Hamilton Sundstrand Corporation

Christina W Millot

Louis J Bruno

Donald E Army

Erin G Kline

Thomas M Zywiak

Harold W Hipsky

Paul M D'Orlando

Debabrata Pal

John H Paliulis

James P Hurst

Khem Vanwijak Eowsakul

Paul M D'orlando

Paul D'ORLANDO

Jr Donald E Army

Eric G Kline

An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, and a turbine coupled to the compressor via the shaft. The turbine receives and expands a first medium to provide power to the compressor via the shaft. The compressor receives and compresses a second medium in accordance with the power provided by the turbine via the shaft. The turbine is fluidly coupled to a heat exchanger of an air conditioning system.

Supplemental pack driven by bleed air and cabin air

A system can include a compressor outlet line configured to receive compressor outlet flow from a compressor, a bypass line in fluid communication with the compressor outlet line and a motor outlet line to divert a bypass flow of the compressor outlet flow. The system can include at least one pump in fluid communication between the bypass line and the motor outlet line such that the bypass flow at least partially drives the pump to pull cooling flow through a motor to cool the motor.

Motor cooling systems

An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device separate from the compressing device and arranged in fluid communication with the ram air circuit and the at least one dehumidification system. The environmental control system receives a flow of a first medium and a flow of a second medium. The environmental control system is operable in a plurality of modes and in a first mode, a flow of the first medium is provided to the compressing device and the expansion device in series.

Aircraft enviromental control system with series bleed air turbines

An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, and a compression device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor, a turbine, and a fan coupled by a shaft, wherein the fan is operable to move ram air through the ram air circuit and the turbine includes a first inlet for receiving a first flow of medium and a second inlet for receiving a second flow of medium.

Aircraft environmental control system

A system is provided. The system includes a first environmental control sub-system, operating in a first mode, that receives a first medium at a first flow amount and a first pressure. The system also includes a second environmental control sub-system, operating in a second mode, that receives a second medium at a second flow amount and a second pressure. The first flow amount is greater than the second flow amount, and the second pressure is greater than the first pressure.

Unequal bleed flow

An environmental control system (ECS) pack is provided including a primary heat exchanger and a secondary heat exchanger. An air cycle machine is arranged in fluid communication with at least one of the primary and second heat exchanger. The air cycle machine includes a compressor and a plurality of turbines. Discharged cabin air is supplied to at least one of the plurality of turbines to operate the compressor.

A system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers.

Environmental control system utilizing parallel ram heat exchangers

A replacement system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The replacement system employs a subsystem to treat the medium from the low-pressure location of the engine before it is received by the inerting system.

Replacement system providing replacement air to an inerting system

A heat exchanger is provided. The heat exchanger includes a first member having an inlet at a first end and a first flange at an opposite end. The first member is made from a nickel-chromium material. A second member is provided having a second flange one end coupled to the first flange. The second member further having an outlet on a second end opposite the second flange. The second member is made from titanium.

Aircraft precooler heat exchanger

A system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The compressing device is bypassed based on the preparing in parallel the medium for the chamber, which in turn enables the compressing device to windmill. Therefore, the system employs at least one mechanism to prevent components of the compressing device from windmilling.

Environmental control system utilizing parallel RAM heat exchangers with air cycle machine speed compensation

A system includes an inlet line configured to receive a medium flowing from a low-pressure location of an engine to a chamber, a plurality of heat exchangers configured to receive the medium from the inlet line, and a valve located upstream from the plurality of heat exchangers. The valve is configured to divide in parallel the medium across at least a first heat exchanger and a second heat exchanger of the plurality of heat exchangers. A recirculation air system is configured to supply a recirculation.

Recirculation system for parallel ram heat exchangers

A system that comprises a nozzle arrangement is provided. The nozzle arrangement includes at least one nozzle configured to supply a medium at a nozzle flow rate to a fan of an air cycle machine. The nozzle flow rate provides a pneumatic power assist or a power augmentation to a fan of an air cycle machine. The power augmentation, in accordance with the nozzle flow rate, reduces a need for a flow across a turbine of the air cycle machine.

Power augmentation for an air cycle machine of an environmental control system

A nitrogen gas system for an aircraft is provided and operable in warm-up and normal modes. The system includes an air separation module (ASM), a line to transport nitrogen enriched air (NEA) from the ASM to a fuel distribution system and a diverter valve disposed on the line and configured to divert the NEA away from the fuel distribution system during warm-up operations.

Growing community of inventors

Wilbraham, MA, United States of America

Christina W Millot