Abstract: A thrust compensation apparatus for high-speed rotating machinery includes an electromagnetic thrust bearing having a thrust rotor and a thrust stator, a first chamber filled with a pressurized medium on one side of the bearing, and a second chamber on the other side of the bearing. The pressure differential across the bearing augments the electromagnetic force between the rotor and stator in order to counteract the axial thrust load of the high-speed rotating machinery.

Abstract: A valve housing of the control valve has a communication passage communicating a suction port of the compressor with a crank chamber of the compressor. A main valve is provided in the valve housing for opening and closing the communication passage. A spring member resiliently biases the main valve toward its closed position. A pressure actuated unit moves the main valve toward the open position by receiving a suction pressure of the compressor. A flow adjustment valve is disposed in the valve housing for adjusting an open degree of a leak passage and receives the discharge pressure exerting a force on the flow adjustment valve toward its closed position. The flow adjustment valve increases a leak flow rate of a fluid flowing from a discharge port of the compressor to a crank chamber through a leak passage when the compressor provides a lower discharge pressure. A correction spring is disposed between the main valve and the flow adjustment valve.

Abstract: A fuel supplying apparatus for a vehicle for supplying fuel including an in-tank type fuel pump 7 provided in a sub-tank 5 inside a main tank 1 and a tubular fuel holding case 21 surrounding a suction filter portion 20 of this fuel pump 7 and having an opening portion 21B which is open in an opposite direction to a forwardly moving direction of the vehicle, so as to supply fuel 2 to outside the main tank 1 through a delivery pipe 16 by means of the fuel pump 7. The fuel 2 can be supplied to an engine even during the quick braking of the vehicle when the amount of fuel 2 is small without increasing the number of component parts of the apparatus.

Abstract: Cooling structure of gas turbine combustor in which cooling medium flows through grooves in wall is improved so that adjustment of flow velocity, pressure loss and heat transfer rate of cooling medium flow in the wall becomes possible and cooling effect thereof is enhanced. Wall of combustor tail tube is made in double structure in which outer plate (1) and inner plate (4) are jointed together being lapped one on another. The outer plate (1) has air inlet hole (3) and groove (2) formed therein. The groove (2) is closed by jointing of the inner plate (4) to the outer plate (1). The inner plate (4) has air outlet hole (5) formed therein. The groove (2) communicates with the air inlet hole (3) and the air outlet hole (5). Cross sectional shape of the groove (2) is changed two-dimensionally or three-dimensionally such that width enlarges toward the hole (5) from the hole (3) or depth is constant or changed in tapered form.

Abstract: A double wall bearing cone closes an opening between a bearing housing and an exhaust frame in a gas turbine. The bearing cone includes a conical forward plate having an inner diameter and an outer diameter and a conical aft plate nested with and spaced from the conical forward plate. A hub connects the inner diameters of the forward plate and the aft plate. The hub preferably includes holes therein that serve to meter air flow between the forward plate and the aft plate. The double wall bearing cone defines a cooling circuit that reduces wear between a third stage turbine wheel in a gas turbine and the rotor aft shaft.

Abstract: The invention relates to a simple low cost fuel nozzle support stem that can be manufactured to meet extremely close tolerances with enhanced structural rigidity through use of a cylindrical stem body machined from solid bar stock. Superior thermal control to regulate thermal displacement of the stem body and to prevent fuel coking is provided by a concentric secondary fuel bore and a primary fuel tube disposed within the bore. The low pressure secondary fuel flow encircles the high pressure primary flow tube and serves to cool the fuel tube and cylindrical stem body in a uniform symmetric manner. An outer cylindrical insulating sleeve mounted on shoulders extending from the cylindrical body of the stem defines an elongate annular insulating air gap between the sleeve and cylindrical stem body. The support stem includes a dual fuel spray nozzle and a fuel adapter/mounting flange that are mounted to the stem body with simple cylindrical sockets.

Abstract: The invention concerns a backblast gas structure for jet engine comprising a thrust reversal system with two downstream doors. The invention is characterized in that the two tilt-up doors articulated about axes (6, 7) are mounted on two side beams (2, 3) with free downstream edges (16, 17) comprising protuberances (18, 19). The door downstream edges (13, 14) having median zones (13b, 14b) forming an angle (A) with the lateral parts (13a, 14a), such that when the doors are in retracted position in direct jet, the beam (13b, 14b) edges (16, 17) of the doors are found in the same plane (P2), thereby constituting a gas exhaust outlet which is planar and substantially circular. The invention aims at improving the power package performance in direct jet.

Abstract: A control and method is provided that continuously adjusts fuel sensitive schedules in the ECU for changes in the heating value of the fuel being combusted by the engine. The control and method includes calculating, as the engine is running, an expected fuel flow for a baseline fuel type and an actual fuel flow. A ratio of these two fuel flows is determined and applied to the heating value of a baseline fuel type that is preprogrammed into the ECU. This results in a scale factor that is then applied to fuel sensitive schedules in the ECU.

Abstract: A distributor for supplying burners of a gas turbine with fuel, air and coolant. Prior art distributors contain a combination of ring lines and tie lines, over which the fuel is distributed to individual burners. It is very complicated and expensive to replace defective components, and in some cases the entire apparatus has to be dismantled to do so. The distributor of the invention has two or more modules, depending on the number of burners, which are assembled from distributor units and regulating units in such a way that they can be taken apart again. For each burner, at least one regulating unit is provided, from which at least one supply line for the fuel, air and coolant extends to the burner.

Abstract: A casing construction is provided on a gas turbine having a fan downstream of which a precompressor is situated, the precompressor casing being detachably connected with the casing of the compressor which follows the precompressor—viewed in the flow direction. An upstream end section of the precompressor casing is additionally linked to the compressor casing by at least two tension-rod-type tension devices which are situated essentially diametrically opposite one another with respect to the longitudinal axis of the gas turbine. Steel cables are preferably used as the tension devices and are fastened at least on one of the two casings by means of a tension-nut-type end piece. As a result, the precompressor casing can be constructed of a non-high-strength material and, in addition, can be linked by means of several pairs of tension-rod type tension devices to the casing of the compressor.