| CPC F02C 9/18 (2013.01) | 12 Claims |
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1. A turbine engine for an aircraft comprising:
a compressor including an inlet, an outlet, a low-pressure spool arranged between the inlet and the outlet, and a high-pressure spool arranged between the low-pressure spool and the outlet, the low-pressure spool including a low-pressure tap and the high-pressure spool including a high-pressure tap;
a combustor connected to the compressor, the combustor including an inlet portion connected to the outlet of the combustor and an outlet portion;
a turbine connected to the combustor, the turbine including an inlet section connected to the outlet portion of the combustor and an outlet section; and
an integrated engine bleed system connected to the compressor and a plurality of aircraft sub-systems, the integrated engine bleed system including:
a first inlet fluidically connected to the low-pressure tap;
a second inlet fluidically connected to the high-pressure tap;
a plurality of outlets connected to corresponding ones of the plurality of aircraft sub-systems;
at least two shut-off valves connected to the high-pressure tap; and
at least one heat exchanger (HX) connected to the low-pressure tap and the high-pressure tap;
wherein the at least two shut-off valves include a first shut-off valve having a first shut-off valve inlet fluidically connected to the high-pressure tap and a first shut-off valve outlet fluidically connected to two of the plurality of aircraft sub-systems and a second shut-off valve having a second shut-off valve inlet fluidically connected to the high-pressure tap and a second shut-off valve outlet fluidically connected to another two of the aircraft sub-systems;
wherein the HX includes:
a first HX circuit having a first HX circuit inlet fluidically connected to the first shut-off valve and a first HX circuit outlet fluidically connected to the two of the plurality of aircraft sub-systems; and
a second HX circuit including a second HX circuit inlet fluidically connected to the low-pressure tap and a second HX Circuit outlet fluidically connected to ambient, the second HX circuit passing through the HX in a heat exchange relationship with the second HX circuit;
the turbine further comprising:
a low-pressure feed fluidically connected between the low-pressure tap and the first HX circuit inlet downstream of the first shut-off valve;
a check valve arranged in the low-pressure feed;
a third shut-off valve arranged between the first HX circuit outlet and the two of the plurality of aircraft sub-systems; and
a fourth shut-off valve arranged between the second HX circuit outlet and at least one of the another two of the aircraft sub-systems.
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