Abstract: An air compressing system is provided that includes a compressor configured to compressor air. An engine is operatively connected to the compressor. Further, an infinitely variable transmission is operatively connected between the engine and the compressor. A first shaft operatively connects the engine to the infinitely variable transmission and is configured to rotate at a first speed and a second shaft operatively connects the infinitely variable transmission to the compressor and is configured to rotate at a second speed.

Abstract: An aircraft environmental conditioning system is disclosed that includes an air cycle system for conditioning a flow of hot compressed air by reducing its temperature and pressure. The air cycle system includes a heat exchanger having a heat rejection side in fluid communication with the airflow and a heat absorption side in fluid communication with external unconditioned air. The system also includes an airflow path from an external air inlet to the heat absorption side of the heat exchanger. A centrifugal separator is disposed in the airflow path, and includes a tubular body portion having an inlet that receives airflow, a deflector in the tubular body portion that imparts a vortex motion to airflow in the tubular body portion, and an outlet portion that includes a clean air outlet in fluid communication with the heat absorption side of the heat exchanger and a scavenge air outlet for removing particulate matter.

Abstract: A system, which includes a plurality of heat exchangers and a compressing device, prepares 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 includes a turbine that provides supplemental power to the compressing device based on a pressure of the medium in the chamber.

Abstract: A recirculation flow collector for a fan includes an arcuate housing; a first face with a first circular opening to receive flow; a second face with a second circular opening to allow flow in a normal fan operating condition; and an outlet in a bottom of the arcuate housing to allow recirculation flow.

Abstract: According to one aspect, an air cycle machine includes a fan rotor, a diffuser cone axially aligned with the fan rotor, and a strut plate assembly. The strut plate assembly includes a first strut plate and a second strut plate with an ejector formed between the first strut plate and the second strut plate. The first strut plate is axially positioned between the fan rotor and the ejector, and the second strut plate is axially positioned between the fan rotor and the diffuser cone. The first strut plate includes a plurality of outer struts and is absent inner struts between the fan rotor and the ejector. The second strut plate includes a plurality of inner struts and outer struts, where the inner struts are axially positioned between the ejector and the diffuser cone.

Abstract: An engine bleed air system having one or more taps in the compressor section of an aircraft engine, for example a low pressure tap and a high pressure tap. The low pressure tap is fluidly connected to the compressor of a turbo-compressor and the high pressure tap is fluidly connected to the turbine of the turbo-compressor. A bypass line connects the high pressure air to the outlet of the compressor, with a heat exchanger used to remove excess heat from the bypass line. An additional heat exchanger is used to remove any excess heat from the compressed air, dumping the heat to a fan stream or to the expanded air exiting the turbine. The system is controlled to minimize the amount of high pressure air extracted from the engine.

Abstract: An environmental control system having parallel compressors includes a first compressor driven by a first motor, the first compressor being operable for fluidly directing a first flow at a first flow rate through the first compressor. Also included is a second compressor driven by a second motor, the second compressor being operable for fluidly directing a second flow at a second flow rate through the second compressor. Further included is a monitoring component configured to compare the first flow rate to the second flow rate.

Abstract: A fan rotor of an air cycle machine includes a hub with fan blades extending from the hub. Each of the plurality of fan blades includes a main airfoil portion located distally from the hub. The main airfoil portion generally has a uniform thickness along its span. A base portion located between the hub and the main airfoil portion of each of the fan blades has a chord length that is longer than a chord length of the main airfoil portion.

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine. The nose cone provides an aperture that communicates air to an interior of the nose cone.

Abstract: An aircraft system includes a fan, a differential pressure sensor, a temperature sensor, and a system controller. The fan provides airflow for at least one heat exchanger. The differential pressure sensor senses a pressure difference between an inlet of the fan and a diffuser exit of the fan. The temperature sensor senses a temperature at the inlet of the fan. The system controller is configured to receive the sensed pressure difference, the sensed temperature, and a speed of the fan, and determines an operating point of the fan based upon the sensed pressure difference, the speed of the fan, and the sensed temperature. The operating point is indicative of contamination of the at least one heat exchanger.

Abstract: A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.5% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included.

Abstract: A compressing device added to a cabin air conditioning system to increase a pressure of air in the cabin air conditioning system itself and, thus, allow for lower pressure air to be bled from the engine. For instance, the compressing device allows air to be bled from a low, rather than a high, pressure locations of the engine.

Abstract: A diffuser for an air cycle machine defines airflow both to a compressor rotor from the inlet and from the compressor rotor through a plurality of vanes that define radially extending airflow passages. The size and shape of both the inlet and the vanes of the diffuser define and tailor the character of airflow presented to and leaving the compressor rotor to provide a desired change in air flow.

Abstract: An environmental control system includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with a gas turbine engine. A lower pressure tap is associated with a lower pressure location, which is at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into the turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section of the turbocompressor and the turbine section intermix and pass downstream to be delivered to an aircraft use.

Abstract: A cabin air compressor assembly that include a cabin air compressor disposed at a compressor inlet and a cabin air compressor motor operably connected to the cabin air compressor. At least one cooling flow inlet is configured to direct a cooling flow through various pathways in the cabin air compressor assembly, including across the cabin air compressor motor. A blower is configured to boost the cooling flow across the cabin air compressor motor, thereby increasing cooling flow provided to the air compressor motor. A static seal plate is downstream of the blower and guides the boosted cooling flow toward a cooling flow exit. In addition, the static seal plate isolates boosted cooling flow from a moving rotor of the cabin air compressor, and also forms part of a containment structure that contains fragments and breakage that may come from the cabin air compressor rotor.

Abstract: A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.25% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included.

Abstract: A turbine nozzle for an air cycle machine includes a base with a multiple turbine vanes which each extend for a vane height H, a throat width W defined between each of the multiple of turbine vanes, wherein a ratio W/H is 0.101-0.112.

Abstract: A cabin air compressor assembly includes a cabin air compressor disposed at a compressor inlet and a cabin air compressor motor operably connected to the cabin air compressor. At least one cooling flow inlet is located at a first end of the cabin air compressor motor substantially opposite a second end whereat the cabin air compressor is located. The cooling flow inlet is configured to direct a cooling flow across the cabin air compressor motor. A blower is operably connected to the cabin air compressor and is configured to urge a cooling flow from across the cabin air compressor motor toward a cooling flow outlet, thereby increasing the cooling flow across the cabin air compressor motor.

Abstract: A diffuser for an air cycle machine defines airflow both to a compressor rotor from the inlet and from the compressor rotor through a plurality of vanes that define radially extending airflow passages. The size and shape of both the inlet and the vanes of the diffuser define and tailor the character of airflow presented to and leaving the compressor rotor to provide a desired change in air flow.

Abstract: A turbine nozzle for an air cycle machine includes a disk section with a multiple turbine vanes which each extend for a vane height H, a throat width W defined between each of the multiple of turbine vanes, wherein a ratio W/H is 0.745-0.769.