Abstract:
An aircraft includes one or more engines configured to generate high-pressure bleed air and low-pressure bleed air. An aircraft environmental control system (ECS) is in fluid communication with one or more of the engines to receive the high-pressure bleed air and the low-pressure bleed air. The ECS calculates a synthesized low-pressure value associated with the low-pressure bleed air while still providing bleed air using the high pressure bleed air. The ECS further switches from the high pressure bleed air to the low-bleed pressure air through the ECS while blocking flow of the high-pressure bleed air through the ECS based on the synthesized low-pressure value.
Abstract:
A piston configuration is provided, the configuration including a piston having a ring seat and a piston ring disposed within the ring seat. The piston ring is configured to form a sealing surface between a surface of the piston ring and a surface of the ring seat. The sealing surface is formed when a first pressure on a first side of the piston ring is greater than a second pressure on a second side of the piston ring. At least one fluid channel is configured to increase a surface area on the piston ring that is subject to the second pressure.
Abstract:
A piston seal includes an inner surface configured to extend proximate a perimeter of a piston. Also included is an outer surface disposed proximate a chamber wall, wherein the chamber wall defines a chamber for the piston and the piston seal to translate within. Further included is a first axial side exposed to a first pressure portion of the chamber. Yet further included is a second axial side exposed to a second pressure portion of the chamber. Also included is at least one pressure differential reducing hole extending radially through the piston seal from the inner surface to the outer surface.
Abstract:
A valve system includes a valve for controlling flow of a fluid and a valve controller for providing fluid to control the movement of a valve actuator. The valve includes a flow control device, a modulating chamber, and the valve actuator. The valve actuator is movable within the modulating chamber to open and close the flow control device. The valve controller includes a channel within the valve controller and an inlet port for connecting the channel and a high pressure source. The valve controller also includes an exhaust port for connecting the channel and an ambient pressure and a modulating port connecting the channel to the modulating chamber. The valve controller further includes an armature movable relative to the channel. The armature closes the inlet port and the exhaust port in a first position, the armature opens the inlet port and closes the exhaust port in a second position, and the armature opens the exhaust port and closes the inlet port in a third position. The valve controller also includes an electromagnetic motor adjacent to the channel for moving the armature.
Abstract:
An aircraft includes one or more engines configured to generate high-pressure bleed air and low-pressure bleed air. An aircraft environmental control system (ECS) is in fluid communication with one or more of the engines to receive the high-pressure bleed air and the low-pressure bleed air. The ECS calculates a synthesized low-pressure value associated with the low-pressure bleed air while still providing bleed air using the high pressure bleed air. The ECS further switches from the high pressure bleed air to the low-bleed pressure air through the ECS while blocking flow of the high-pressure bleed air through the ECS based on the synthesized low-pressure value.
Abstract:
A piston configuration is provided, the configuration including a piston having a ring seat and a piston ring disposed within the ring seat. The piston ring is configured to form a sealing surface between a surface of the piston ring and a surface of the ring seat. The sealing surface is formed when a first pressure on a first side of the piston ring is greater than a second pressure on a second side of the piston ring. At least one fluid channel is configured to increase a surface area on the piston ring that is subject to the second pressure.