Abstract: A method and system for supplying compressed air to a process plant using a combustor-turbine unit directly coupled to a bull gear meshing with pinions on which are mounted gas compression stages and expansion stages. Some stages compress a stream of air supplied to the combustor-turbine unit for combustion and to the process plant. Other stages expand or compress other gas streams directed to the combustor-turbine unit or to external applications. Direct energy transfers and intercooling and aftercooling after compression stages enhance the efficiency of the system.

Abstract: A reversing marine drive utilizing a gas generator prime mover provided with first and second counter-rotating power turbines. The first turbine is connectable by a differential gear set and a pinion and reduction gear assembly to the ship's shaft to drive the shaft and the screw thereon in the forward thrust direction. The second turbine is connectable by the differential gear set and the pinion and reduction gear assembly to the ship's shaft to drive it and the screw thereon in the reverse thrust direction. A brake assembly is provided in association with each of the first and second power turbines so that when one of the power turbines is driving the screw, the other power turbine is stopped. A master computer may be provided to control the reversing marine drive.

Abstract: A reduction gear for producing and feeding the rotation of a low pressure turbine driven by a combustion gas generated in a combustor to an output shaft is received in a central opening of a rotary type heat exchanger which is disposed so as to be perpendicular to a turbine shaft at a rear portion of a body housing of a gas turbine engine. As a result, not only the engine can be made small but also the output can be produced at to the opposite side of the heat exchanger. The combustor and a collector housing for collecting combustion gas are disposed on diametrical opposite sides in a transverse cross section of the body housing whereby an internal space of the body housing is effectively utilized and an axial dimension of the engine is shortened. Since the compressed air is supplied to the heat exchanger through peripheral walls of the body housing having a double construction, prevention of heat radiation from the body housing and effective utilization of an internal space of the body housing are realized.

Abstract: An improved rolling element bearing assembly is provided which is particularly applicable for use in gas turbine engine gearboxes. The rolling element bearing includes an inner ring mounted to a rotatable shaft and an outer ring mounted to a stationary structure. The inner and outer rings define a raceway for a plurality of rolling elements. The rolling element bearing assembly includes the bearing and a compliant anti-rotation ring compressed between the bearing outer ring and the stationary structure. The compliant ring provides improved frictional engagement and improved bearing damping between the bearing outer race and the stationary structure preventing outer ring rotation within the stationary housing.

Abstract: A multifunction integrated power unit (MIPU) (10) for use aboard aircraft provides the functions both of an auxiliary power unit and of an emergency power unit while being smaller, lighter, and less expensive than the two units it replaces. Additionally, the integration of both functions in a single unit allows elimination of duplicated service devices and a further reduction in size, cost, and weight in the aircraft itself. The MIPU (10) includes two turbine engines (12, 22) operable under differing conditions, an integrating gear box (34) receiving power from the two engines (12, 22) selectively, and a plurality of accessory devices (36, 38) receiving shaft power from either of the two engines (12, 22) via the gear box (34). The gear box (34) includes a power transfer unit (PTU) apparatus (108) which selectively delivers shaft power from one of the engines (12, 22) to the accessory devices (36, 38).

Abstract: A gearless air motor utilizes a high speed rotor having turbine buckets defined in epoxy rather than metal to substantially avoid the danger inherent in high speed rotor fragmentation. The unit has a housing which contains the compressed air chamber, the rotor chamber and a speed reduction chamber in which a toothed belt speed reduction system avoids the use of gears for speed reduction, with their relatively high friction and noise output.

Abstract: A differential gear assembly which is suitable for providing a power off-take from a gas turbine engine, comprises first and second power input gears which drive a plurality of idler gears rotatably mounted on a common cage structure. The idler gears are grouped in meshing pairs so that one idler gear of each pair is additionally in meshing engagement with one of the power input gears and the other idler gear of each pair is additionally in meshing engagement with the other of the power input gears. Together the first and second power input gears drive the common cage structure at the mean speed of the power input gears and the common cage structure in turn drives a single power output shaft.

Abstract: A propfan turbo-engine has two shrouded propfan rotors arranged upstream of a gas turbine which are driven by a contra-rotating working turbine. In addition to a favorable flow onto the blades, a low weight of the engine can be achieved.

Abstract: The present invention provides a high bypass turbofan engine configuration wherein a fan drive turbine is divided into first and second turbine sections mounted for independent rotation within the engine frame. The first, higher pressure, higher speed turbine section is coupled to the fan section drive shaft via a gear box which reduces the rotational speed of the power delivered by the higher pressure first turbine section to match the design rotational speed of the fan section. The second turbine section, having a larger diameter and lower rotational speed as compared to the first turbine section, is directly connected to the fan section and drives the fan section at the same rotational speed as that of the second turbine section. In this manner, the fan drive shaft horsepower is provided while reducing the weight and size of the necessary gearing between the fan drive turbine and the fan. The weight and size of the fan drive turbine and the booster compressor are also reduced.

