Abstract: Temperature regulation of an air cycle refrigeration system is achieved by selectively adjusting the turbine stator geometry in response to the temperature of turbine airflow at a desired location. Such adjustment in stator geometry includes the selective positioning of a portion of the stator adjacent the turbine blades thereby controlling the amount of cooling produced by the turbine or the selective opening and closing of bypass ports provided in the turbine stator to control the flow of air through the turbine. Both of these adjustments in stator geometry are effected by an actuator comprising at least two members of differing coefficients of thermal expansion such as a bimetallic element.

Abstract: An apparatus for improving the efficiency of a turbo-supercharger at low load levels is disclosed. The apparatus includes an annular gas inlet housing which encircles the turbine of the turbo-supercharger and which housing includes an inlet for gases flowing toward the turbine. Arranged within the housing is a diaphragm, an outer periphery of which diaphragm is connected to the housing. Connected to the inner periphery of the diaphragm is a guide vane ring. Biasing springs, arranged within the housing, urge the diaphragm, and thus the guide vane ring connected to the diaphragm, toward the inlet.

Abstract: An arrangement for controlling the apparent curvature of diffuser vanes of turbine fan to reduce stalling of the vanes and increase efficiency of the fan output over a wider range of flow demand. Sensors responsive to pressure on opposite sides of the vanes selectively control the discharge of pressurized fluid from the diffuser vanes to effect their apparent curvature changes. The arrangement has particular use in a ride control system for surface effect ships.

Abstract: A diffuser control for controlling vapor flow through a diffuser passage comprising an annular recess defined by a housing of the passage and in communication therewith, a diffuser control ring supported for movement within the annular recess and the diffuser passage between a full throttling position, wherein the restriction means throttles vapor flow through the diffuser passage, and an open position for permitting a substantially free flow of vapor through the diffuser passage. The control further comprises a first set of springs for urging the control ring toward the full throttling position, and a second set of springs for urging the control ring toward an intermediate throttling position located between the open and full throttling positions. The diffuser control also comprises a low pressure conduit for connecting the annular recess to a low pressure source, and a intermediate pressure conduit for connecting the annular recess to an intermediate pressure source.

Abstract: The disclosed system detects the pressure rise across the fan and the flow rate in the system and integrates signals corresponding thereto, and outputs a signal to indicate to the user when the pressure rise exceeds a given level for a corresponding flow rate to warn of a condition within a given degree of a stall condition. The system outputs another signal to block any increase in fan blade pitch and substitutes a decrease pitch signal in response to a predetermined closer approach to a stall condition so that the pitch of the blades is reduced to a position in which the pressure rate rise and flow rate are reduced to a safe level with respect to a stall condition. The system also includes means responsive to the predetermined closer approach to stall to prevent the user from feeding a blade pitch increase signal following a reduction in the pressure rise across the fan until the user resets a bistable device.

Abstract: This case relates to a variable performance pump wherein the width of the impeller in a centrifugal pump can be regulated while the unit is operating. The impeller's width is regulated by the pump pressure and is controlled by a small external valve. The pump performance may be varied over a wide range to obtain constant head, constant capacity or other desired pumping characteristics.

Abstract: A gas turbine engine has variable vanes in the rear compressor that are automatically scheduled to their optimum position for proper engine operation by a closed loop primary engine control system in response to selected engine operating conditions. A failure in the engine control system may cause the variable vanes to be locked in a position which degrades the engine aerodynamics to a dangerous level. An emergency controller is connected to schedule the position of the variable compressor vanes in an open loop manner in response to changes in the power lever when a failure of the primary engine control system occurs.