Abstract: In an example implementation, an example printer system includes a lift, an indicator, a trigger, and a reset mechanism. In an example implementation, a lift is orientable by an amount of media when adjacent to the lift and a trigger has a first portion engageable with the lift at a first orientation of the lift. In an example implementation, the trigger causes the indicator to move towards a first location relative to an aperture defined by an exterior surface in response to engagement with the lift. In an example, the reset mechanism has a first portion engageable with the lift at a second orientation of the lift and the reset mechanism causes movement of the indicator away from the first location in response to engagement with the lift.

Abstract: A combined refrigeration and power plant. The power plant comprises an internal combustion engine an air cycle machine refrigerator driven by the internal combustion engine and configured to refrigerate atmospheric air to provide working fluid to combined refrigeration and power generation cycle, a refrigerated air storage unit configured to store working fluid produced by the air cycle machine refrigerator; and first and second heat exchangers. The first heat exchanger arrangement is configured to exchange heat between a device to be cooled and the working fluid, and the second heat exchanger arrangement is configured to exchange heat between the working fluid downstream of the first heat exchanger in the combined refrigeration and power generation cycle and waste heat from the internal combustion engine; and a generator turbine configured to receive heated working fluid from the second heat exchanger arrangement, and configured to power an electrical generator.

Abstract: According to an example, a printing apparatus may include a first output bin, a second output bin, a first light source positioned to illuminate a portion of the first output bin, a second light source positioned to illuminate a portion of the second output bin, and a controller. The controller may activate the first light source in response to a media being outputted to the first output bin and may activate the second light source in response to a media being outputted to the second output bin to direct a user to the first output bin and/or the second output bin containing a most recently printed media.

Abstract: In an example implementation, an example printer system includes a lift, an indicator, a trigger, and a reset mechanism. In an example implementation, a lift is orientable by an amount of media when adjacent to the lift and a trigger has a first portion engageable with the lift at a first orientation of the lift. In an example implementation, the trigger causes the indicator to move towards a first location relative to an aperture defined by an exterior surface in response to engagement with the lift. In an example, the reset mechanism has a first portion engageable with the lift at a second orientation of the lift and the reset mechanism causes movement of the indicator away from the first location in response to engagement with the lift.

Abstract: An integrated soldering device comprising a wire feed mechanism, a heater configured to heat the wire, and an air recirculation system. The heated wire is fed from the device functions as the soldering tip as the device is used. The air recirculation system collects fumes and smoke generated by the soldering process.

Abstract: A turbofan gas turbine engine (10) comprises a variable area exhaust nozzle (12) arranged at the downstream end of a casing (17). A control unit (66) analyzes the power produced by the gas turbine engine (10), the flight speed of the gas turbine engine (1) and/or the altitude of the gas turbine engine (10). The control unit (66) configures the variable area nozzle (12) at a first cross-sectional area (70A) when the flight speed of the gas turbine engine (10) is less than a first predetermined value. The control unit (66) configures the variable area nozzle (12) at a second, smaller, cross-sectional area (70B) when the flight speed of the gas turbine engine (10) is greater than the first predetermined value and the power produced by the gas turbine engine (10) is greater than a second predetermined value.

Abstract: A method of analysing measured data from a system having multiple associated system variables, the method including the steps of: a) optimizing an error function relating the measured data to a predetermined number of the system variables to adjust the system variables; b) selecting a subset of the adjusted variables; and c) re-optimizing the error function by adjusting only the variables in the subset. A method of identifying likely contributors to an error caused in measured data from a system which has multiple associated system variables. A method of analysing measured engine service or test data form an engine having a plurality of associated system variables, includes the step of optimizing an error function which relates the measured data to a predetermined number of the system variables, by least-absolutes optimization wherein the error function is a sum of absolute variations.

Abstract: A turbofan gas turbine engine (10) comprises a variable area exhaust nozzle (12) arranged at the downstream end of a casing (17). A control unit (66) analyses the power produced by the gas turbine engine (10), the flight speed of the gas turbine engine (1) and/or the altitude of the gas turbine engine (10). The control unit (66) configures the variable area nozzle (12) at a first cross-sectional area (70A) when the flight speed of the gas turbine engine (10) is less than a first predetermined value. The control unit (66) configures the variable area nozzle (12) at a second, smaller, cross-sectional area (70B) when the flight speed of the gas turbine engine (10) is greater than the first predetermined value and the power produced by the gas turbine engine (10) is greater than a second predetermined value.

Abstract: A method is provided of analysing measured parameter values, in relation to corresponding expected parameter values, from a system which has a plurality of associated system variables. The method includes the step of optimising an error function which relates said measured parameter values to the system variables. The step of optimising the error function includes adjusting the system variables to vary the expected parameter values and thereby vary the amount of error represented by the error function. A portion of the system variables are adjusted independently of each other. A further portion of the system variables are adjusted dependently of each other. In the further portion, the system variables remain in a predetermined constant ratio relative to each other, the predetermined constant ratio being characteristic of a known mechanism changing the performance of the system.

Abstract: A method of analysing measured data, in relation to expected data, from a system which has a plurality of associated system variables, is provided, the method including the steps of: a) optimising an error function which relates said measured data to a predetermined number of the system variables adjusting the system variables; b) selecting a subset of the adjusted variables; and c) re-optimising the error function by adjusting only the variables in said subset. A method of identifying likely contributors to an error cause in measured data from a system which has a plurality of associated system variables, is also provided which uses the above method.

Abstract: To determine free field thrust of a gas turbine engine, the gas turbine engine may be attached to a movable support, and operated at a selected engine operating point. The thrust applied by the engine to the thrust cradle is measured. The gas turbine engine intake momentum drag generated by airflow into the gas turbine engine intake, the thrust cradle drag force generated by airflow past the moveable support of the thrust cradle, the base drag generated as a result of accelerating nozzle ejector airflow, a pre-streamtube force related to turning of stream lines in the intake air path, a pre-stream tube force related to a bell mouth pull-off force are calculated. Forces due to forward anemometer plane and nozzle static pressures, and a nozzle exit buoyancy force are summed according to respective positive and negative values to determine the free field thrust at the selected engine operating point.