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A turbine engine cooling arrangement includes a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, and a second airflow source including a second passage adjacent the first passage for conve

A turbine engine cooling arrangement includes a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, and a second airflow source including a second passage adjacent the first passage for conveying a second airflow. A heat exchanger is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow.

대표청구항 ▼

1. A turbine engine cooling arrangement comprising: a core passage for receiving a core flow for combustion;a first airflow source including a first passage adjacent the core passage for conveying a first airflow;a second airflow source including a second passage adjacent the first passage for conve

1. A turbine engine cooling arrangement comprising: a core passage for receiving a core flow for combustion;a first airflow source including a first passage adjacent the core passage for conveying a first airflow;a second airflow source including a second passage adjacent the first passage for conveying a second airflow; anda heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow, wherein the entire first passage is located radially outwards of the core passage, and the entire second passage is located radially outwards of the first passage, relative to the core flow. 2. A gas turbine engine cooling arrangement comprising: a core passage for receiving a core flow for combustion;a first airflow source including a first passage adjacent the core passage for conveying a first airflow;a second airflow source including a second passage adjacent the first passage for conveying a second airflow; anda heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow, wherein the first passage includes a first outlet located at a first exhaust section position and the second passage includes a second outlet located at a second exhaust section position that is axially aft of the first exhaust section position relative to the core flow. 3. The arrangement as recited in claim 2, wherein the first exhaust section position and the second exhaust section position are located at a divergent section of an engine exhaust. 4. The arrangement as recited in claim 3, wherein the first passage includes another outlet located axially forward of the first outlet. 5. The arrangement as recited in claim 4, wherein the outlet that is located axially forward of the first outlet is located at a convergent section of the engine exhaust. 6. A gas turbine engine cooling arrangement comprising: a core passage for receiving a core flow for combustion;a first airflow source including a first passage adjacent the core passage for conveying a first airflow;a second airflow source including a second passage adjacent the first passage for conveying a second airflow; and a heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow, wherein the first airflow source comprises a bypass passage, and the second airflow source comprises a ram air scoop. 7. A gas turbine engine cooling arrangement comprising: a core passage for receiving a core flow for combustion;a first airflow source including a first passage adjacent the core passage for conveying a first airflow;a second airflow source including a second passage adjacent the first passage for conveying a second airflow; anda heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow, wherein the first airflow source comprises a bypass passage, and the second airflow source comprises an auxiliary power unit. 8. A turbine engine comprising: a core passage including a combustion section and a turbine section for receiving a core flow for combustion;an engine inlet section for dividing inlet air into the core flow, a first bypass flow, and a second bypass flow;a first bypass passage that is radially outwards of the core passage for receiving the first bypass flow;a second bypass passage radially outwards of the first bypass passage for receiving the second bypass flow;an exhaust for receiving the core flow, the exhaust having a convergent section and a divergent section located aft of the convergent section; anda heat exchanger that is thermally connected with the first bypass passage and the second bypass passage for transferring heat between the first bypass flow and the second bypass flow,wherein the first bypass passage includes a first outlet and the second bypass passage includes a second outlet, wherein the first outlet is located at the convergent section and the second outlet is located at the divergent section.