An antisurge controller for a turbocompressor system stores multiple control algorithms in a memory for the antisurge controller. The antisurge controller identifies capabilities of field devices in the turbocompressor system. The field devices include an antisurge valve and multiple sensors. The antisurge controller selects one of the multiple control algorithms based on the identified capabilities and applies the selected control algorithm to the turbocompressor system. The selected control algorithm provides the smallest surge control margin, of the surge control margins in the multiple control algorithms, that are supported by the identified capabilities.

A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.

A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades. A lower pressure tap and a higher pressure tap tap air from two distinct locations within the compressor and radially outwardly through the outer housing. A valve selectively delivers at least one of the lower pressure tap and the higher pressure tap to the bore of the disc. A control for the valve is programmed to move the valve to a position delivering the higher pressure tap at a point prior to take-off when the compressor is mounted in a gas turbine engine on an aircraft. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

A vehicle having an engine system which can detect an expected compressor surge event while the compressor is operating in a stable region of a compressor map, and upon detecting the expected compressor surge event controlling one or more engine operating parameters to maintain compressor operation in the stable region of the compressor map without transgressing (or mitigating the transgression of) a compressor surge line on the compressor map which, if transgressed, may cause compressor surge to occur.

An anti-surge recycle valve system for a natural gas line using a pipeline rotary control valve for controlling gas flow through the gas line and a valve controller having a surge-programmable feature including a threshold setpoint deviation limit, which is used to control first and second control valve loops. The first solenoid valve loop drives a rotary high-pressure piston actuator when the linear position sensor determines a setpoint deviation in gas flow below the threshold deviation, and the second solenoid valve loop drives the rotary high-pressure piston actuator when the linear position sensor determines a setpoint deviation in gas flow above the threshold deviation. The system provides ultra-rapid stroking speed in tandem with highly accurate and stable positioning.

A method for controlling takeoffs of mechanical energy and/or air on a turbine engine for the propulsion of an aircraft. It is based on a protocol for the exchange of a request/authorization between and by the energy manager and a system for controlling the turbine engine. This protocol is implemented as a result of a modification of the takeoff requirement. It is intended to check whether the surge margin is compatible with the modification of the takeoff requirement and, if the need arises, to apply temporary measures in order to prevent surge in the turbine engine, for example by providing at least a part of the energy requirements by a buffer. This permits the optimization of the operation of a turbine engine for the propulsion of an aircraft, while avoiding the risk of surge of the turbine engine.

A surge avoidance control method that includes a surge detection step of determining whether the operation point of the compressor is positioned in a surge operation region at each predetermined timing; a surge avoidance opening-degree calculation step calculating a surge avoidance opening degree of the operation device necessary for moving the operation point of the compressor determined to be positioned in the surge operation region in the surge detection step out of the surge operation region; a correction opening-degree calculation step calculating a correction opening degree of the operation device on the basis of a moving velocity of the operation point of the compressor which is determined to be positioned in the surge operation region in the surge detection step; and an opening-degree command value calculation step calculating an opening-degree command value of the operation device on the basis of the surge avoidance opening degree and the correction opening degree.

A system and method for supplying compressed air from an auxiliary power unit to a main engine starter motor. The inlet guide vanes are controlled using either first or second inlet guide vane control logic and the surge control valve is controlled using either first or second surge control valve control logic. When the first inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand signal, when the second inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand schedule, when the first surge control valve logic is used, the surge control valve can be commanded to repeatedly move to only a fully-closed position and a fully-open position, and when the second surge control valve logic is used, the surge control valve can be commanded to the fully-closed position only when maximum flow is commanded.

A bleed air valve comprises a piston that moves along a guide, where the piston includes a first surface and an opposing second surface. A pressure divider network includes a divider network inlet having an inlet cross sectional area in fluid communication with a fluid passage, a divider network outlet having an outlet cross sectional area in fluid communication with ambient pressure, and a network chamber in fluid communication with the divider network inlet and the divider network outlet. The network chamber has a pressure value between pressure at the divider network inlet and pressure at the divider network outlet. A shuttle valve includes a shuttle inlet and a shuttle outlet, where the shuttle outlet is in fluid communication with the first surface. An electromechanical valve receives a command signal and in response provides compressed air to an electromechanical valve output that is in fluid communication with the shuttle inlet.

Systems and methods are provided that use compressed gas from a tank in an aircraft to avoid and/or recover from a compressor surge. Systems and methods are provided that use compressed gas from a tank to startup a gas turbine engine in an aircraft, where the gas turbine engine is configured as a prime power engine for the aircraft.