A pump of a dishwasher has an integrated heating element, a pump chamber with an inlet and an outlet, a pump rotor inside the pump chamber and a drive motor, wherein the heating element and a temperature sensor are provided on a wall of the pump chamber. For measuring a calcification of the pump chamber it is filled with water and then the pump rotor rotates for mixing the water in the pump chamber without transporting water out of the pump chamber. The temperature of the water in the pump chamber is measured with the temperature sensor as a starting temperature, and then the heating element is activated to heat the water in the pump chamber while the temperature of the water in the pump chamber is measured. Then the heating element is deactivated and the maximum temperature of the water during the heating duration or directly afterwards is determined. A temperature relation between the maximum temperature and the starting temperature of the water is calculated. These steps are executed in the pump at the very beginning of an operation of the new dishwasher after its installation for determining an initial temperature relation. These steps are automatically executed again at a later stage for determining a later temperature relation to determine the heating efficiency of the pump by comparing the later temperature relation to the initial temperature relation.

A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R.sub.1 and a primary fan hub radius R.sub.2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R.sub.3 and a secondary fan hub radius R.sub.4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to % Fn.sub.3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ratio of R.sub.1 to R.sub.3 equals $\sqrt{\left(\mathrm{EFP}\right)\frac{\left(1-Rq{R}_{\mathrm{Sec}.-{\mathrm{Fan}}^2}\right)}{\left(1-Rq{R}_{\mathrm{Prim}.-\mathrm{Fa}{n}^2}\right)}\left(\frac{1}{\%{\mathrm{Fn}}_{3S}}-1\right)}$

A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R.sub.1 and a primary fan hub radius R.sub.2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R.sub.3 and a secondary fan hub radius R.sub.4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to %Fn.sub.3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ratio of R.sub.1 to R.sub.3 equals

[00001]$\sqrt{\left(EFP\right)\frac{\left(1-Rq{R}_{sec.-Fan}{}^2\right)}{\left(1-Rq{R}_{Prim.-Fan}{}^2\right)}\left(\frac{1}{\%F{n}_{3s}}-1\right)};$

wherein EFP is between 1.5 and 11, wherein RqRp.sub.rim.-Fan is a ratio of R.sub.1 to R.sub.2, and wherein RqR.sub.Sec.-Fan is a ratio of R.sub.3 to R.sub.4.

A motor controller of the present invention comprises units which obtain information indicative of a motor speed (ω) and information indicative of motor torque (T), an air flow calculation section which calculates an air flow (Q) of a fan based on the motor speed (ω) and the motor torque (T); and a speed command generation section which generates a speed command (ω*) of a motor such that the air flow (Q) coincides with the predetermined air flow command (Q*).

A fuel supply control device controls a fuel supply pump based on a front-rear differential pressure across a metering valve for a fuel supply amount, which is detected by a differential pressure gauge, using parallel flow passages of an orifice and a pressurizing valve as the metering valve, in which the fuel supply control device includes a first control amount generation unit generating a first control amount based on the front-rear differential pressure, a second control amount generation unit generating a second control amount based on the rotation speed of the fuel supply pump, a control amount selection unit, a subtractor, and a control calculation unit, in which the control amount selection unit selects the first control amount in a case where the rotation speed is equal to or lower than a predetermined threshold and select the second control amount in a case where the rotation speed exceeds the threshold.

A control system for limiting a power turbine torque of a gas turbine engine is disclosed. In various embodiments, the control system includes an engine control module configured to output an effector command signal to a gas generator of the gas turbine engine; a power turbine governor module configured to output to the engine control module a power turbine torque request signal; and a power turbine torque limiter module configured to output to the power turbine governor module a power turbine speed rate signal to limit a power turbine speed overshoot of the gas turbine engine.

The present invention belongs to the technical field of control of aero-engines, and proposes an adaptive boosting algorithm-based turbofan engine direct data-driven control method. First, a turbofan engine controller is designed based on the Least Squares Support Vector Machine (LSSVM) algorithm, and further, the weight of a training sample is changed by an adaptive boosting algorithm so as to construct a turbofan engine direct data-driven controller combining a plurality of basic learners into strong learners. Compared with the previous solution only adopting LS SVM, the present invention enhances the control precision, improves the generalization ability of the algorithm, and effectively solves the problem of sparsity of samples by the adaptive boosting method. By the adaptive boosting algorithm-based turbofan engine direct data-driven control method designed by the present invention.

The present invention belongs to the technical field of control of aero-engines, and proposes an adaptive boosting algorithm-based turbofan engine direct data-driven control method. First, a turbofan engine controller is designed based on the Least Squares Support Vector Machine (LSSVM) algorithm, and further, the weight of a training sample is changed by an adaptive boosting algorithm so as to construct a turbofan engine direct data-driven controller combining a plurality of basic learners into strong learners. Compared with the previous solution only adopting LS SVM, the present invention enhances the control precision, improves the generalization ability of the algorithm, and effectively solves the problem of sparsity of samples by the adaptive boosting method. By the adaptive boosting algorithm-based turbofan engine direct data-driven control method designed by the present invention.

This combustion adjustment method applied to the combustion control of a combustor executes a first step for selecting a combustion parameter for a load of a gas turbine and increasing or decreasing a command value of the combustion parameter from an original location. When the command value reaches a target tolerance upper limit value or a target tolerance lower limit value, the first step is terminated. Furthermore, a second step for decreasing or increasing the command value in a direction opposite to that of the first step is executed. When the command value reaches the target tolerance upper limit value or the target tolerance lower limit value, the present invention includes a combustion tolerance confirmation step for confirming a combustion tolerance range of the combustion parameter at which the second step is terminated.

A pump of a dishwasher has an integrated heating element, a pump chamber with an inlet and an outlet, a pump rotor inside the pump chamber and a drive motor, wherein the heating element and a temperature sensor are provided on a wall of the pump chamber. For measuring a calcification of the pump chamber it is filled with water and then the pump rotor rotates for mixing the water in the pump chamber without transporting water out of the pump chamber. The temperature of the water in the pump chamber is measured with the temperature sensor as a starting temperature, and then the heating element is activated to heat the water in the pump chamber while the temperature of the water in the pump chamber is measured. Then the heating element is deactivated and the maximum temperature of the water during the heating duration or directly afterwards is determined. A temperature relation between the maximum temperature and the starting temperature of the water is calculated. These steps are executed in the pump at the very beginning of an operation of the new dishwasher after its installation for determining an initial temperature relation. These steps are automatically executed again at a later stage for determining a later temperature relation to determine the heating efficiency of the pump by comparing the later temperature relation to the initial temperature relation.