Air cycle machine for an aircraft environmental control system
An ECS system provides an ACM which locates the compressor upon a common shaft between a first turbine and a second turbine. Each RAF is located remote from the ACM such that the turbines are located outboard on each end of the ACM to provide the highest efficiency possible with each turbine using a straight axial outlet diffuser. As the compressor is located between the turbines the bypass circuits from the turbines are less circuitous and more efficient. Integral valve ports formed into the ACM housing portions results in a weight reduced design due to increase bypass efficiencies and simplified installations.
1. An Environmental Control System comprising:
an air cycle machine housing assembly;
a housing assembly having a first turbine housing portion, a second turbine housing portion, and a compressor housing portion;
a shaft mounted for rotation about an axis of rotation;
a hydrodynamic foil bearing which rotationally supports said shaft;
a first turbine mounted to said shaft, said first turbine communicating with a first turbine outlet along said axis of rotation, said first turbine outlet define by said first turbine housing portion;
a second turbine mounted to said shaft, said second turbine communicating with a second turbine outlet along said axis of rotation, said second turbine outlet axially opposite said first turbine, said first turbine outlet define by said first turbine housing portion;
a compressor upstream of said first turbine and said second turbine, said compressor mounted to said shaft between said first turbine and said second turbine, said compressor in communication with a compressor inlet and a compressor outlet located between said first turbine outlet and said second turbine outlet, said compressor inlet and said compressor outlet directed in a radial direction
an annular compressor shim between said first turbine housing portion and said compressor housing portion to provide a desired clearance for said compressor;
an annular first turbine outlet shim between said first turbine housing portion and said first turbine outlet to provide a desired clearance for said first turbine; and
an annular second turbine outlet shim between second turbine housing portion and said second turbine outlet to provide a desired clearance for said second turbine.
2. The System as recited in claim 1 , further comprising a low limit valve port in communication with a first turbine inlet.
3. The System as recited in claim 1 , further comprising an auxiliary ground unit bypass port in communication with a compressor inlet.
4. The System as recited in claim 1 , wherein said shaft includes a radial flange which extends between said first turbine housing portion and said compressor housing portion.
5. The System as recited in claim 4 , further comprising a hydrodynamic foil thrust bearing adjacent said radial flange.
6. The System as recited in claim 1 , wherein said first turbine inlet, said second turbine inlet and said compressor inlet are at least partially wound around said housing assembly.
7. The System as recited in claim 1 , wherein said compressor inlet and said compressor outlet are directed in a generally common radial direction.