Abstract: A counter rotating propeller system comprises a structure configured to control the front propeller outer slipstream and prop wash. Specifically disclosed is a structure configured to vary the effective hub-tip radius ratio of the rear propeller.

Abstract: Both a method and apparatus for producing liquified natural gas (LNG) at a well head or other source where cool high pressure natural gas is provided. The natural gas flow from the source is cleaned, if required, and is split into two portions. The first flow portion goes to a primary heat exchanger, then to a second heat exchanger or super cooler, and is thereafter throttled into a LNG tank wherein a part thereof flashes to liquid natural gas and a part thereof becomes a very cold saturated vapor to be vented from the LNG tank. This vent remainder of the first flow portion enters the super cooler as a coolant therefor. The second flow portion enters an expander where work is extracted and the temperature and pressure of the second flow portion are lowered. The cold lower pressure second portion combines with the partially warmed vent remainder of the first portion from the super cooler and passes into the primary heat exchanger as the initial coolant for the first portion.

Abstract: A method and apparatus for the partial conversion of natural gas to liquid natural gas. Natural gas, at a high pressure and free of impurities which would hinder the formation of liquid natural gas, is split into first and second flow portions. The first flow portion is conducted through a first heat exchanger and thereafter through a second heat exchanger. From the second heat exchanger, the first flow portion is throttled into a collector, wherein part thereof flashes to liquid natural gas and a part thereof constitutes a cold saturated vapor to be vented from the collector. The vent remainder serves as a coolant for the second heat exchanger. The second flow portion passes through a restrictor and is thereby cooled. The vent remainder from the second heat exchanger is joined with the cooled second flow portion and this combination serves as a coolant for the first heat exchanger before it is conducted to a receiver.

Abstract: A method and apparatus for an engine driven system having the capability of liquefying 100% of the natural gas entering the system. The apparatus is connected to a source of clean natural gas, and comprises an engine or prime mover, a compressor and an expander, all drivingly connected, at least one cooler, at least one heat exchanger, a restrictor, a liquid natural gas collector and connecting conduits. The clean natural gas is provided to the inlet of the compressor and is compressed. The compressed natural gas is passed through the at least one cooler to remove heat of compression. The natural gas is split into two flow portions. The first flow portion is cooled in the at least one heat exchanger and is passed through the restrictor into the collector. The temperature and pressure of the first flow portion are such that a substantial portion flashes to liquid natural gas.

Abstract: A method and an apparatus for producing liquid natural gas (LNG) from a well head or other source of cool, high pressure natural gas. The natural gas from the source is purified and split into first and second flow portions. The first flow portion is split into two parts passing through first and second heat exchangers. The two parts are thereafter recombined and throttled into a LNG tank wherein part thereof flashes to liquid natural gas and a part thereof constitutes a very cold saturated vapor to be vented from the LNG tank. The vent remainder of the first flow portion is used as a coolant for the second heat exchanger and is then conveyed to a low pressure receiver such as a collection pipeline, the vent remainder having a pressure equal to or greater than the receiver. The second flow portion enters an expander wherein its pressure is lowered below that of the receiver and its temperature is lowered accordingly.

Abstract: A system for controlling thrust forces on a thrust bearing in a rotating structure of a gas turbine engine at designated operating points including a device for providing thrust load compensation to the thrust bearing, a control for operating the thrust load compensation device, and a sensor for detecting rotational cage speed of the thrust bearing. The sensor provides a signal to the control when the rotational cage speed of the thrust bearing drops below a specified ratio of the rotational speed for the rotating structure, the signal being indicative of an incipient skid condition for the thrust bearing. The control then causes the thrust load compensation device to provide an additional predetermined load on the thrust bearing when it receives the signal from the sensor so that a resultant load thereon is within a specified load range which extends the life of the thrust bearing.

Abstract: An internal combustion engine having a pair of opposed pistons in a block has a piston connected to a respective crankshaft. A gear train synchronizes the speed and relative angular relationship between the crankshafts. A timing actuator, connected to and engaged with either of the crankshafts, permits continuous selective adjustment of the headspace between the pistons by varying parameters such as intake and exhaust port timing and air flow through the cylinder.

Abstract: An apparatus for supplying compressed air to the auxiliary system of a vehicle such as an aircraft, or other device powered by a gas turbine engine, comprises an auxiliary compressor which is connected by a differential to the main drive shaft of the compressor of the gas turbine engine. A controller receives a signal from a pressure sensor at the output of the auxiliary compressor representing the pressure and/or flow rate of the compressed air discharged from the auxiliary compressor and compares that signal with a signal from the auxiliary system representing its requirements for compressed air which can be set at predetermined levels or dynamically determined during operation of the vehicle. The controller is effective to control a variable speed motor connected to the differential which speeds up or slows down the auxiliary compressor and thus varies the compressed air output from the auxiliary compressor to the auxiliary system of the vehicle.

Abstract: An internal combustion engine having a pair of opposed pistons in a block has a piston connected to a respective crankshaft. A gear train synchronizes the speed and relative angular relationship between the crankshafts. A timing actuator, connected to and engaged with either of the crankshafts, permits continuous selective adjustment of the headspace between the pistons by varying parameters such as intake and exhaust port timing and air flow through the cylinder.

Abstract: A turbine arrangement for a gas turbine engine having a sloped gas flowpath through the turbine. The radial axes of the rotor blades and stator vanes in the sloped flowpath are tilted such that the axes are substantially normal to the mean flow streamline of the gases. This arrangement reduces tip losses and thereby increases engine efficiency.

Abstract: An axial compressor is provided with a cooling air manifold surrounding a portion of the shroud, and means for bleeding air from the compressor to the manifold for selectively flowing it in a modulating manner axially along the outer side of the stator/shroud to cool and shrink it during steady-state operating conditions so as to obtain minimum shroud/rotor clearance conditions. Provision is also made to selectively divert the flow of cooling air from the manifold during transient periods of operation so as to alter the thermal growth or shrink rate of the stator/shroud and result in adequate clearance with the compressor rotor.

Abstract: A turbine arrangement for a gas turbine engine having a sloped gas flowpath through the turbine. The radial axes of the rotor blades and stator vanes in the sloped flowpath are tilted such that the axes are substantially normal to the mean flow streamline of the gases. This arrangement reduces tip losses and thereby increases engine efficiency.