Abstract: Methods of forming a heat exchanger from a metal body made from a material having a melting temperature greater than 660° C. with the metal body having opposing first and second surfaces and at least one fluid passageway formed in the metal body so that fluid may be passed through the fluid passageway and heat from the fluid may be dissipated through a plurality of fins.

Abstract: Methods of skiving metal using a skiving blade to form a shaving and methods of forming fins in a heat exchanger by skiving using a skiving blade. Where the metal body used to form the shaving or fin is made from a metal material having a hardness greater than that of aluminum.

Abstract: A method and apparatus for controlling fluid flow is provided. The valve assembly includes a valve body including a longitudinal axis and a radially inner internal flow passage extending axially between an inlet opening and an outlet opening, a disk selectively positionable to modulate a flow of working fluid through the flow passage, and a radially outer external surface. The valve assembly further includes a first actuator positioned radially outboard of the external surface, a second actuator positioned radially outboard of the external surface, and a first linkage including a first actuator end configured to couple to the first actuator, a second actuator end configured to couple to the second actuator, and a rod end configured to couple to the disk, wherein an actuating force applied from each actuator to each respective actuator end is combined through the first linkage to the rod end.

Abstract: Methods of skiving metal using a skiving blade to form a shaving and methods of forming fins in a heat exchanger by skiving using a skiving blade. Where the metal body used to form the shaving or fin is made from a metal material having a hardness greater than that of aluminum.

Abstract: Methods of forming a heat exchanger from a metal body made from a material having a melting temperature greater than 660° C. with the metal body having opposing first and second surfaces and at least one fluid passageway formed in the metal body so that fluid may be passed through the fluid passageway and heat from the fluid may be dissipated through a plurality of fins.

Abstract: A hydropnuematic riveter system is described, having features that allow for a reduction in size and weight over traditional rivet squeezers and rivet pullers. The riveter system also provides for greater versatility by permitting the operator to connect different rivet forming heads to the pressure intensifier portion, via a single flexible conduit with fluid-tight quick disconnect fittings.

Abstract: A hydropnuematic riveter system is described, having features that allow for a reduction in size and weight over traditional rivet squeezers and rivet pullers. The riveter system also provides for greater versatility by permitting the operator to connect different rivet forming heads to the pressure intensifier portion, via a single flexible conduit with fluid-tight quick disconnect fittings.

Abstract: A method for regulating gas turbine engine fluid flow may include the steps of providing a flow tube having an open valve, a first bend and a second bend, flowing fluid through the flow tube, actuating a piston so that the piston moves in the axial direction, and closing the valve due to the axial movement of the piston.

Abstract: A valve assembly may include a body having an axis and a flow tube attached to the body for flowing a fluid therethrough, the flow tube having a first bend and a second bend. The valve assembly may further include a valve attached to the flow tube having an axle that is perpendicular to the axis, and a piston attached to the body and the axle and parallel to the axis.

Abstract: A method and apparatus for controlling fluid flow is provided. The valve assembly includes a valve body including a longitudinal axis and a radially inner internal flow passage extending axially between an inlet opening and an outlet opening, a disk selectively positionable to modulate a flow of working fluid through the flow passage, and a radially outer external surface. The valve assembly further includes a first actuator positioned radially outboard of the external surface, a second actuator positioned radially outboard of the external surface, and a first linkage including a first actuator end configured to couple to the first actuator, a second actuator end configured to couple to the second actuator, and a rod end configured to couple to the disk, wherein an actuating force applied from each actuator to each respective actuator end is combined through the first linkage to the rod end.

Abstract: A valve assembly may include a body having an axis and a flow tube attached to the body for flowing a fluid therethrough, the flow tube having a first bend and a second bend. The valve assembly may further include a valve attached to the flow tube having an axle that is perpendicular to the axis, and a piston attached to the body and the axle and parallel to the axis.

Abstract: A method for regulating gas turbine engine fluid flow may include the steps of providing a flow tube having an open valve, a first bend and a second bend, flowing fluid through the flow tube, actuating a piston so that the piston moves in the axial direction, and closing the valve due to the axial movement of the piston.

