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 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 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 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 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 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.

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 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).