Hamilton Sundstrand Corporation

Goodrich Corporation

Rtx Corporation

Raytheon Technologies Corporation

Peter A T Cocks

Joseph Brent Staubach

Lance L Smith

Eric Surawski

Sean C Emerson

Ying She

Zissis A Dardas

Haralambos Cordatos

Jonathan Rheaume

Zhongtao Dai

Thomas P Filburn

William P May

Michael L Perry

Andrzej Ernest Kuczek

Joseph E Turney

James S Elder

Matthew Pess

Marios C Soteriou

Christopher Britton Greene

Kevin P Aceves

James M Donohue

Xiaoyi Li

A combustor for a rotating detonation engine includes a radially outer wall extending along an axis (A); a radially inner wall extending along the axis (A), wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a first passage for feeding at least one of the fuel and the oxidant along a first passage axis (a) to the inlet; a second passage for feeding at least one of the fuel and the oxidant along a second passage axis (a) to the inlet, wherein the second passage axis is arranged at an angle (α) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.

Turbulence generator mixer for rotating detonation engine

A combustor for a detonation engine includes a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned at least partially within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a cooling flow passage defined along at least one of the radially outer wall and the radially inner wall and comprising at least two axially spaced cooling flow passage sections, whereby a different cooling rate can be implemented in the at least two axially spaced cooling flow passage sections.

Cooling for detonation engines

A system and method fare disclosed for inerting a protected space. Process water is delivered to an anode of an electrochemical cell where a portion of the process water is electrolyzed to form protons and oxygen. The protons are transferred across the separator to the cathode, and process water is directed through a process water fluid flow path including a first side of a membrane. Gas is transferred to a second side of the membrane to form a de-gassed process water on the first side of the membrane, and the de-gassed process water is recycled to the anode. Air is delivered to the cathode and oxygen is reduced at the cathode to generate oxygen-depleted air. The oxygen-depleted air is directed from the cathode of the electrochemical cell along an inerting gas flow path to the protected space.

Process water gas management of electrolyzer system with membrane

Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a temperature of the catalytic reactor.

Catalytic fuel tank inerting apparatus for aircraft

Systems and methods for generating inerting gas on vehicles are described. The systems include a proton exchange membrane (PEM) inerting system, a pure water replenishment system configured to provide pure water to the PEM inerting system, wherein the pure water replenishment system is in fluid communication with the PEM inerting system to replenish water lost during operation of the PEM inerting system, and a control system configured to control operation of the pure water replenishment system to automatically replenish pure water to the PEM inerting system.

Water systems for onboard inerting systems of vehicles

A combustor for a rotating detonation engine includes a radially outer wall extending along an axis (A); a radially inner wall extending along the axis (A), wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a first passage for feeding at least one of the fuel and the oxidant along a first passage axis (a) to the inlet; a second passage for feeding at least one of the fuel and the oxidant along a second passage axis (a) to the inlet, wherein the second passage axis is arranged at an angle (&#x3b1;) relative to the first passage axis whereby mixing of flow from the first passage and the second passage is induced.

A system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a coolant loop coupled to the braking assembly, with the coolant loop being configured to circulate liquid coolant from the braking assembly. That is, the coolant loop may be configured to reduce the temperature of the braking assembly, thus reducing the rate/extent of oxidation of the friction disks and potentially enabling the concentration of oxygen around the braking assembly to be reduced.

Systems and methods for reducing oxidation of friction disks

An aircraft fuel system can include a fuel line configured to transport fuel therein, an exposed aircraft structure in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger in fluid communication with the fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.

Aircraft systems and methods utilizing waste heat in fuel

Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a space velocity through the catalytic reactor.

A fluid gear pump comprising: a first gear including a concentrically disposed first hub portion and a plurality of first teeth; a second gear including a concentrically disposed second hub portion and a plurality of second teeth, wherein at a time in operation the plurality of first teeth and second teeth contact at first and second contact point to create a backlash volume; a first bearing abutting and coaxial to first hub portion; a second bearing abutting and coaxial to second hub portion; and a bridgeland connecting the first and second bearing, the bridgeland separates a low pressure side from a high pressure side, the bridgeland is located such that the backlash volume closes to the high pressure side and opens to the low pressure side when a rate of change of a volume measurement of the backlash volume is decreasing or about equal to zero.

Growing community of inventors

South Glastonbury, CT, United States of America

Peter A T Cocks