The invention relates to the field of mining, specifically to oil extraction using electric centrifugal pump units having a frequency-controlled electric motor, and serves to fully automate oil well operations using an electric centrifugal pump. A method of operating an oil well using an electric centrifugal pump unit, wherein temperature is regulated by means of changing the rotational speed of a pump shaft, which is a novel use of operating temperature as feedback for monitoring the state of the centrifugal pump. Using the invention allows for fully automating the process of launching, putting into an operational mode, and monitoring the operation of the oil well using the electric centrifugal pump unit, which, in turn, increases the overall reliability of the equipment (electric centrifugal pump unit).

The invention relates to a method of monitoring a start-up sequence of a turbomachine that comprises a compressor equipped with a rotor, a starter capable of driving the rotor in rotation and a combustion chamber. The start-up sequence comprises a first phase during which the starter increases the rotation speed of the rotor up to an instant at which fuel is injected into the turbomachine combustion chamber, and a second phase after the first phase that terminates when the starter stops driving the rotor. The method includes: acquisition (ACQ) of a signal representative of the rotation speed of the rotor during the start sequence; detection (DRP1, DRP2, INT) of an instant at which there is a sudden change in the variation of said signal with time, the sudden change instant thus detected being deemed to be the instant at which an air-fuel mix is ignited in the combustion chamber.

A method of determining an inlet total air pressure includes determining a first parameter indicative of a first inlet total air pressure. The method includes executing a sequence that includes: determining a mass air flow passing through the air inlet based on the first parameter, determining a Mach number of air passing through the air inlet based on the mass air flow, determining a static air pressure at the air inlet, determining an air pressure ratio based on the Mach number, generating a subsequent parameter indicative of the revised inlet total air pressure based on the air pressure ratio and the static air pressure, and substituting the subsequent parameter for the first parameter. The method includes executing at least one additional instance of the sequence with the subsequent parameter, and outputting the subsequent parameter as the inlet total air pressure.

A method to predict an onset of flow separation from a surface of an inner barrel of a nacelle is disclosed. In various embodiments, the method includes determining a static pressure distribution about the inner barrel surface of the nacelle; determining a mean static pressure value and a minimum static pressure value using the static pressure distribution; determining a separation indicator value using the mean static pressure value and the minimum static pressure value; and comparing the separation indicator value against a separation threshold value.

Compressor stage with a stator-side intake connection piece via which medium which is to be compressed can be introduced into the compressor stage in the region of the compressor stage, with a stator-side inflow channel via which the medium to be compressed can be conveyed in direction of a rotor-side impeller proceeding from the intake connection piece, wherein the impeller has a radially inner hub, a radially outer cover disk and impeller blades extending between the hub and the cover disk, wherein a plus measuring point and a minus measuring point are provided at the compressor stage for measuring the effective pressure at the compressor stage, and wherein the minus measuring point is positioned upstream of the impeller outside of the stator-side inflow channel in an annular gap which branches off from the inflow channel.

A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

A hydrogen dispensing system includes a hydrogen storage tank for storing hydrogen gas, a turboexpander generator fluidly connected to the hydrogen storage tank, and a dispenser fluidly connected to the turboexpander generator. The turboexpander generator receives a flow of the hydrogen gas from the hydrogen storage tank at an inlet of the turboexpander generator, reduces a pressure and a temperature of the flow of hydrogen gas, and outputs the hydrogen gas to the dispenser.

A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

In accordance with at least one aspect of this disclosure, a system, includes a fuel line defining a fuel inlet and a fuel outlet, configured to provide fuel from a fuel tank to an engine. A boost pump, including a boost impeller, is disposed in the fuel line configured to drive fuel from the fuel inlet to the fuel outlet and operatively connected to the boost pump via a drive shaft. The system includes a fluid line defining a fluid inlet and a fluid outlet, configured to provide fluid from a fluid source to a fluid destination. A fluid turbine is disposed in the fluid line configured to alter a pressure of the fuel line between the fuel inlet and the fuel outlet.

A fan is described, with the aid of which a volume flow and/or a mass flow of a medium moved by the fan (1) can be determined. This fan comprises an electric motor (2) and an impeller (3) driven by the electric motor (2), wherein the impeller (3) moves a gaseous medium in a media flow from an inflow side (5) to an outflow side (7). The fan additionally comprises a pressure sensor system, a speed ascertainment system, and an evaluation unit. The pressure sensor system is designed to ascertain an actual pressure difference (?p*) between a first region (10) and a second region (13), wherein the first region (10) and/or the second region (13) is/are formed in the electric motor (2), wherein a pressure (p.sub.A) prevails in the first region (10), which corresponds to a pressure (p.sub.1) present on the inflow side, wherein a pressure (p.sub.B) prevails in the second region (13), which corresponds to a pressure (p.sub.2) present on the outflow side. The speed ascertainment system is designed to ascertain an actual speed (n) of the impeller (3). The evaluation unit is finally designed to quantitatively determine a mass flow and/or a volume flow of the medium based on the actual pressure difference (?p*), the actual speed (n), and a pressure characteristic curve of the fan (1). Furthermore, an electric motor for this fan and a corresponding method are disclosed.