Abstract:
The differential transmission mechanism has an output differential (10). A first hydraulic displacement unit (18) having a normally fixed, approximately maximum displacement is connected to the output differential. A second hydraulic displacement unit (16) which is of variable displacement is connected to an input shaft (12). Additional components of the output differential are connected to the input shaft (12) and to an output shaft (14). An output shaft speed sensing device (32) controls the displacement of the variable displacement hydraulic displacement unit (16) to achieve a constant output speed. A sensor and control (74) responds to a reduced speed of the input shaft (12) to reduce the displacement of the fixed displacement unit (18) to effectively make the latter displacement unit a smaller, faster unit and extend the constant output speed range at the low end of the input speed range.
Abstract:
In a dynamoelectric machine a disadvantageous feature is that coolant tends to find its way into an airgap between a rotor and a stator to cause friction and windage losses. This problem is solved by an end turn construction to improve cooling in the dynamoelectric machine and to axially reduce the size thereof. The machine includes a body (12) of magnetizable material having opposed ends (18), an opening (14) extending between the ends (18), and the plurality of slots (50) about the opening (14). A rotor (16) is disposed within the opening (14) and journalled for rotation therein and electric conductors (52) are located in the slots (50) and extend to ends (54, 56) just past the ends (18) of the body (12). End turns (58, 60, 62 and 68) each interconnect a predetermined pair of conductors (52) and extend substantially circumferentially and radially of the rotor axis with no appreciable extension axially of the axis.
Abstract:
A combined engine starting and power generating system includes an engine (110) connected to a dynamoelectric machine (142) useable as a motor or as a generator via a differential (114). The system utilizes variable and fixed displacement hydraulic units (146, 156) sized for power generating operation. An auxiliary fixed displacement hydraulic unit (162) is provided for use only during an engine starting mode.
Abstract:
Prior power supply systems which develop constant-frequency AC power and/or DC power from variable-speed motive power require complex electrical power converters, special electromagnetic machines or bulky constant speed drives. These components may render the system unsuitable for use in some applications. In order to overcome this problem, a power supply system for developing electrical power from variable-speed motive power produced by a prime mover includes a differential speed summer (18) having a first shaft (16) coupled to the prime mover (12) and further having second and third shafts (20, 24) coupled to first and second generators (22, 26), respectively, a power conditioner (30) coupled to the second generator (26) for conditioning the power developed thereby and means (34) for regulating the conditioned power developed by the second generator (26) so that the first generator (22) develops constant-frequency AC power.
Abstract:
Prior starting/generating systems which operate a generator as a motor to start a prime mover have been inefficient since motive power was delivered to the prime mover through hydrostatic trim and differential components of a constant speed drive interposed between the prime mover and the generator. In order to overcome this problem, means (78) are provided between the prime mover (16) and the generator (12) for bypassing these components of the constant speed drive (14) when operating in a starting mode so that motive power is transferred directly to the prime mover (16). This, coupled with the fact that the generator (12) is operated as a motor in accordance with generator speed and/or generator power factor, increases the efficiency of the system when in the starting mode.
Abstract:
An aircraft secondary power system having a selectively operable power source (40, 70, 100) for drive of accessories and for starting of a jet engine. The system includes a clutch (50, 79, 109) which is engaged when the power source is to start the engine. At a predetermined engine speed, the engine takes over the drive of the accessories through the clutch and, at a selected higher speed of the engine, the clutch is disengaged to cause the drive of the accessories from the engine at a lower drive ratio whereby the accessories are driven at a lower speed relative to the speed of the engine.
Abstract:
The problem of reducing the effect of inaccuracies in rotor position detection for an engine starting system is solved in an engine start control apparatus (10) operating a generator (12) as a synchronous motor which employs acceleration control. The motor (12) receives power from a main inverter and an excitation inverter (48). The inverters (46, 48) are controlled by a control unit (22) which provides for acceleration control and closed loop reactive power control. The control unit (22) includes a pulse width modulation generator (100) which is responsive to a voltage command and a commutation command to develop switching signals for controlling the switches (S1-S6) in the main inverter (46). The voltage command is used to vary the duty cycle of the PWM signals. The commutation angle command is used to control the timing of the PWM signals. The commutation angle command is determined in accordance with an acceleration reference (112) and rotor position (70) feedback in a closed loop manner to maintain generally constant acceleration.
Abstract:
The effects of operational loading on a permanent magnet generator of the type having first and second permanent magnet assemblies (28, 30) mounted on a shaft (26), and movable relative to each other is eliminated by rotatably mounting each of the assemblies (28, 30) for rotation relative to the shaft (26), as well as to each other, and connecting them to the shaft by equal, but oppositely pitched helical spline connections (50, 52, 58, 60). Axial movement of the shaft (26) will then cause equal, but opposite, relative movement of the permanent magnet assemblies (28, 30) so that the forces resisting movement of one such assembly act to encourage movement of the other, thereby balancing out said forces.
Abstract:
The differential transmission mechanism has an output differential (10). A first hydraulic displacement unit (18) having a normally fixed, approximately maximum displacement is connected to the output differential. A second hydraulic displacement unit (16) which is of variable displacement is connected to an input shaft (12). Additional components of the output differential are connected to the input shaft (12) and to an output shaft (14). An output shaft speed sensing device (32) controls the displacement of the variable displacement hydraulic displacement unit (16) to achieve a constant output speed. A sensor and control (74) responds to a reduced speed of the input shaft (12) to reduce the displacement of the fixed displacement unit (18) to effectively make the latter displacement unit a smaller, faster unit and extend the constant output speed range at the low end of the input speed range.
Abstract:
An aircraft secondary power system having a selectively operable power source (40, 70, 100) for drive of accessories and for starting of a jet engine. The system includes a clutch (50, 79, 109) which is engaged when the power source is to start the engine. At a predetermined engine speed, the engine takes over the drive of the accessories through the clutch and, at a selected higher speed of the engine, the clutch is disengaged to cause the drive of the accessories from the engine at a lower drive ratio whereby the accessories are driven at a lower speed relative to the speed of the engine.