A planning device according to the present invention includes a remaining life specifying unit that specifies a remaining life of a component for a turbine. On the basis of the specified remaining life, a usage plan generating unit generates a usage plan that indicates the timing at which the component is to be incorporated into the turbine, such that the remaining life of the component becomes equal to or less than an allowable error value at a predetermined timing.

There is provided a gas turbine engine comprising a low pressure shaft and a high pressure shaft; wherein the low pressure shaft connects a fan to a fan drive turbine, and the high pressure shaft connects a high pressure turbine to a compressor section. The low pressure shaft and the high pressure shaft are arranged such that when operating at idle the idle shaft speed ratio is greater than 6.05. The idle shaft speed ratio is the ratio of the speed of the high pressure shaft to the speed of the low pressure shaft at idle conditions.

An embodiment of an engine assembly includes a plurality of offtakes powered by a combustion turbine engine having a high spool and at least one lower spool, and a controller configured to operate the combustion turbine engine through a range between a first low-idle mode, a second high idle mode, and a maximum takeoff power rating mode. The controller operates the engine in the low-idle mode by directing at least a first portion of power from the at least one lower spool to the plurality of offtakes, and wherein the controller operates the engine in the high idle mode by increasing a speed of the high spool relative to a speed of the high spool in the low-idle mode, thereby increasing a compressor outlet (T.sub.3) temperature in the high idle mode relative to a T.sub.3 temperature in the low-idle mode.

A lubrication system for an aircraft engine includes an engine lubricant tank including at least a supply port hydraulically connectable to the aircraft engine, a lubricant makeup port, and an overfill port, an auxiliary lubricant tank, a lubricant makeup conduit hydraulically connecting the auxiliary lubricant tank to the lubricant makeup port. The lubricant makeup conduit includes a pump operable to move lubricant from the auxiliary lubricant tank to the lubricant makeup port, and an overfill conduit hydraulically connecting the overfill port to the auxiliary lubricant tank. A method of operating a lubrication system of an aircraft engine of an aircraft is also disclosed.

A control for a multi-shaft turbine engine system using electrical machines seeks optimal system performance while accommodating hard and soft component limits. To accommodate the component limits, the control may generate a number of possible operating point options reflecting potential trade-offs in performance, lifing, efficiency, or other objectives.

A flutter control system for a turbine includes a processor. The processor is configured to detect blade flutter of a turbine. The blade flutter indicates that blades of the turbine are in a deflected position different from a nominal operating position. The processor is configured to control operational parameters of the turbine that reduce or eliminate the blade flutter to improve the reliability and efficiency of the turbine.

A system and method for determining performance of an engine is provided. The system includes two or more sensors configured in operable arrangement at two or more respective positions at a flowpath. The system includes one or more computing devices configured to perform operations, the operations include acquiring, via the two or more sensors, parameter sets each corresponding to two or more engine conditions different from one another, wherein each parameter set indicates a health condition at a respective location at the engine; comparing, via the computing device, the parameter sets to determine the respective health condition corresponding to the respective location at the engine; and generating, via the computing device, a health condition prediction based on the compared parameter sets.

Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor.

A method for creating a three-dimensional (3D) mark in a protective coating including at least one of a TBC and a bond coating over a metal part, is provided. The method may include positioning a mask over the protective coating, the mask including an opening pattern therein; and performing an abrasive waterjet process on the protective coating using the mask. The abrasive waterjet erodes a first portion of the protective coating exposed through the first opening pattern to create the 3D mark. The mask is removed, leaving the 3D mark in the protective coating. The 3D mark only partially penetrates through the protective coating. A metal part may include a metal body, a protective coating over the metal body, and the 3D mark in the protective coating, is also provided. The 3D mark in the protective coating may include an opening having a width of between 30 and 300 micrometers.

A fuel supply system has a fuel tank, a first fuel pump, and a first oxygen removal unit. The first fuel pump delivers fuel from the fuel tank into the first oxygen removal unit. A valve downstream of the first oxygen removal unit is operable to selectively deliver fuel back to the fuel tank in a bypass position or downstream to a use in a use position. A controller programmed to control the valve and the first fuel pump maintains the valve in the bypass position when an associated gas turbine engine is not operating. The controller moves the valve to the use position when the associated gas turbine engine is operating. A gas turbine engine and a method of operating a fuel supply system are also disclosed.