Abstract: A system for monitoring propeller health includes a processing unit having a processor which is programmed to apply a plurality of algorithms to inputted aircraft parameter data. The system also includes a plurality of data inputs for inputting aircraft parameter data into the algorithms, wherein the processor is configured to apply the physics based algorithms to the aircraft parameter data to determine at least the fatigue life consumption of one or more critical components of a propeller. In addition, the system includes an output device which is able to output an indication of the determined fatigue life consumption to an observer.

Abstract: A method of controlling air flow in an environmental control system includes receiving a target total flow value and a combined flow measurement at an outer control loop module. A first air flow reference value is determined based on the target total flow value and the combined flow measurement using the outer control loop module. The first air flow reference value is communicated to an inner control loop module and a flow control valve command determined based at least in part on the first air flow reference value using the inner control loop module. The flow control valve command is communicated to a flow control valve operatively associated with the inner control loop module to control flow through the ECS using the flow control valve. Environmental control systems and computer program products are also described.

Abstract: A system for monitoring propeller health includes a processing unit having a processor which is programmed to apply a plurality of algorithms to inputted aircraft parameter data. The system also includes a plurality of data inputs for inputting aircraft parameter data into the algorithms, wherein the processor is configured to apply the physics based algorithms to the aircraft parameter data to determine at least the fatigue life consumption of one or more critical components of a propeller. In addition, the system includes an output device which is able to output an indication of the determined fatigue life consumption to an observer.

Abstract: A system includes a venturi duct, a first delta P sensor, a second delta P sensor, and an ECS controller. The venturi duct is configured to receive a first bleed air flow or a second bleed air flow. The first and second delta P sensors are configured to sense a first and second pressure difference between a first point and a second point of the venturi duct. The first and second delta P sensors are configured to sense pressure difference over different pressure ranges. The ECS controller is configured determine a flow rate of an ECS air flow based upon the first pressure and/or second sensed pressure differences.

Abstract: An environmental control system includes a first air flow conduit and a second air flow conduit. A turbine is in fluid communication with the first air flow conduit and a compressor is in fluid communication with the second air flow conduit. The compressor is operatively associated with the turbine. A flow control valve is arranged along the first air flow conduit to control a second air flow in the second air flow conduit according to a first air flow in the first air flow conduit. Aircraft and methods of controlling flow through environmental control systems are also described.

Abstract: A method of controlling air flow in an environmental control system includes receiving a target total flow value and a combined flow measurement at an outer control loop module. A first air flow reference value is determined based on the target total flow value and the combined flow measurement using the outer control loop module. The first air flow reference value is communicated to an inner control loop module and a flow control valve command determined based at least in part on the first air flow reference value using the inner control loop module. The flow control valve command is communicated to a flow control valve operatively associated with the inner control loop module to control flow through the ECS using the flow control valve. Environmental control systems and computer program products are also described.

Abstract: A system includes a venturi duct, a first delta P sensor, a second delta P sensor, and an ECS controller. The venturi duct is configured to receive a first bleed air flow or a second bleed air flow. The first and second delta P sensors are configured to sense a first and second pressure difference between a first point and a second point of the venturi duct. The first and second delta P sensors are configured to sense pressure difference over different pressure ranges. The ECS controller is configured determine a flow rate of an ECS air flow based upon the first pressure and/or second sensed pressure differences.

Abstract: A fan rotor blade extending radially from a hub is described. The fan rotor blade may include first surface and a second surface, where the first surface and second surfaces are respectively defined by a set of X-coordinates, Y-coordinates and Z-coordinates. The X, Y and Z coordinates can be set out in any of Tables T-1, T-2, E-1, and E-2. The X, Y, and Z-coordinates can also be scaled by a predetermined factor, with the X-coordinates are oriented in a tangential direction, the Z-coordinates are oriented in an axial direction, and the Y-coordinates are oriented in a radial direction.

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: A fan rotor blade extending radially from a hub is described. The fan rotor blade may include first surface and a second surface, where the first surface and second surfaces are respectively defined by a set of X-coordinates, Y-coordinates and Z-coordinates. The X, Y and Z coordinates can be set out in any of Tables T-1, T-2, E-1, and E-2. The X, Y, and Z-coordinates can also be scaled by a predetermined factor, with the X-coordinates are oriented in a tangential direction, the Z-coordinates are oriented in an axial direction, and the Y-coordinates are oriented in a radial direction.

Abstract: A mixer has an internal bore with an inlet to a chamber, and an outlet at an opposed end/A duct is connected to receive a recirculated air flow. The duct communicates air into the chamber through recirculating air ports such that the recirculating air can mix with the air from the inlet. The mixer housing has a cockpit outlet for delivering air to a second outlet, with the cockpit output being located axially upstream from the recirculating air ports. An isolator is mounted at an outer periphery of the mixer housing, and has flat sides on each of two circumferentially spaced sides. A belly band is bolted to an outer periphery of the mixer housing and to flat sides of the isolator.

