 54 portion. The core stream 54 portion is directed to the compressor 56. The propulsion systems 30 mount inside a fuselage 22 of an airframe 20 or they are suspended beneath a wing 24 via pylons 32.

Abstract: A thrust reverser structure for a gas turbine engine, the structure comprising an outer structure and an inner structure, the structure is capable of being secured in a closed position via outer fastening members on the outer structure, characterised in that the structure is capable of being further secured on the inner structure via a securing device having a securing position and first and second release arrangements, each release arrangement being operable to release the securing device to a non-securing position.

Abstract: A shield device for an exhaust pipe includes a socket, a shield board and a fastening device. The socket defines a connecting portion extending crookedly downwards from two ends thereof The socket is attached onto the exhaust pipe by the connecting portion. A shield board defines a shield piece and a plug. A fastening portion extends backwards from the shield piece. The plug is set on the inside wall of the shield piece, and the fastening device is set on the fastening portion of the shield piece. The shield board is attached onto the exhaust pipe by inserting the plug into the socket and fixing the fastening device onto the exhaust pipe. The shield device is easily assembled, its appearance is attractive, and the shield device and the exhaust pipe are integrated together stably. The shield device isn't prone to shaking, noise is reduced, and its life-span is protracted.

Abstract: An internal combustion engine of a vehicle is provided with an exhaust cleaning apparatus and control method. In the exhaust cleaning apparatus and method, exhaust from a combustion chamber is conducted to a main catalytic converter disposed in a main exhaust channel. A fuel cutting operation is performed upon determining a deceleration state in the vehicle and establishment of a condition for stopping fuel supply to the engine. Then, a main-channel blocking device closes the main exhaust channel so that the exhaust flows through a bypass catalytic converter disposed in a bypass exhaust channel upstream from the main catalytic converter and then merges again with the main exhaust channel upstream from the main catalytic converter after the fuel cutting operation and upon determining one of either an elapsed of a prescribed period of time, or an air-fuel ratio of the exhaust reaching a stable state.

Abstract: An exhaust-treatment system is provided having an oxidation catalyst configured to heat exhaust gas flowing through the oxidation catalyst. The system also has a particulate filter configured to receive the heated exhaust gas, and a recirculation loop configured to receive a portion of heated exhaust gas downstream of the oxidation catalyst and deliver the portion of exhaust gas upstream of the oxidation catalyst.

Abstract: An exhaust gas purifying apparatus includes a primary diesel particulate filter provided in an exhaust line of a diesel engine, a secondary exhaust line branched from the exhaust line at an upstream side of the primary diesel particulate filter, a secondary diesel particulate filter provided in the secondary exhaust line, and a low pressure part provided in the secondary exhaust line at a downstream side of said secondary diesel particulate filter. The secondary diesel particulate filter has a soot load capacity smaller than the soot load capacity of the primary diesel particulate filter. The low pressure part provides a pressure lower than a pressure of the branching point. The apparatus further includes a differential pressure measuring part for measuring a differential pressure between an inlet and an outlet of the secondary diesel particulate filter.

Abstract: An exhaust system for a combustion engine is disclosed. The exhaust system may have a housing connected to receive a flow of exhaust. The exhaust system may also have a first catalyst disposed within the housing to reduce the concentration of an exhaust constituent, and a second catalyst disposed within the housing downstream of the first catalyst to further reduce the concentration of the exhaust constituent. The exhaust system may further have a sensor disposed between the first and second catalysts to generate a signal indicative of the concentration of the exhaust constituent at the location between the first and second catalysts. The exhaust system may additionally have a controller in communication with the sensor to receive the signal. The controller may determine, based on the received signal, the concentration of the exhaust constituent at a location downstream of the second catalyst.

Abstract: A control system for a power unit having a supply of fuel and a supply of reductant is disclosed. The control system may have a first sensor associated with the supply of fuel to generate a signal indicative of a quantity of fuel remaining. The control system may also have a second sensor associated with the supply of reductant to generate a signal indicative of a quantity of the reductant remaining. The control system may further have a controller in communication with the first and second sensors. The controller may be configured to affect operation of the power unit such that the remaining fuel is consumed before consumption of the remaining reductant.

Abstract: An exhaust treatment system for a combustion source is disclosed. The exhaust treatment system may have a supply of catalyst configured to lower the combustion threshold value of an exhaust constituent, and an injector operable to selectively pass catalyst to the exhaust constituent. The exhaust treatment system may further have a controller in communication with the injector. The controller may be configured to determine a temperature of an exhaust flow, and operate the injector to pass catalyst in response to the combustion threshold value being greater than the determined temperature.

