Abstract: An assembly is provided for a turbine engine. This assembly includes a primary duct, a bleed duct, a plurality of secondary ducts, a heat exchanger and a flow regulator. The bleed duct extends from a bleed duct inlet to a bleed duct outlet. The bleed duct inlet is fluidly coupled with the primary duct. The secondary ducts are arranged in parallel between the bleed duct outlet and the primary duct. The secondary ducts include a first duct and a second duct. The heat exchanger is configured with the second duct. The flow regulator is configured to direct at least a majority of fluid flowing through the bleed duct outlet to: (A) the first duct during a first mode of operation; and (B) the second duct during a second mode of operation.

Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a cooling air tap at a location upstream of the downstream most location. A main turbine section, each of the main turbine section and the main compressor section are mounted within a housing, and each have rotatable components. A first heat exchanger is connected to the cooling air tap. The first heat exchanger is also connected to receive fuel to be supplied to a combustor in the gas turbine engine, and such that the fuel may cool the cooling air in the first heat exchanger. A boost compressor is connected to receive air downstream of the first heat exchanger and connected to deliver the cooling air to at least one of the rotatable components in at least one of the compressor and turbine sections.

Abstract: An assembly is provided for a turbine engine. This assembly includes a primary duct, a bleed duct, a plurality of secondary ducts, a heat exchanger and a flow regulator. The bleed duct extends from a bleed duct inlet to a bleed duct outlet. The bleed duct inlet is fluidly coupled with the primary duct. The secondary ducts are arranged in parallel between the bleed duct outlet and the primary duct. The secondary ducts include a first duct and a second duct. The heat exchanger is configured with the second duct. The flow regulator is configured to direct at least a majority of fluid flowing through the bleed duct outlet to: (A) the first duct during a first mode of operation; and (B) the second duct during a second mode of operation.

Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a cooling air tap at a location upstream of the downstream most location. A main turbine section, each of the main turbine section and the main compressor section are mounted within a housing, and each have rotatable components. A first heat exchanger is connected to the cooling air tap. The first heat exchanger is also connected to receive fuel to be supplied to a combustor in the gas turbine engine, and such that the fuel may cool the cooling air in the first heat exchanger. A boost compressor is connected to receive air downstream of the first heat exchanger and connected to deliver the cooling air to at least one of the rotatable components in at least one of the compressor and turbine sections.

Abstract: Aspects of the disclosure are directed to a system associated with an engine, comprising: a bearing compartment, a scavenge line coupled to the bearing compartment at a first end of the scavenge line that receives a fluid via the first end of the scavenge line, a fluid pump coupled to the scavenge line at a second end of the scavenge line to receive the fluid, and a flow control valve having a variable flow area and disposed in the scavenge line to control flow of the fluid in the scavenge line and the fluid pump.

Abstract: Aspects of the disclosure are directed to a system associated with an engine, comprising: a bearing compartment, a scavenge line coupled to the bearing compartment at a first end of the scavenge line that receives a fluid via the first end of the scavenge line, a fluid pump coupled to the scavenge line at a second end of the scavenge line to receive the fluid, and a flow control valve having a variable flow area and disposed in the scavenge line to control flow of the fluid in the scavenge line and the fluid pump.

Abstract: A grommet for an aircraft fire seal has multiple grommet layers. Each of the grommet layers includes a thickness and a complex geometrical face normal to the thickness.