A method of thermodynamic assessment of flow through a turbomachine having a compressor, comprising: receiving sensor readings from a plurality of acoustic sensors located about an intake for the turbomachine upstream of the compressor; and receiving pressure and stagnation temperature readings for the flow into the intake. A static temperature is determined for the flow into the intake and an average velocity of the flow over a flow area of the intake upstream of the compressor using the acoustic sensor readings. A mass flow rate of the flow through the intake is determined using the average velocity of the flow and the stagnation pressure.

A system includes a gas turbine engine and a controller operable to determine a closing threshold with respect to an upper limit and an opening threshold with respect to a lower limit of a movement range of an effector of the gas turbine engine based on an on-board model, where the upper limit and the lower limit are defined for a target parameter of the gas turbine engine. The controller determines a projected state of the target parameter absent a correction command to the effector, applies a closing correction to the effector based on determining that the projected state of the target parameter would result in being above the closing threshold, and applies an opening correction to the effector based on determining that the projected state of the target parameter would result in being below the opening threshold.

Systems, program products, and methods for adjusting operating limit (OL) thresholds for compressors of gas turbine systems based on mass flow loss are disclosed herein. The systems may include at least one computing device in communication with the gas turbine system, sensor(s) measuring operational characteristic(s) of the gas turbine system, and a pressure sensor measuring an ambient fluid pressure surrounding the gas turbine system. The computing device(s) may be configured to adjust operational parameters of the gas turbine system by performing processes including determining a mass flow loss between an estimated, first mass flow rate and a calculated, second mass flow rate for the compressor of the gas turbine system, and adjusting an OL threshold for the compressor of the gas turbine system based on the mass flow loss. The OL threshold for the compressor may be below a predetermined surge threshold for the compressor.

The invention relates to a method for determining a fluid conveying parameter, a fluid conveying device, particularly for determining a volumetric flow, comprising the steps of

Determining excitation information for mechanical excitation of at least one fluid conveying element of the fluid conveying device in at least one spatial direction by at least one first sensor means,

Providing operating information, comprising at least a value of an operating variable of the fluid conveying device by means of a providing means,

Analyzing the information provided and determined,

Determining a fluid conveying parameter, particularly a volumetric flow, of the fluid conveying device based on the analyzed information.

In IHSs (Information Handling Systems), cooling is provided by increasing the airflow generated by cooling fans. However, unnecessary airflow cooling results in noise and wasted energy. An IHS processor may support faster operating frequencies when cooled below an upper threshold, but these operating frequencies drop at temperatures below a lower threshold. Embodiments provide techniques for calibrating the cooling of an IHS to the thermal characteristics of a specific processor since manufacturing variances result in processors having differing responses to cooling. A turbo frequency supported by a processor is measured at a series of temperature margins that are progressively lower than the processor's specification temperature. A rate of increase in the measured turbo frequencies is determined at each of the temperature margins. A first temperature margin is identified at which the rate of increase in turbo frequencies falls below a threshold. This margin is used in providing airflow cooling.

A feed pump to increase the pressure in a line includes a pumping chamber for a pumping medium. At least one temperature sensor, which is arranged in the feed pump, is allocated to the pumping chamber and is in thermal contact with the pumping chamber for determining a temperature of the pumping medium in the pumping chamber. A temperature control device is allocated to the at least one temperature sensor and by which defined temperature conditions can be created in an area surrounding the at least one temperature sensor. An evaluation device to which the at least one temperature sensor is coupled for signal purposes uses the data from the at least one temperature sensor to determine whether pumping medium is flowing through the pumping chamber or not.

The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

A steam turbine includes: a rotor; a casing; a thrust bearing; a steam inlet; a first pipe; a first regulation valve; a second pipe; a second regulation valve; and a control device. The control device estimates an exhaust flow rate of the steam turbine based on an operating point map which derives the exhaust flow rate of the steam turbine from an operating point of the steam turbine and estimates the thrust force applied to the thrust bearing based on the exhaust flow rate.

The present disclosure provides a method for maintaining stable combustion of a gas turbine during a dynamic process, a computer-readable medium, and a gas turbine control system. The method comprises: compensating a fuel control valve stroke command δ.sub.f,CLC with a fuel flow compensation function G.sub.f,COMP(s); and compensating a VIGV command θ.sub.VIGV,CLC with an air flow compensation function G.sub.air,COMP(s), wherein the fuel flow compensation function G.sub.f,COMP(s) and the air flow compensation function G.sub.air,COMP(s) satisfy the following relation: G.sub.f,COMP(s).Math.G.sub.f(s)=G.sub.air,COMP(s).Math.G.sub.air(s), and an fuel-to-air ratio is directly proportional to δ.sub.f,CLC/θ.sub.VIGV,CLC even during the dynamic process, where G.sub.f(s) represents an overall transfer function of a fuel channel from a fuel control valve servo system to an inlet of a combustion chamber, and G.sub.air(s) represents an overall transfer function of an air channel from a VIGV servo system to the inlet of the combustion chamber.

Systems, program products, and methods for adjusting operating limit (OL) thresholds for compressors of gas turbine systems based on mass flow loss are disclosed herein. The systems may include at least one computing device in communication with the gas turbine system, sensor(s) measuring operational characteristic(s) of the gas turbine system, and a pressure sensor measuring an ambient fluid pressure surrounding the gas turbine system. The computing device(s) may be configured to adjust operational parameters of the gas turbine system by performing processes including determining a mass flow loss between an estimated, first mass flow rate and a calculated, second mass flow rate for the compressor of the gas turbine system, and adjusting an OL threshold for the compressor of the gas turbine system based on the mass flow loss. The OL threshold for the compressor may be below a predetermined surge threshold for the compressor.