Abstract: A method enables a gas turbine engine to be operated. The method includes directing fluid flow from a source into an inlet of a valve, channeling the fluid flow entering an inlet portion of the valve towards an outlet portion of the valve such that a direction of the fluid flow is changed within the inlet portion, and controlling the amount of fluid flow entering the outlet portion of the valve by selectively positioning a valve disk coupled within the inlet portion of the valve by a valve disk axle. The method also comprises channeling the fluid flow from the inlet portion of the valve through the outlet portion of the valve and into a fluid supply pipe, wherein the valve outlet portion has a substantially right cylindrical shape such that a direction of fluid entering the body outlet portion remains substantially constant therethrough.

Abstract: A method enables a gas turbine engine to be operated. The method includes directing fluid flow from a source into an inlet of a valve, channeling the fluid flow entering an inlet portion of the valve towards an outlet portion of the valve such that a direction of the fluid flow is changed within the inlet portion, and controlling the amount of fluid flow entering the outlet portion of the valve by selectively positioning a valve disk coupled within the inlet portion of the valve by a valve disk axle. The method also comprises channeling the fluid flow from the inlet portion of the valve through the outlet portion of the valve and into a fluid supply pipe, wherein the valve outlet portion has a substantially right cylindrical shape such that a direction of fluid entering the body outlet portion remains substantially constant therethrough.

Abstract: A method enables a gas turbine engine to be operated. The method includes directing fluid flow from a source into an inlet of a valve, channeling the fluid flow entering an inlet portion of the valve towards an outlet portion of the valve such that a direction of the fluid flow is changed within the inlet portion, and controlling the amount of fluid flow entering the outlet portion of the valve by selectively positioning a valve disk coupled within the inlet portion of the valve by a valve disk axle. The method also comprises channeling the fluid flow from the inlet portion of the valve through the outlet portion of the valve and into a fluid supply pipe, wherein the valve outlet portion has a substantially right cylindrical shape such that a direction of fluid entering the body outlet portion remains substantially constant therethrough.

Abstract: A method enables a duct to be coupled to a gas turbine engine casing. The method comprises extending a first inner tube support member circumferentially around the duct, such that a radially inner side of the first inner tube support is against the duct, and wherein the first inner tube support member has a substantially curved cross sectional profile extending between the radially inner side of the first inner tube support, and a radially outer side of the first inner tube support. The method also comprises extending an outer tube support member circumferentially around the first inner tube support member such that the outer tube support member is against the first inner tube support member outer surface, and coupling the outer tube support member to the gas turbine engine casing.

Abstract: A method enables a duct to be coupled to a gas turbine engine casing. The method comprises extending a first inner tube support member circumferentially around the duct, such that a radially inner side of the first inner tube support is against the duct, and wherein the first inner tube support member has a substantially curved cross sectional profile extending between the radially inner side of the first inner tube support, and a radially outer side of the first inner tube support. The method also comprises extending an outer tube support member circumferentially around the first inner tube support member such that the outer tube support member is against the first inner tube support member outer surface, and coupling the outer tube support member to the gas turbine engine casing.

Abstract: A coupling used to transfer fluid between two conduits includes a seal arrangement that permits an inner sleeve to move axially and angularly without fluid leaking from the coupling. The coupling also includes a pair of coupling members coupled to the inner sleeve, around each end of the inner sleeve. The inner sleeve includes tapered ends sized to receive a seal including a spherical lip. Each coupling member includes a tapered end that compresses each seal during assembly of the coupling. The seal spherical lips maintain sealable contact between the inner sleeve and the coupling first and second members.

Abstract: A method enables a gas turbine engine to be operated. The method includes directing fluid flow from a source into an inlet of a valve, channeling the fluid flow entering an inlet portion of the valve towards an outlet portion of the valve such that a direction of the fluid flow is changed within the inlet portion, and controlling the amount of fluid flow entering the outlet portion of the valve by selectively positioning a valve disk coupled within the inlet portion of the valve by a valve disk axle. The method also comprises channeling the fluid flow from the inlet portion of the valve through the outlet portion of the valve and into a fluid supply pipe, wherein the valve outlet portion has a substantially right cylindrical shape such that a direction of fluid entering the body outlet portion remains substantially constant therethrough.