Abstract: In a gas generator of a gas turbine, the turbine is provided with more stages than aerodynamically necessary for reducing the turbine rotational speed. As a result thereof, the stresses of the turbine rotor are reduced, the latter can be made of ceramic material, and the turbine inlet temperature can be increased. In order to permit the compressor to continue to operate at optimum rotational speed, the compressor is coupled with the turbine by way of a transmission providing a speed-up. Owing to this arrangement, the thermal efficiency and therewith the economy of the gas turbine can be considerably increased and the heretofore occurring problems with the use of ceramic material in the turbine are solved in a simple manner.

Abstract: A power turbine and first stage gear reduction assembly for a gas coupled gas turbine engine includes a first stage reduction gear, a tubular pinion shaft carrying a first stage pinion gear, and a power turbine shaft having a power turbine at a turbine end thereof. The first stage pinion gear and the first stage reduction gear are straddle mounted on an engine block of the gas turbine engine for rotation about parallel primary and secondary axes of the engine, respectively, and in meshing engagement. The power turbine shaft is aligned on the primary axis with a power transfer end thereof within and connected to the pinion shaft through a self-holding taper connection so that the power transfer end of the pinion shaft is supported on the engine block for rotation about the primary axis.

Abstract: A gas turbine drive (1) is presented, for which an auxiliary device power unit (16) can be coupled alternately with the low-pressure rotor (2) or the high-pressure rotor (3).

Abstract: A gas turbine engine for vehicular road type operation includes a gasifier spool and a power turbine spool driven by gases from a gas turbine engine combustor and wherein the gasifier spool includes first and second shaft portions thereon one of which is connected to the gasifier compressor and the other of which is connected to the gasifier turbine.

Abstract: A gas turbine engine for vehicles in which an infinitely variable transmission in the form of a hydraulic transmission is coupled to the engine. A flywheel stores and releases braking energy, and has a disengageable coupling connecting the flywheel with the variable transmission to at least one wheel drive shaft. The hydraulic transmission has a pump unit and a motor unit which are hydraulically operable. The pump unit and motor unit are reversible for braking the vehicle, whereby the motor is driven by the wheels of the vehicle and operates as a pump, and the pump unit operates as a motor.

Abstract: A regulating system for a prime mover, especially a single-spool gas turbine for use in propelling a motor vehicle or aircraft, in which system there is provided a first speed governor for controlling the fuel flow or input power and a second speed governor for controlling the power output. The two speed governors act concurrently in response to the speed of the prime mover and regulate the power input and power output independently of one another.

Abstract: A torque control system designed to economize on consumed fuel includes a source of motive power, a load and a transmission coupling the motive power to the load. A torque measuring device is attached to the output of the transmission and senses a torque applied to the load. The output of the torque sensor is compared with electrical analogs of optimized torque situations. The comparison results in the development of a control voltage which is applied to the source of motive power and the transmission to effect optimization of torque control.

Abstract: In order to obtain a low-cost, light-weight automotive gas turbine plant, the latter is provided with a compressor operating on a first shaft and a turbine operating on a second shaft formed as an element separate from that of the rotor. An infinitely variable transmission interconnects the first and second shafts and ensures that sufficient power for any operational condition is transferred from the turbine to the compressor.

Abstract: In order to provide adequate space for bumpers and auxiliaries, the propulsion engine of a vehicle is arranged transversely with respect to the longitudinal axis of the vehicle. The engine is a gas turbine unit having its power take-off shaft parallel to its rotor axis. The power transmission to the wheels of the vehicle includes a differential located outside the engine and below the same, being connected to the power take-off shaft by a transmission including a reversing step.

Abstract: A power train having a gas turbine engine with controlled power transfer between the load turbine drive train and the compressor turbine drive train and a power shift transmission is shown. The engine control system includes a fuel control responsive to input and output speeds and compressor discharge pressure and an output power characteristic, horse power and torque, program control responsive to compressor and auxiliary torque and speed controlling the power transfer clutch between the compressor and engine to maintain proper turbine inlet temperature at a proper constant high value in a wide range of operation for optimum efficiency. Overcontrols responsive to acceleration and the temperature of the power transfer clutch and ambient air are provided. The power shift transmission control pressure is controlled by compressor discharge pressure and engine output or transmission input speed to provide a shift actuating pressure proportional to the torque produced by the engine.