Abstract: A system is provided for supplying reductants to an emission treatment unit. The system comprises a fuel tank adapted to directly or indirectly supply a first premixed fuel stream and a second premixed fuel stream, wherein each fuel stream comprises a primary fuel component and an oxygenate reductant component. An engine is in fluid communication with the fuel tank, wherein the engine is configured to receive the first premixed fuel stream and create an exhaust stream. The system further includes an emission treatment unit to treat the exhaust stream. A separation unit is configured to receive the second premixed fuel stream, separate the second premixed fuel stream into a first fraction stream and a second fraction stream, and supply the first fraction stream to the emission treatment unit, wherein the first fraction stream comprises a higher concentration of the oxygenate reductant component than the second fraction stream.

Abstract: A device for purifying exhaust gas of an internal combustion engine is provided, equipped with an HC catalyst having the ability to oxidize HC, as well as adsorb HC, and release HC which it has adsorbed, and there exists a specific condition where the amount to release HC becomes greater than the amount to oxidize HC, wherein the device for purifying exhaust gas of an internal combustion engine executes an HC feed control for feeding HC to the HC catalyst. The amount of HC fed to the HC catalyst is decreased by the HC feed control or the HC feed control is discontinued when the specific condition is established during execution of the HC feed control.

Abstract: The present invention generally relates to engines, and, more particularly, to an exhaust system for reducing buildup in an exhaust gas recirculation system when mixing hydrocarbons with exhaust.

Abstract: It is an object of the present invention to provide a load control system capable of controlling pressure generated by a pneumatic device with a high degree of accuracy and further capable of reacting to variations of the pressure without delay.

Abstract: A hydraulic differential with a variable displacement hydraulic unit of the axial piston type, a fixed displacement hydraulic unit of the axial piston type, a stationary housing for mounting the hydraulic units, an input shaft for coupling to a variable speed power source and an output shaft for coupling to a constant speed load, comprises: a wobbler and a port plate for the variable displacement hydraulic unit coupled to the stationary housing; an axial block and piston set for the variable displacement hydraulic unit, a port plate for the fixed displacement hydraulic unit and a wobbler for the fixed displacement hydraulic unit coupled to the input shaft; and an axial block and piston set for the fixed displacement hydraulic unit coupled to the output shaft; wherein the variable displacement hydraulic unit port plate and the fixed displacement hydraulic unit port plate couple together through a circumferential interface to minimise hydraulic thrust forces developed by the hydraulic unit.

Abstract: A turbocharger (107) for an internal combustion engine (100) includes a turbine having a divided turbine housing (109). A first inlet port (113) may be connected to a first volute that is formed in the turbine housing (109), and a second inlet port (114) connected to a second volute that is formed in the turbine housing (109). A center housing may be connected to the turbine housing (109), and a compressor (111) may be connected to the center housing. An exhaust gas valve (137) is in fluid communication with the first inlet port (113) and arranged to at least partially constrict a flow of exhaust gas from entering the first inlet port (113) of the turbine (109), but not constrict the flow of exhaust gas from entering the second inlet port (114).

Abstract: A method and apparatus is shown for operating an internal combustion engine having a turbocharger, comprising comparing estimated air flow to a mass air flow sensor signal to create a flow deviation signal, using the flow deviation signal and a modeled volumetric efficiency to calculate a required intake pressure, and using the required intake pressure as a set point for boost pressure control.

Abstract: An exemplary center housing rotating assembly includes a turbine wheel, a compressor wheel, a center housing with a through bore extending from a compressor end to a turbine end, a lubricant inlet and a lubricant outlet, a pair of bearings disposed at least partially in the through bore of the center housing, a bearing spacer and a shaft rotatably supported by the bearings and having a rotational axis coincident with a rotational axis of the turbine wheel and a rotational axis of the compressor wheel where the center housing includes bearing lubricant paths to direct lubricant from the lubricant inlet to the pair of bearings and a shaft lubricant path to direct lubricant from the lubricant inlet to the shaft in a manner dependent on rotational position of the bearing spacer in the through bore of the center housing. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A dual fuel nozzle of a gas turbine combustor with a variable jetting hole diameter is disclosed. The combustor includes a plurality of swirling wings disposed along an outer peripheral surface of a central shaft to have at least one main fuel jetting hole, an air duct positioned at the lower side of the swirling wings to supply air to the swirling wings, a pilot fuel injection hole and jetting hole formed to pass through a central portion of the central shaft to supply a pilot fuel, a switching plate disposed inside the swirling wings to vary the size of the main fuel jetting hole, a driving unit disposed to be connected to the switching plate to move a position of the switching plate, and a casing containing the swirling wings, the air duct, the switching plate and the driving unit. It is possible to enhance fuel flexibility in a multiple fuel system for applying two or more fuels to a gas turbine at the same time.

