Abstract: A vane heating system for an engine includes a plurality of static vanes, an electrically resistive material, and an electric power source. The static vanes are disposed within the engine, and each static vane has an inner surface that defines a vane cavity. The electrically resistive material is disposed within the vane cavity of each static vane. The electric power source is electrically coupled to, and is configured to selectively supply an electric current to, the electrically resistive material in each static vane. When the electric current is supplied to the electrically resistive material, a temperature of the static vane increases.

Abstract: Heat resistant systems provide a self-activating insulative solution. A seal system includes a case defining a joining line where two sections of the case join together. The case envelops an internal space and separates the internal space from an external space. A seal is disposed at the joining line and a case extension defines a cavity on an outside of the seal. The case extension has an opening that extends between the cavity and the external space. A lining of a heat responsive material is provided in the case extension. The material expands to an activated state when exposed to heat above a threshold temperature and passes through the opening encapsulating the case extension and insulating the seal from the external space.

Abstract: A vane heating system for an engine includes a plurality of static vanes, an electrically resistive material, and an electric power source. The static vanes are disposed within the engine, and each static vane has an inner surface that defines a vane cavity. The electrically resistive material is disposed within the vane cavity of each static vane. The electric power source is electrically coupled to, and is configured to selectively supply an electric current to, the electrically resistive material in each static vane. When the electric current is supplied to the electrically resistive material, a temperature of the static vane increases.

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing the number, size, and type of particulate at a first position on the gas turbine engine and supplying first data representative thereof, where the first position located at a first side of a gas turbine engine component; sensing the number, size, and type of particulate at a second position on the gas turbine engine and supplying first data representative thereof, where the second position located at a second side of the gas turbine engine component and downstream of the first position; and processing the first data and the second data to determine the mass of the particulate accumulated on the gas turbine engine component.

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing the number, size, and type of particulate at a first position on the gas turbine engine and supplying first data representative thereof, where the first position located at a first side of a gas turbine engine component; sensing the number, size, and type of particulate at a second position on the gas turbine engine and supplying first data representative thereof, where the second position located at a second side of the gas turbine engine component and downstream of the first position; and processing the first data and the second data to determine the mass of the particulate accumulated on the gas turbine engine component.

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing particulate at a first position that is located at a first side of a gas turbine engine component and supplying a first sensor signal representative thereof, and sensing particulate at a second position that is located at a second side of the gas turbine engine component and downstream of the first position, and supplying a second sensor signal representative thereof, where the second position. The first sensor and second sensor signals are processed to determine the type, quantity, and size of particulate at the first and second positions, respectively. Based at least on the quantity and size of the particulate at the first and the second positions, an amount of the particulate accumulated on the gas turbine engine component is determined.

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing particulate at a first position that is located at a first side of a gas turbine engine component and supplying a first sensor signal representative thereof, and sensing particulate at a second position that is located at a second side of the gas turbine engine component and downstream of the first position, and supplying a second sensor signal representative thereof, where the second position. The first sensor and second sensor signals are processed to determine the type, quantity, and size of particulate at the first and second positions, respectively. Based at least on the quantity and size of the particulate at the first and the second positions, an amount of the particulate accumulated on the gas turbine engine component is determined.

Abstract: A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.

Abstract: A system and method of operating an engine anti-ice system includes supplying heat from one or more heat sources to one or more components on or within a gas turbine engine, sensing data representative of one or more parameters related to ice crystal accretion, and based on the data, at least selectively inhibiting at least selected ones of the one or more heat sources from supplying heat to at least selected ones of the one or more components on or within the gas turbine engine.

Abstract: A fireproof system is provided for protecting a structure during a fire event. The system includes a fire resistant panel defining a first attachment opening and disposed adjacent to the structure; a canister including a side wall defining a first end and a second end, and an end wall enclosing the first end and defining a second attachment opening that is aligned with the first attachment opening; a fastener extending through the canister at the second attachment opening and the fire resistant panel at the first attachment opening such that the canister, the fire resistant panel, and the structure are fastened together; and a fire retardant agent disposed within the canister in an inactive condition and configured to transition out of the second end of the canister in an active condition at a predetermined temperature.

Abstract: An icing detection subsystem for an aircraft turbine engine is presented. The icing detection subsystem includes a plurality of air pressure sampling ports formed within structure that surrounds a rotating component of the aircraft turbine engine. The subsystem also includes a pressure sensor arrangement coupled to the plurality of air pressure sampling ports to obtain air pressure measurements for the plurality of air pressure sampling ports. A processing module is coupled to the pressure sensor arrangement to analyze the air pressure measurements over time during operation of the aircraft turbine engine, and to generate an alert when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice in the aircraft turbine engine.

Abstract: A fireproof system is provided for protecting a structure during a fire event.