United Technologies Corporation

Hamilton Sundstrand Corporation

Eric Andrew Nager

Anthony C Jones

Ted A Martin

Behzad Hagshenas

Eric A Brust

James C Napier

Brady A Manogue

Jake A Rohrig

David Lau

Nagamany Thayalakhandan

Brett Colin Bonner

Farooq Rehman

Donald L Kerr

Giri Prakash Devalapally

Giri P Devalapally

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.

Alignment system for exhaust installation

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.

APU exhaust system

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.

Redundant mount system

A bearing system has first and second bearings each having an inner race. The inner races are mounted to a shaft. The first bearing inner race has a plurality of first ports. The second bearing inner race has a plurality of second ports. The shaft is insertable into the inner races in a plurality of orientations and has a plurality of outer diameter (OD) channels positioned to cooperate with at least the first bearing inner race to communicate with at least some of the first ports and at least some of the second ports. Regardless of said installed orientation, at least one of the second ports are in communication with at least one said inlet port along a flowpath bypassing all the first ports.

Duplex bearing lubrication

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.

Pressure influencing assembly for an aircraft auxiliary system

A generator includes a main cavity and a shaft located in the main cavity. The shaft is configured to be connected to an auxiliary power unit (APU) and rotated by the APU. The generator is configured to generate power based on the rotation of the shaft. A fluid system is configured to receive a fluid from the APU, flow the fluid through the main cavity and return the fluid to the APU through a fluid scavenge channel. A filter is configured to filter the fluid from the main cavity to the fluid scavenge channel and a sensor is configured to detect a characteristic of the fluid at the filter.

Auxiliary power unit generator

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.

Hose arrangement for a gas turbine engine

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.

Growing community of inventors

El Cajon, CA, United States of America

Eric Andrew Nager