Integrated aircraft cooling system
An integrated aircraft cooling system comprising a turbine engine and a plurality of secondary cooling streams, wherein the turbine engine core exhaust stream drives the plurality of secondary cooling streams. A core exhaust stream outlet has a periphery and a composite secondary outlet positioned around the periphery of the core exhaust stream outlet, and the composite secondary outlet is segregated between the plurality of secondary streams. Each of the secondary flows are in fluid isolation from each other upstream of the composite secondary outlet.
1. An aircraft having a turbine engine with a turbine engine core exhaust stream and a plurality of secondary streams, wherein the turbine engine core exhaust stream drives the plurality of secondary streams, wherein a core exhaust stream outlet has a periphery and a composite secondary outlet positioned around the periphery of the core exhaust stream outlet, wherein a composite secondary outlet is segregated between the plurality of secondary streams, and wherein each of the secondary flows are in fluid isolation from each other upstream of the composite secondary outlet.
2. The aircraft of claim 1 , wherein the plurality of secondary streams are coolant streams.
3. The aircraft of claim 2 , wherein the coolant streams are selected from the group consisting of lubricant, hydraulic fluid, and engine fluid.
4. The aircraft of claim 1 , wherein the exit area of the composite secondary outlet normal to the core exhaust stream velocity is divided among the plurality of secondary streams.
5. The aircraft of claim 1 , wherein the static pressure of the core exhaust stream is approximately the same proximate to each of the plurality of secondary streams at the composite secondary stream outlet.
6. The aircraft of claim 1 , wherein the static pressure of each of the plurality of secondary streams proximate the composite secondary outlet are approximately equal.
7. The aircraft of claim 6 , wherein the exit areas for each of the plurality of secondary streams respectively in the composite secondary outlet are not equal.
8. The aircraft of claim 1 , wherein the total pressure of each of the plurality of secondary streams upstream from the composite secondary outlet are not the same.
9. The aircraft of claim 8 , wherein the exit areas for each of the plurality of secondary streams respectively in the composite secondary outlet are equal.
10. The aircraft of claim 1 , wherein the core exhaust stream outlet and the composite secondary outlet are co-axial.
11. The aircraft of claim 1 , wherein the core exhaust stream outlet and the composite secondary outlet are not co-axial.
12. The aircraft of claim 1 , further comprising a plurality of heat exchangers, each of the plurality of heat exchanges associated with a respective one of the plurality of secondary flows.