Abstract: A seal shaft for use in an air cycle machine has two axial edges. An axial distance is measured between contact faces at the axial edges, with a tolerance to the dimension. A greatest variation between the axial distance at a plurality of spaced locations on the edge face is maintained with a ratio of the greatest variation to the tolerance being less than 0.2. A rotor assembly, an air cycle machine and a method are also disclosed.

Abstract: A cabin air compressor outlet duct includes an outlet portion, a first inlet portion fluidly connected to the outlet portion, and a second inlet portion fluidly connected to the outlet portion and joined to the first inlet through a curvilinear surface having a bend radius between about 2.50 inches (6.35 cm) and about 2.60 inches (6.60 cm).

Abstract: An elbow for use in a cabin air supply system for an aircraft has an inlet duct. The inlet duct diverges into two outlet ducts with an interface area between the outlet ducts. Each of the outlet ducts has a nominal wall thickness, with a central portion of the interface having a first thickness at a point of maximum thickness, and the nominal wall thickness being of a second thickness. The central portion of the interface curves to the central portion of the interface area. A ratio of the first thickness to the second thickness is between 3 and 8. A cabin air supply system is also disclosed.

Abstract: A cross-support bracket for a cabin air compressor assembly includes a mating portion having a first group of apertures at a first end and a second group of apertures at a second end. A reference line is defined between a lowermost primary aperture of the first group of apertures and a lowermost primary aperture of the second group of apertures. A stiffener portion is formed along a lower edge of the mating portion. A curved region is formed in the mating portion between a first and second upper edge of the mating portion. The curved region includes a first curved portion, a substantially straight portion, and a second curved portion. A ratio of a radius of the first and second curved portions of the curved region to a length from the substantially straight portion to the reference line is between 9.06 and 10.19.

Abstract: A support bracket for a cabin air compressor (CAC) assembly includes a CAC mounting portion with a plurality of CAC mounting holes distributed in an arc configuration along a CAC mounting hole circle radius defined from an origin. A support portion includes a ramped face that transitions to an upper lug portion and a substantially perpendicular face relative to the CAC mounting portion. An upper lug includes a coupling hole offset from a first CAC mounting hole at a first length in a first direction and a second length in a second direction. The first CAC mounting hole is offset from the origin by a third length in the first direction and a fourth length in the second direction. A ratio of the first length to the third length is between 0.48 and 0.50, and a ratio of the second length to the fourth length is between 2.48 and 2.54.

Abstract: A cabin supply bracket for a cabin supply duct assembly is provided. The cabin supply bracket includes a base plate with a first, second, and third mounting hole distributed in a substantially triangular arrangement. The first mounting hole has a centerline defined therethrough. A coupling socket extends from the base plate. The coupling socket includes a first and second tie rod coupling support having a tie rod coupling hole formed therethrough and a first and second outer edge. The first outer edge is proximate the second mounting hole, and the second outer edge is proximate the third mounting hole. The coupling socket has a socket width defined between a first socket edge proximate the first outer edge and a second socket edge proximate the second outer edge. A ratio of the socket width to a thickness of the base plate is between 6.31 and 7.84.

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: A support bracket for a cabin air compressor (CAC) assembly includes a CAC mounting portion with a plurality of CAC mounting holes distributed in an arc configuration along a CAC mounting hole circle radius. A support portion includes a ramped face that transitions to an upper lug portion and a substantially perpendicular face relative to the CAC mounting portion. An upper lug extends from the upper lug portion. The upper lug includes a coupling hole that is offset from a first CAC mounting hole of the CAC mounting holes at a length in a first direction and a length in a second direction. A ratio of the CAC mounting hole circle radius to the length in the first direction is between 2.14 and 2.20, and a ratio of the CAC mounting hole circle radius to the length in the second direction is between 1.16 and 1.19.

Abstract: A mount bracket for use in a cabin air supply system for an aircraft has three legs extending from a cylindrical central bore and at a first axial end of the bracket. There are two legs at an opposed second axial end. A central leg is on the first axial end, and two of the legs are positioned at each of two lateral sides at first and second ends. The legs extend to feet. Strengthening legs connect feet at each of the lateral sides, and to the central leg foot. A thickness of the strengthening legs connected to the central leg is defined as a first dimension. A distance along the first axial end between a laterally outermost portion of the feet at each of the lateral sides is defined as a second dimension. A ratio of the first dimension to the second dimension is between 0.032 and 0.037.