A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

A control device (101) that controls a fuel gas supply system (100) that comprises: a compressor (1) that supplies compressed fuel gas to a load apparatus (15); an inflow amount regulating means (5) that regulates the amount of fuel gas that flows into the compressor (1); and an anti-surge valve (7) that is for returning to an inlet side of the compressor (1) fuel gas that is discharged from the compressor (1). The control device (101) comprises: a main pressure-control unit (101a) that controls the inflow amount regulating means (5) and the anti-surge valve (7) on the basis of a feedforward control value that is generated on the basis of the load of the load apparatus (15) and of a prescribed conversion process, and on the basis of a feedback control value that is generated on the basis of the deviation between a set value and a measured value for the discharge pressure of the compressor (1); and an emergency pressure-control unit (101b) that calculates a bias-added control value that is found by adding a predetermined bias value to an anti-surge valve control value that is for controlling the anti-surge valve (7) and that is calculated on the basis of at least one of the feedforward control value and the feedback control value, and that, on the basis of the occurrence of load variations that are at or above a prescribed value, switches between the anti-surge control value and the bias-added control value and controls the anti-surge valve (7).

A method of determining at least one fuel characteristic of a fuel provided to a gas turbine engine of an aircraft includes making an operational change, the operational change being effected by a controllable component of a propulsion system of which the gas turbine engine forms a part, and being arranged to affect operation of the gas turbine engine, sensing a response to the operational change; and determining the at least one fuel characteristic based on the response to the operational change.

An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

In one or more arrangements, a pumping system is presented having a plurality of pumps with inlets and outlets, wherein liquid enters the pumps through the inlets and exists the pumps through the outlets. In one or more arrangements, the pumping system has a plurality of engines configured to provide power to the plurality of pumps. In one or more arrangements, the pumping system has a plurality of tubes connected to the plurality of pumps such that liquid exiting the plurality of pumps flows through the plurality of tubes. In one or more arrangements, the plurality of tubes, and liquid flowing through the plurality of tubes, converge at an intersection. In one or more arrangements, the pumping system has a baffle positioned at the intersection to smooth the convergence of the liquid flowing through the plurality of tubes.

An anti-icing system includes a nozzle assembly, a bleed air supply, a bleed control valve assembly, and a controller. The bleed air supply is configured to direct pressurized bleed air to the nozzle assembly. The bleed air supply includes a first pressure sensor configured to measure a first pressure of the pressurized bleed air. The bleed control valve assembly includes a control valve and a valve actuator. The control valve is positionable to control a flow rate of the pressurized bleed air. The valve actuator is configured to control a position of the control valve. The controller is configured to identify a power condition of the bleed air supply as a first power condition or a second power condition and control the valve actuator to position the control valve in a fully opened position for the first power condition and in a predetermined position based on the first pressure for the second power condition.

A system and method for providing bleed air compensation for a continuous power assurance analysis of a gas turbine engine includes estimating bleed air flow rate from the gas turbine engine, estimating a shift in power turbine inlet temperature based on the estimated bleed air flow rate, and applying the estimated shift in power turbine inlet temperature to the continuous power assurance analysis of the gas turbine engine.

A control device that controls a fuel gas supply system that has: a compressor that supplies compressed fuel gas to a load apparatus; an inflow amount regulating means that regulates the amount of fuel gas that flows into the compressor; an anti-surge valve that is for returning to an inlet side of the compressor fuel gas that is discharged from the compressor; and an inlet pressure-regulating valve that regulates the pressure of fuel gas supplied toward the inflow amount regulating means. The control device includes: a main pressure-regulating unit that controls the inflow amount regulating means and the anti-surge valve using a first feedforward control value that is generated on the basis of the load of the load apparatus and of a first conversion process and using a feedback control value that is generated on the basis of the deviation between a set value and a measured value for the discharge pressure of the compressor; and an inlet pressure-regulating unit that controls the inlet pressure-regulating valve using a second feedforward control value that is generated on the basis of the load of the load apparatus and of a second conversion process.

An electric air pump includes an impeller and a blower motor coupled to the impeller and configured to drive the impeller to rotate and generate air pressure. The electric air pump also includes a power interface in electrical communication with the blower motor and configured to supply alternating current to power the blower motor. The electric air pump further includes an adjustable speed motor drive electrically coupled to the power interface and the blower motor to steplessly regulate the air pressure generated by the impeller via the blower motor.