Abstract: A motor driven compressor system includes a motor with an internal cooling loop. The internal cooling loop draws cooling air from outside the motor driven compressor system. At least one compressor is driven by the motor. A heat exchanger is in fluid communication with the at least one compressor and the cooling loop and is arranged in a ram air duct. An on board inert gas generating system (OBIGGS) for a gas turbine engine and a method of cooling the system utilizing such a compressor system are also disclosed.

Abstract: A vapor cycle heat exchanger has a plurality of heat exchanger lines and a distributor. The distributor comprises a distributor housing, a swirl vane, an atomizing nozzle, a plurality of nozzles, and a fluid line intersection. The distributor housing defines a main distributor line configured to receive a non-homogenous flow of the two-phase refrigerant fluid. The swirl vane is disposed within the main distributor line and configured to distribute the non-homogeneous flow into a symmetric fluid distribution. The atomizing nozzle is disposed downstream of the swirl vane. The routing lines each lead to one of the plurality of heat exchanger lines. The main distributor line branches into the routing lines at the fluid line intersection, which is situated downstream of the nozzle.

Abstract: 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.

Abstract: An air separation module has an inlet for receiving a source of air. The inlet communicates with an inlet manifold and the inlet manifold communicates with a plurality of canisters. The canisters are provided with hollow fibers constructed such that oxygen can permeate the fiber and nitrogen passes through the fiber. A jacket manifold surrounds the canisters and the jacket manifold receives oxygen that has permeated the fibers. The canisters extend to a downstream end, and to an outlet. The jacket manifold communicates with a jacket outlet manifold and an outlet for separated oxygen. The outlet for the jacket manifold is at a downstream end of the canisters.

Abstract: A refrigeration unit and a method of regulating a temperature of a compartment of an aircraft is described. The refrigeration unit includes an evaporator receptive of an airflow and a refrigerant and operatively arranged to transfer heat from the airflow to the refrigerant in order to cool the airflow as the airflow travels from an inlet at an inlet side of the evaporator to an outlet at an outlet side of the evaporator. The outlet is in fluid communication with a compartment of the aircraft. A heater is positioned at the inlet side of the evaporator and heats the airflow before the airflow passes through the outlet of the evaporator. A compressor receives the refrigerant from the output of the evaporator and pressurizes the refrigerant. A condenser receives the refrigerant from the compressor and condenses the refrigerant to liquid phase.

Abstract: A motor driven compressor system includes a motor with an internal cooling loop. The internal cooling loop draws cooling air from outside the motor driven compressor system. At least one compressor is driven by the motor. A heat exchanger is in fluid communication with the at least one compressor and the cooling loop and is arranged in a ram air duct. An on board inert gas generating system (OBIGGS) for a gas turbine engine and a method of cooling the system utilizing such a compressor system are also disclosed.

Abstract: An air separation module has an inlet for receiving a source of air. The inlet communicates with an inlet manifold and the inlet manifold communicates with a plurality of canisters. The canisters are provided with hollow fibers constructed such that oxygen can permeate the fiber and nitrogen passes through the fiber. A jacket manifold surrounds the canisters and the jacket manifold receives oxygen that has permeated the fibers. The canisters extend to a downstream end, and to an outlet. The jacket manifold communicates with a jacket outlet manifold and an outlet for separated oxygen. The outlet for the jacket manifold is at a downstream end of the canisters.

Abstract: 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.

Abstract: A fitting incorporating a crimp sealing device and a method of forming a seal between a length of corrugated tubing and the fitting are provided. A sealing crimp is formed over at least one corrugation of the tubing, where the sealing crimp can utilize a preformed bend or bulge to form a crimp and seal. Alternatively, the sealing crimp can apply pressure radially against an outer sleeve of the fitting, such that at least one corrugation of the tubing is compressed axially or radially to form a primary seal. The outer sleeve also can include one or more gaskets arranged between the outer sleeve and the tubing for forming a secondary seal. An inner sleeve can be received radially inside the outer sleeve, and one or more gaskets can be arranged between the inner sleeve and the tubing. Further, a jacket crimp can be applied against an end of the sleeve member to contact a jacket that at least partially covers the tubing.

Abstract: A fitting incorporating a bushing for forming a seal between a length of corrugated tubing and the fitting, and methods of actuating the fitting and forming a seal using the fitting and tubing are provided. The tubing can be corrugated stainless steel tubing having a jacket that at least partially covers the tubing. The fitting includes a bushing having a substantially open configuration, the bushing configured to engage at least one corrugation groove. When a nut is advanced, the bushing applies pressure to the tubing to crush at least one initial corrugation to form a metal-to-metal seal that is gas and liquid tight.

Abstract: A fitting incorporating a snap-fit sealing and locking device and methods of actuating the fitting and forming a seal between a length of corrugated tubing and the fitting are provided. The tubing can be corrugated stainless steel tubing having a jacket that at least partially covers the tubing. The sealing and locking device incorporates a bushing that is advanced through the application of axial pressure into a sleeve portion. Fingers on the bushing engage one or more corrugation grooves on the tubing and apply force to the tubing to collapse one or more corrugations to form a metal-to-metal seal. Distal motion of the bushing is inhibited after forming a metal-to-metal seal by contact between the bushing and the sleeve portion.

Abstract: A fitting incorporating a crimp sealing device and a method of forming a seal between a length of corrugated tubing and the fitting are provided. A sealing crimp is formed over at least one corrugation of the tubing, where the sealing crimp can utilize a preformed bend or bulge to form a crimp and seal. Alternatively, the sealing crimp can apply pressure radially against an outer sleeve of the fitting, such that at least one corrugation of the tubing is compressed axially or radially to form a primary seal. The outer sleeve also can include one or more gaskets arranged between the outer sleeve and the tubing for forming a secondary seal. An inner sleeve can be received radially inside the outer sleeve, and one or more gaskets can be arranged between the inner sleeve and the tubing. Further, a jacket crimp can be applied against an end of the sleeve member to contact a jacket that at least partially covers the tubing.