Abstract: An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least one exhaust bracket for movably mounting the exhaust duct to an airframe. An alignment system is configured to be operatively connected to the exhaust duct.

Abstract: An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.

Abstract: An auxiliary power unit mounting system according to an exemplary aspect of the present disclosure includes, among other things, a plurality of linkages to support an auxiliary power unit, and a redundant mount to selectively support said auxiliary power unit.

Abstract: An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least one exhaust bracket for movably mounting the exhaust duct to an airframe. An alignment system is configured to be operatively connected to the exhaust duct.

Abstract: An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis.

Abstract: An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.

Abstract: An auxiliary power unit mounting system according to an exemplary aspect of the present disclosure includes, among other things, a plurality of linkages to support an auxiliary power unit, and a redundant mount to selectively support said auxiliary power unit.

Abstract: An example gas turbine engine hose arrangement includes a hose configured to communicate fluid and a thermal blanket directly adjacent the hose. A section of the hose is radially closer to a centerline of the gas turbine engine than the thermal blanket. An example method of limiting hose exposure to thermal energy includes routing a hose near a combustor housing of a gas turbine engine and covering the hose with thermal blanket to limit thermal energy communicated radially inwardly toward an axial center of the combustor housing.

Abstract: A turbo machine is provided that includes a turbine nozzle having a wall. The wall provides spaced apart first and second surfaces. A combustor includes a liner having an annular lip that engages one of the first and second surfaces. A floating ring seal is supported by the liner in a slip-fit relationship, for example, using a retainer. The floating ring seal engages the other of the first and second surfaces. The floating ring seal is slidably moveable relative to the liner in a floating direction in response to movement of the liner in a radial direction.

Abstract: An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis.

Abstract: A turbo machine is provided that includes a turbine nozzle having a wall. The wall provides spaced apart first and second surfaces. A combustor includes a liner having an annular lip that engages one of the first and second surfaces. A floating ring seal is supported by the liner in a slip-fit relationship, for example, using a retainer. The floating ring seal engages the other of the first and second surfaces. The floating ring seal is slidably moveable relative to the liner in a floating direction in response to movement of the liner in a radial direction.

Abstract: An example gas turbine engine hose arrangement includes a hose configured to communicate fluid and a thermal blanket directly adjacent the hose. A section of the hose is radially closer to a centerline of the gas turbine engine than the thermal blanket. An example method of limiting hose exposure to thermal energy includes routing a hose near a combustor housing of a gas turbine engine and covering the hose with thermal blanket to limit thermal energy communicated radially inwardly toward an axial center of the combustor housing.