A fire truck pump flow prediction system includes a pump, an inlet pipe connected to the pump, a discharge pipe connected to the pump, an intake pressure sensor connected to the inlet pipe, a discharge pressure sensor connected to the discharge pipe, a rotational sensor associated with the pump and a central processor connected to the intake pressure sensor, the discharge pressure sensor and the rotational sensor. The intake pressure sensor is configured to detect fire suppressant inlet pressure and the discharge pressure sensor is configured to detect fire suppressant discharge pressure. The rotational sensor configured to detect a rotational speed of the pump. The central processor configured to determine a flow through the pump and into the discharge pipe based on the inlet pressure, the discharge pressure and the rotational speed.

A system includes a dynamic compressor to compress a working fluid and a controller. The controller is connected to the dynamic compressor and includes a processor and a memory. The memory stores a map of predetermined operating points of the dynamic compressor, each predetermined operating point including a mass flow of the compressor at that predetermined operating point. The memory stores instructions that program the processor to operate the dynamic compressor to compress the working fluid and determine a current operating point of the compressor. The instructions program the processor to calculate the mass flow for the current operating point from the map of the plurality of predetermined operating points. The instructions further program the processor to continue to operate the dynamic compressor to compress the working fluid based at least in part on the calculated mass flow for the current operating point.

The present disclosure provides methods and systems for determining a synthesized engine parameter of a gas turbine engine. An initial model parameter is obtained from an onboard model associated with the gas turbine engine. A correction factor for the onboard model is determined by modifying a difference between the onboard model and an aero-thermal model of the gas turbine engine using first and second engine parameters and first and second operating conditions, wherein the first and second engine parameters are independent from one another over an operating envelope of the gas turbine engine. The initial model parameter is scaled by applying the correction factor thereto to obtain a corrected model parameter. The corrected model parameter is output as the synthesized engine parameter.

A turbine engine including a fan, a nacelle circumscribing at least the fan, a compressor section downstream of the fan, and a conduit defined, at least in part, by the nacelle. The conduit includes a first opening at the compressor section, a second opening downstream of the fan and upstream of the compressor section, and a third opening upstream of the fan. Pressure sensors coupled to the nacelle are communicatively coupled to at least one actuator. The at least one actuator can adjust airflow between the first opening and the second opening, or between the first opening and the third opening. The pressure sensors can provide outputs for generating commands that control the at least one actuator.

There are described methods, systems, and assemblies for monitoring a bleed valve of a gas turbine engine. The method comprises determining a rate of change of a gas generator speed of the gas turbine engine; determining a rate of change of a parameter indicative of engine power of the gas turbine engine; comparing at least one ratio based on the rate of change of the gas generator speed and the rate of change of the parameter indicative of engine power to at least one range of values; detecting a modulation delay of the bleed valve when the at least one ratio is within the at least one range of values; and transmitting a signal indicative of the bleed valve malfunction in response to detecting the modulation delay.

A refrigerant compressor according to an exemplary aspect of the present disclosure includes, among other things, a first stage and a second stage downstream of the first stage, and a cooling line configured to cool power electronics. The cooling line is configured to be switched between a first mode and a second mode. The first mode is configured to dump refrigerant between the first stage and the second stage, and the second mode is configured to dump refrigerant upstream of the first stage.

Embodiments of a direct-drive fan system and a variable process control system are disclosed herein. The direct-drive fan system and the variable process control system efficiently manage the operation of fans in a cooling system such as a wet-cooling tower or air-cooled heat exchanger (ACHE), HVAC systems, mechanical towers or chiller systems.

Method for controlling a plural stage compressor comprising at least a first stage (10), a second stage (20) and a first inter-stage line (12) between the first stage (10) and the second stage (20), comprising the steps of: a—measuring the temperature at the inlet of the compressor, b—measuring the ratio between the outlet pressure (Pout) and the inlet pressure (Pin) of the first stage (10) of the compressor, c—calculating a coefficient (ψ) based at least on the value of the inlet temperature (Tin) and on the measured pressure ratio (Pout/Pin), d—if the calculated coefficient (ψ) is in a predetermined range, acting on a control valve (70; 76; 92) mounted in a line (4; 8) supplying the inlet of the first stage (10) of the compressor or in a gas recycle line (74) which opens into the first inter-stage line (12).

Methods, apparatus, systems, and articles of manufacture are disclosed to detect air flow separation of an engine. An example apparatus includes hardware, and memory including instructions that, when executed, cause the hardware to at least determine an inlet flow separation parameter based on a first pressure value from a first pressure sensor included in a nacelle of a turbofan and a second pressure value from a second pressure sensor included in the nacelle, determine a severity level parameter based on the inlet flow separation parameter, the severity level parameter based on a difference between the first pressure value and the second pressure value, and adjust a contribution of airflow from aft of a fan of the turbofan based on the severity level parameter.

Method for controlling a plural stage compressor comprising at least a first stage (10), a second stage (20) and a first inter-stage line (12) between the first stage (10) and the second stage (20), comprising the steps of: a—measuring the temperature at the inlet of the compressor, b—measuring the ratio between the outlet pressure (Pout) and the inlet pressure (Pin) of the first stage (10) of the compressor, c—calculating a coefficient (ψ) based at least on the value of the inlet temperature (Tin) and on the measured pressure ratio (Pout/Pin), d—if the calculated coefficient (ψ)is in a predetermined range, acting on a control valve (70; 76; 92) mounted in a line (4; 8) supplying the inlet of the first stage (10) of the compressor or in a gas recycle line (74) which opens into the first inter-stage line (12).