Abstract: A surface cooler configured to be operably coupled to an aircraft fan casing includes a body having a first surface configured to confront the aircraft fan casing and a second surface opposite the first surface, multiple fluid passages located within the body, and a set of fins located on at least the second surface of the body.

Abstract: A turbine engine for an aircraft can includes a casing. The casing can be a fan casing surrounding a fan assembly for drawing air into the turbine engine. The fan casing can have a peripheral wall. A surface cooler can be provided in the turbine engine confronting the peripheral wall of the fan casing. The surface cooler can have a mounting bracket for mounting the surface cooler to the fan casing.

Abstract: A surface cooler configured to be operably coupled to an aircraft fan casing includes a body having a first surface configured to confront the aircraft fan casing and a second surface opposite the first surface, multiple fluid passages located within the body, and a set of fins located on at least the second surface of the body.

Abstract: A surface cooler configured to be operably coupled to an aircraft fan casing and having a first surface configured to confront a peripheral wall of an aircraft fan casing and a second surface opposite the first surface, a set of fluid passages internal to the body and a set of fins located on at least a portion of the second surface of the body.

Abstract: A fan casing assembly for a turbine engine including a fan casing having a peripheral wall, a surface cooler having a first surface confronting the peripheral wall and a mounting assembly having a lower portion generally retained between the first surface of the annular surface cooler and the peripheral wall and having a floating body extending through the set of fan casing fastener openings and an upper portion located radially exterior of the annular fan casing and operably coupled to the lower portion.

Abstract: A heat exchanger including a manifold body having at least one fluid passage, a cooling passage section having a body including a set of fluid passages extending through at least a portion of the cooling passage section, and a weld joint fluidly sealing the manifold body and the cooling passage such that at least one of the set of fluid passages is fluidly coupled to the at least one fluid passage of the manifold body and methods of forming.

Abstract: A surface cooler assembly includes at least one surface cooler comprising surface cooler hook rails extending circumferentially the length of the surface cooler and including axially extending and radially extending portions. The surface cooler assembly also includes at least one support bracket comprising bracket hook rails extending circumferentially the length of the support bracket and including axially extending and radially extending portions. The support bracket and surface cooler are contoured in a circumferential direction. Each of the surface cooler hook rails contacts a bracket hook rail.

Abstract: A surface cooler having a first cooling passage section configured to be operably coupled to a fan casing of an aircraft engine, the cooling passage section having a heat exchanger body defining a first distal end and a second distal end and having a set of fluid passages internal to the heat exchanger body and a first set of fins located on a first exterior surface of the heat exchanger body and a manifold operably coupled to a first distal end of the cooling passage section and wherein the manifold includes a manifold body having an interior fluidly coupled to at least one of the set of fluid passages and a second set of fins located on the manifold body to define a finned manifold and a method for forming same.

Abstract: A surface cooler configured to be operably coupled to an aircraft fan casing and having a first surface configured to confront a peripheral wall of an aircraft fan casing and a second surface opposite the first surface, a set of fluid passages internal to the body and a set of fins located on at least a portion of the second surface of the body.

Abstract: A heat exchanger including a manifold body having at least one fluid passage, a cooling passage section having a body including a set of fluid passages extending through at least a portion of the cooling passage section, and a weld joint fluidly sealing the manifold body and the cooling passage such that at least one of the set of fluid passages is fluidly coupled to the at least one fluid passage of the manifold body and methods of forming.

Abstract: A fan casing assembly for a turbine engine including a fan casing having a peripheral wall, a surface cooler having a first surface confronting the peripheral wall and a mounting assembly having a lower portion generally retained between the first surface of the annular surface cooler and the peripheral wall and having a floating body extending through the set of fan casing fastener openings and an upper portion located radially exterior of the annular fan casing and operably coupled to the lower portion.

Abstract: A turbine engine with a casing including opposing surfaces and a manifold opening passing through the surfaces. A surface cooler is provided adjacent one of the surfaces. A cooler manifold passes through the manifold opening. A seal is provided between the surface cooler and the casing. At least one bolt is used to secure the surface cooler to the casing with the seal in between.

Abstract: A fan casing assembly for a turbine engine including a casing having an annular fan cooler. The annular fan cooler includes first and second connection assemblies to fix movement of the fan cooler during engine operation, while permitting circumferential thermal growth of the fan cooler without suffering from high cycle fatigue.

Abstract: A fan casing assembly for a turbine engine including a fan casing having a peripheral wall, a surface cooler having a first surface confronting the peripheral wall and forward and aft projections, which are radially spaced from the first surface and located between the peripheral wall and the first surface, and a mounting bracket to mount the surface cooler to the fan casing and a method of mounting a surface cooler to a fan casing of a turbine engine.

Abstract: A surface cooler assembly includes at least one surface cooler comprising surface cooler hook rails extending circumferentially the length of the surface cooler and including axially extending and radially extending portions. The surface cooler assembly also includes at least one support bracket comprising bracket hook rails extending circumferentially the length of the support bracket and including axially extending and radially extending portions. The support bracket and surface cooler are contoured in a circumferential direction. Each of the surface cooler hook rails contacts a bracket hook rail.

Abstract: A turbine engine with a casing including opposing surfaces and a manifold opening passing through the surfaces. A surface cooler is provided adjacent one of the surfaces. A cooler manifold passes through the manifold opening. A seal is provided between the surface cooler and the casing. At least one bolt is used to secure the surface cooler to the casing with the seal in between.

Abstract: A turbine engine for an aircraft can includes a casing. The casing can be a fan casing surrounding a fan assembly for drawing air into the turbine engine. The fan casing can have a peripheral wall. A surface cooler can be provided in the turbine engine confronting the peripheral wall of the fan casing. The surface cooler can have a mounting bracket for mounting the surface cooler to the fan casing.

Abstract: A method of forming fins in a heat exchanger having a metal body by skiving the metal body to form a first fin in a first orientation, and skiving the metal body again to form a second fin in a second orientation while straightening the first fin into a third orientation.

Abstract: A method of forming fins in a heat exchanger includes using a stacked slit saw with multiple saw blades to simultaneously cut multiple fins into a metal body of the heat exchanger, with each fin having a body extending from an upper surface of the metal body and terminating in a tip.

Abstract: A fan casing assembly for a turbine engine including a casing having an annular fan cooler. The annular fan cooler includes first and second connection assemblies to fix movement of the fan cooler during engine operation, while permitting circumferential thermal growth of the fan cooler without suffering from high cycle fatigue.