Abstract: A fuel injector for a gas turbine engine is disclosed which includes an inlet fitting for receiving fuel, a nozzle for issuing fuel into the gas turbine engine, an injector body extending between the inlet fitting and the nozzle and having and interior bore extending therethrough, and an elongated fuel tube disposed within the interior bore of the injector body for delivering fuel from the inlet fitting to the nozzle. The fuel tube has an inlet end portion dynamically associated with the inlet fitting and an outlet end portion rigidly connected to the nozzle. An adapter is operatively associated with either the inlet end section of the fuel tube or a reception bore formed with the inlet fitting of the injector for accommodating a seal member in a manner that permits thermal growth of the injector body relative to the fuel tube.

Abstract: A method for operating a gas turbine is provided wherein a supply of fuel is passed to a gas turbine combustor, and a supply of nitrogen and sufficient air to provide at least sufficient compressed air to the gas turbine for fuel combustion is passed to a compressor. A sufficient portion of the compressor discharge flow is passed to a combustor for fuel rich combustion of the fuel flow to the combustor and the fuel is combusted to produce hot combustion gases that are, in turn, passed to a turbine.

Abstract: A method for assembling a combustor for use in a turbine engine is provided. The method includes providing at least one support leg, forming at least one opening in the support leg, wherein the at least one opening has a perimeter defined only by a plurality of non-linear segments, and coupling the support leg to the combustor.

Abstract: A method facilitates assembling a gas turbine engine with a flameholder. The method comprises coupling at least one turning vane between a radially outer casing and a radially inner casing to form a flameholder, forming at least two slots that extend substantially radially through the outer and inner casings, coupling at least one fuel injector to the flameholder, and coupling the flameholder within the augmenter.

Abstract: A dual mode scramjet engine has an isolator that serves to minimize combustor influence on inlet operation, a combustor for operation in both ramjet and scramjet mode, and a centerbody positioned within the isolator. The centerbody has an end at an entrance to the combustor.

Abstract: A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.

Abstract: An exhaust eductor system includes a primary exhaust nozzle configured to transport an active flow stream; and a mixing duct at least partially surrounding the primary exhaust nozzle and configured to transport a passive flow stream that is entrained by mixing with the active flow stream from the primary exhaust nozzle. The mixing duct has an interior, and a baffle on the interior of the mixing duct is configured to prevent the mixed flow streams from exiting the mixing duct.

Abstract: A modular turbine generator includes both a turbo generator, and electrical power conditioning and control circuitry. During conditions of high ambient temperature the turbo generator may lose both power output and efficiency, while the electrical circuitry suffers from shortened service life or failure because of the high temperatures experienced. In order to preserve power output and efficiency for the turbo generator, as well as extending the service life span for the electrical power conditioning and control circuitry, a dual function evaporative cooler is provided. This cooler provides evaporatively cooled air both to the turbine engine and to the electrical circuitry by utilizing a single evaporative pad, along with a single water source and recirculation pump, all received in a compact cabinet.

Abstract: A method of lowered NOx combustion is taught wherein the kinetic rate of NOx formation is reduced for a given combustion temperature in a gas turbine combustor. A supply of fuel is provided along with a supply of ambient air in sufficient quantity to form a fuel/air mixture having an equivalence ratio greater than about 0.55 when mixed with the fuel. The fuel/air mixture is mixed with a supply of cooled combustion gases in sufficient quantity such that the oxygen content of the resulting air mixture is less than about 18 percent. The resulting air mixture is then passed into the combustor.

Abstract: A method is provided for performing a transfer from gas fuel operation to liquid fuel operation in a gas turbine with a dual fuel system. The method includes initiating a predetermined uncontrolled liquid fuel prefill flow rate through the liquid fuel system, sensing an onset of the uncontrolled liquid fuel flow to the combustor nozzles, and initiating transfer from gas fuel operation to liquid fuel operation when the flow of uncontrolled liquid fuel at the combustor nozzles is sensed. The onset of uncontrolled liquid fuel flow to the combustor nozzles is determined by monitoring changes of Fuel Normalized Power (FNP), a parameter sensitive to uncontrolled liquid fuel flow, and determining when FNP exceeds a threshold algorithm value.

Abstract: An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and an airflow management feature in the duct.

Abstract: A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor device operates in a steady, constant pressure deflagration mode, receiving its fuel from the fuel injector. In a second mode of operation the dual mode combustor device operates in a pulse detonation mode, receiving its fuel from the high frequency solenoid valve.

Abstract: A cooling fluid reuse system for a turbine engine for capturing spent cooling fluids from row one turbine vanes and directing those fluids into a mixing chamber to be mixed with liner cooling fluids and used in a combustor. The cooling fluid reuse system may be formed from a fluid channel extending from the a cooling fluid collection channel in the first row of turbine vanes, through a rotor cooling fluid collection chamber in the rotor assembly, through a cooling fluid manifold, and into the at least one mixing chamber.