Abstract: A gas turbine engine including an engine core with a duct, nacelle, and bypass duct receiving fan-accelerated bypass air flow. The core duct is located radially inside the bypass duct and receives the core air flow. A housing between the core and bypass ducts has an outer wall, which is the bypass duct inner wall, and inner wall which is core duct outer wall. The housing extends axially from the gas turbine engine, and splits fan accelerated air flow axially forward into the bypass and core ducts. At least two heat exchangers for cooling engine based oil are mounted in the housing. A flow passage inside the housing delivers air flow to the heat exchangers, and returns air flow from the heat exchangers. The at least two heat exchangers extend circumferentially, and a flow divider is between the heat exchanger ends and diverts air flow to the heat exchangers.

Abstract: There is provided an air intake system for providing air to a tip clearance control system. The air intake system comprises a ram-air intake having a scoop portion and a body portion. The body portion of the ram-air intake houses a heat exchanger.

Abstract: A gas turbine engine comprising: an inner core nacelle; an outer fan nacelle; a bypass duct between the inner core nacelle and the outer fan nacelle; at least one bifurcation that extends between the inner core nacelle and the outer fan nacelle; and a cooling system, wherein the cooling system comprises at least one pipe for conveying a fluid to be cooled, the at least one pipe forming part of a fluid system of the engine, wherein the at least one pipe passes through the at least one bifurcation, and wherein at least a portion of one or more of the pipes is arranged to bring the fluid to be cooled into a heat exchanging relationship with a fluid, e.g. air, flowing in the bypass duct.

Abstract: A connector system for a gas turbine engine having an engine core and a fan located upstream of the engine core and configured to provide a bypass airflow around the engine core, wherein the connector system comprises: an engine core mount block, configured to be mounted to the surface of the engine core and comprising a plurality of fluid conduits passing through the engine core mount block; and a rigid conduit configured to be supported by connection of a first end of the rigid conduit to the engine core mount block and/or by connection of a second end to a connection point in the gas turbine engine arranged radially outward of the bypass airflow; wherein the rigid conduit comprises a plurality of fluid conduits extending from the first end to the second end of the rigid conduit; and when the first end of the rigid conduit is connected to the engine core mount block, each of the fluid conduits in the engine core mount block is in fluid communication a respective fluid conduit in the rigid conduit.

Abstract: A gas turbine engine comprising: an inner core nacelle; an outer fan nacelle; a bypass duct between the inner core nacelle and the outer fan nacelle; at least one bifurcation that extends between the inner core nacelle and the outer fan nacelle; and a cooling system, wherein the cooling system comprises at least one pipe for conveying a fluid to be cooled, the at least one pipe forming part of a fluid system of the engine, wherein the at least one pipe passes through the at least one bifurcation, and wherein at least a portion of one or more of the pipes is arranged to bring the fluid to be cooled into a heat exchanging relationship with a fluid, e.g. air, flowing in the bypass duct.

Abstract: There is provided an air intake system for providing air to a tip clearance control system. The air intake system comprises a ram-air intake having a scoop portion and a body portion. The body portion of the ram-air intake houses a heat exchanger.