Abstract: A gas turbine engine includes a buffer system that includes a first circuit and a second circuit. The first circuit can communicate a first buffer supply air to a first portion of the gas turbine engine and the second circuit can communicate a second buffer supply air to a second portion of the gas turbine engine.

Abstract: A system for removing oil from a bearing compartment has a port connected to an end wall of the compartment through which the oil exits the compartment, a scavenge scoop connected to the port for collecting the oil, and a separation device connected to the scavenge scoop for creating an oil collection region.

Abstract: A gas turbine engine includes a very high speed low-pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for a higher pressure turbine is at a ratio between about 0.5 and about 1.5. In addition, the lower pressure turbine is mounted with a first bearing mounted in a mid-turbine frame, and a second bearing mounted within a turbine exhaust case.

Abstract: A disclosed lubrication system for a gas turbine engine includes a primary passage defining a flow path for lubricant to a gas turbine engine and a bypass passage defining a flow path for lubricant around the gas turbine engine. The lubrication system further includes a primary lubrication pump including a reduced total flow capacity of lubricant with a reduced bypass lubricant flow relative to the total overall flow capacity.

Abstract: A gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a buffer system. The buffer system can include a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit can include a first bleed air supply a second bleed air supply and at least one of an ejector and a valve. The second circuit can include a third bleed air supply, a fourth bleed air supply and at least one of an ejector and a valve.

Abstract: An example turbomachine cooling arrangement includes a pump configured to pressurize a first turbomachine fluid that is then communicated through a heat exchanger assembly to remove thermal energy from a second turbomachine fluid. A portion of the pump is configured to be housed within a gearbox housing of a turbomachine.

Abstract: An engine includes a duct containing a flow of cool air and a pump system for providing air to an environmental control system. The pump system has an impeller having an inlet for receiving cool air from the duct and an outlet for discharging air to the environmental control system.

Abstract: An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging air into a discharge manifold. The discharge manifold containing at least one heat exchanger which forms part of a thermal management system.

Abstract: A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed.

Abstract: A gas turbine engine has an impeller pump for delivering air to an environmental control system and a speed control pump connected to the impeller pump for driving the impeller pump at a constant speed.

Abstract: An assembly and method for providing buffer air and/or ventilation air within a gas turbine engine, the assembly includes an accessory gearbox and a centrifugal compressor. The accessory gearbox is connected to a driven shaft of the gas turbine engine. The centrifugal compressor is driven by the accessory gearbox during operation of the gas turbine engine to receive and compress a bleed air to produce the buffer air and/or the ventilation air. The buffer air and/or the ventilation air is communicated within the gas turbine engine.

Abstract: A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine. The buffer system can include a first circuit and a second circuit. The first circuit selects between a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to render a first buffer supply air having an intermediate pressure. The second circuit selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer supply air.

Abstract: A gas turbine engine includes a buffer system that includes a first circuit and a second circuit. The first circuit can communicate a first buffer supply air to a first portion of the gas turbine engine and the second circuit can communicate a second buffer supply air to a second portion of the gas turbine engine.

Abstract: A gas turbine engine has a thrust balance chamber defined between a static housing and a rotating component. The thrust balance chamber is sealed by a first non-contact seal at a radially inner location and a second non-contact seal at a radially outer location.

Abstract: In one exemplary embodiment, a gas turbine engine includes a turbine and a high pressure compressor. The high pressure compressor includes a last stage having a last stage compressor blade and a last stage vane. The gas turbine engine includes a first flow path through which bleed air flows to the turbine and a second flow path through which air from the last stage of the high pressure compressor flows. The bleed air in the first flow path exchanges heat with a portion of the air in the second flow path in a heat exchanger to cool the air in the second flow path. The cooled air in the second flow path is returned to the high pressure compressor to cool the high pressure compressor.

Abstract: A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler.

Abstract: A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment.

Abstract: A compression pump for an engine is provided. The pump may include a first impeller operatively coupled to a main shaft of the engine, a first inlet configured to at least partially receive bypass airflow, and a first outlet configured to direct compressed air to a thermal management system.

Abstract: A gas turbine engine includes a spool, a gearbox having gearing driven by the spool, and a lubrication system. The lubrication system includes a first heat exchanger positioned in a first air flow path, a second heat exchanger positioned in a second air flow path, and a lubrication pump fluidically connected to both the first heat exchanger and the second heat exchanger. A first air fan is driven by the gearbox for inducing air flow through the first air flow path. A second air fan is driven by an electric motor for inducing air flow through the second air flow path.

Abstract: A buffer air pump provides pressurized cooling air for cooling components of the gas turbine engine. The buffer air pump is supported on and/or within an accessory gearbox and draws bypass air in through an inlet manifold. An impeller supported within a scroll housing pressurizes the incoming bypass air and directs the pressurized air through passages to a component requiring cooling. The buffer air pump draws in relatively cool air from the bypass flow, pressurizes the air with the impeller and sends the air through conduits and passages within the gas turbine engine to the component that requires cooling such as a bearing assembly.