Crossover cooling flow for multi-engine systems
A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.
1. A method of operating a multi-engine system comprising a first turbine engine and a second turbine engine, the method comprising:
operating the multi-engine system in a one-engine-inoperable mode,
wherein operating the multi-engine system in the one-engine-inoperable mode comprises:
operating the first turbine engine while the second turbine engine is inoperable;
routing a portion of a total compressor airflow of a first compressor of the first turbine engine as crossover airflow through a first crossover cooling network that extends from the first compressor of the first turbine engine to a body chamber of a vane in a vane row of the second turbine engine; and
preventing backflow of the crossover airflow in the first crossover cooling network via a check valve.
2. The method of claim 1 , wherein, in response to the multi-engine system operating in the one-engine-inoperable mode, the portion of the total compressor flow via the first crossover cooling network is about 10% of the total compressor flow of the first compressor.
3. The method of claim 2 , wherein the total compressor flow is above 100% of a first compressor inlet flow capacity of the first compressor.
4. The method of claim 3 , wherein the total compressor flow is about 105% of the first compressor inlet flow capacity of the first compressor.
5. The method of claim 1 , wherein the first crossover cooling network is controlled via a first controlled valve that controls flow of the crossover airflow.
6. The method of claim 1 , wherein the first compressor and a first turbine of the first turbine engine are each configured to rotate about a first engine central longitudinal axis of the first turbine engine, wherein the second turbine engine comprises a second compressor and a second turbine, and wherein the second compressor and the second turbine of the second turbine engine are each configured to rotate about a second engine central longitudinal axis of the second turbine engine.
7. The method of claim 1 , wherein the first turbine engine and the second turbine engine have a same power and compressor flow capacity or the first turbine engine and the second turbine engine have a different power and compressor flow capacity.
8. A multi-engine system comprising:
a first turbine engine comprising a first compressor and a first turbine;
a second turbine engine comprising a second compressor and a second turbine;
a crossover cooling network that extends from the first compressor of the first turbine engine to a body chamber of a vane in a vane row of the second turbine engine;
a controller configured to:
identify a one-engine-inoperable mode based at least in part on a failure of the second turbine engine; and
cause a portion of a total compressor airflow of the first compressor to be routed as crossover airflow through the crossover cooling network from the first compressor of the first turbine engine to the body chamber of the vane in the vane row of the second turbine engine; and
a check valve that prevents backflow of the crossover airflow in the crossover cooling network.
9. The multi-engine system of claim 8 , wherein the portion of the total compressor flow routed via the crossover cooling network is 10% of the total compressor flow of the first compressor.
10. The multi-engine system of claim 9 , wherein the total compressor flow is above 100% of a first compressor inlet flow capacity of the first compressor.
11. The multi-engine system of claim 10 , wherein the total compressor flow is about 105% of the first compressor inlet flow capacity of the first compressor.
12. The multi-engine system of claim 8 , wherein the multi-engine system further comprises a control valve that is configured to control flow of the crossover airflow.
13. The multi-engine system of claim 8 , wherein the first compressor and the first turbine of the first turbine engine are each configured to rotate about a first engine central longitudinal axis of the first turbine engine, and wherein the second compressor and the second turbine of the second turbine engine are each configured to rotate about a second engine central longitudinal axis of the second turbine engine.
14. The multi-engine system of claim 8 , wherein the first turbine engine and the second turbine engine have a same power and compressor flow capacity or the first turbine engine and the second turbine engine have a different power and compressor flow capacity.