There is provided a system and method for detecting excess flow in an engine fluid system, the method comprising sensing a temperature of a fluid flowing in a fluid line of the fluid system, the fluid line located downstream of a fluid flow restrictor configured to receive the fluid from a source upstream thereof and to flow the fluid from the source into the fluid line downstream thereof, comparing the temperature to a temperature threshold, and when the temperature is beyond the temperature threshold, detecting excess flow of the fluid in the fluid line and outputting an excess flow indication accordingly.

A system including a thermal management body attached to an electronics equipment, a cavity within the thermal management body storing a coolant, and a cold plate separating the cavity and the electronics equipment.

One or more cooling systems for ventilating a turbine and rotary shaft of a gas turbine system is provided. The gas turbine system includes a gas turbine engine and a turbine exhaust collector in separate enclosures. A first cooling system includes an educator that sucks exhaust gas through a diffuser and directs it out of the turbine exhaust collector enclosure based on suction pressure created from the high velocity of exhaust gas. A second cooling system include struts that enable the exhaust gas to flow from the diffusers to a ventilation flow stack. A third cooling system includes exhaust gas sucked from an opening to a top duct based on suction pressure created from the rotation of the rotary shaft disposed about a coupling. A guideway associated with the third cooling system also directs the exhaust gas to flow to the top duct.

Gas turbine engine including a nacelle and an engine core within the nacelle. The engine core defines a principal rotational axis along its length. The engine core and nacelle define a bypass passage therebetween. The gas turbine engine further includes a cooling system including a cooling duct, which duct defines an inlet for receiving bypass air from the bypass passage at an upstream location and an outlet for discharging the bypass air at a downstream location. The cooling duct extends, relative to the principal axis, axially and circumferentially around a section of the engine core. The cooling duct comprises: first portion that extends at least axially relative to the principal rotational axis; second portion downstream of the first portion that extends circumferentially around the engine core relative to the principal rotational axis; and third portion downstream of second portion that extends at least axially relative to the principal rotational axis.

A heat insulating material assembly is provided with: a heat insulating material covering an outer surface of a casing of a gas turbine; and a guard part disposed so as to protrude from the outer surface of the casing and face an end surface of the heat insulating material. The heat insulating material is disposed outside an arrangement area of a plurality of openings for air intake from an external space into the casing and on an opposite side to the arrangement area across the guard part.

A heat insulating material assembly is provided with: a heat insulating material covering an outer surface of a casing of a gas turbine; and a guard part disposed so as to protrude from the outer surface of the casing and face an end surface of the heat insulating material. The heat insulating material is disposed outside an arrangement area of a plurality of openings for air intake from an external space into the casing and on an opposite side to the arrangement area across the guard part.

A system is provided, including a heat management system. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a first zone of a turbomachinery, and a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the first zone, to minimize or to eliminate positional changes, structural changes, or a combination thereof, in one or more components of the turbomachinery due to thermal energy.

A system is provided, including a heat management system. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a first zone of a turbomachinery, and a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the first zone, to minimize or to eliminate positional changes, structural changes, or a combination thereof, in one or more components of the turbomachinery due to thermal energy.

A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.

A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.