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One embodiment of the present disclosure is a gas turbine engine. Another embodiment is a unique combustion system. Another embodiment is a unique engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for employing continuous detonation combustion proce

One embodiment of the present disclosure is a gas turbine engine. Another embodiment is a unique combustion system. Another embodiment is a unique engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for employing continuous detonation combustion processes. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

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1. A combustion system configured for continuous detonation combustion, comprising: an annular combustion chamber having a centerline axis, the annular combustion chamber configured to contain therein a rotating continuous detonation wave; anda first fluid diode positioned flow-wise upstream of the

1. A combustion system configured for continuous detonation combustion, comprising: an annular combustion chamber having a centerline axis, the annular combustion chamber configured to contain therein a rotating continuous detonation wave; anda first fluid diode positioned flow-wise upstream of the combustion chamber, including a first rotating diode structure and a second rotating fluid diode structure; and wherein the first fluid diode is configured to form, with the first diode structure and the second diode structure, during operation of the combustion system: a first rotating region rotating at a speed that is the same as a speed of the rotating continuous detonation wave, wherein the first rotating region has a first flow area through the first fluid diode; and wherein the first rotating region is positioned adjacent to the rotating continuous detonation wave at a higher pressure zone of the rotating continuous detonation wave; anda second rotating region rotating about the combustion chamber at the same speed as the rotating continuous detonation wave, wherein the second rotating region has a second flow area through the first fluid diode of a greater magnitude than a magnitude of the first flow area; and wherein the second rotating region is positioned adjacent to a lower pressure zone circumferentially of the rotating continuous detonation wave downstream of the higher pressure zone,wherein the first rotating diode structure and the second rotating diode structure rotate around the centerline axis. 2. The combustion system of claim 1, wherein the first rotating region is configured to reduce or prevent a backflow from the combustion chamber through the first fluid diode at the higher pressure zone. 3. The combustion system of claim 1, wherein the second rotating region is configured to introduce a first fluid into the combustion chamber in the lower pressure zone. 4. The combustion system of claim 3, wherein the first fluid is an oxidant. 5. The combustion system of claim 3, further comprising a second fluid diode configured to introduce a second fluid into the combustion chamber in the lower pressure zone circumferentially downstream of a leading portion of the lower pressure zone. 6. The combustion system of claim 5, wherein the first fluid diode is configured to introduce air into the lower pressure zone at a first location; and wherein the second fluid diode is configured to introduce a fuel into the lower pressure zone at a second location circumferentially downstream of the first location, and to form an air-only zone in the lower pressure zone. 7. The combustion system of claim 6, wherein the second fluid diode is configured to lag the fuel introduction circumferentially behind the oxidant introduction. 8. The combustion system of claim 7, wherein the second fluid diode is configured to vary the amount of fuel introduction lag. 9. The combustion system of claim 7, wherein the second fluid diode is configured to vary the amount of fuel introduction lag on the fly during operation of the combustion system. 10. The combustion system of claim 5, further comprising the second fluid diode positioned flow-wise upstream of the combustion chamber, including a third rotating diode structure and a fourth rotating fluid diode structure; wherein the second fluid diode is configured to form, with the third diode structure and the fourth diode structure, during operation of the combustion system: a third rotating region rotating about the combustion chamber at the same speed as the rotating continuous detonation wave, wherein the third rotating region is configured to have a third flow area through the second fluid diode; and wherein the third rotating region is positioned adjacent to the rotating continuous detonation wave at the higher pressure zone of the rotating continuous detonation wave; anda fourth rotating region rotating about the combustion chamber at the same speed as the rotating continuous detonation wave, wherein the fourth rotating region is configured to have a fourth flow area through the second fluid diode greater in magnitude than the third flow area; wherein the fourth rotating region is positioned adjacent to the lower pressure zone circumferentially downstream of the higher pressure zone of the rotating continuous detonation wave; and wherein a leading portion of the fourth rotating region circumferentially lags a leading portion of the second rotating region. 11. The combustion system of claim 10, wherein the first rotating diode structure has a plurality of first fluid flow passages; wherein the second rotating fluid diode structure has a plurality of second fluid flow passages; wherein the number of first fluid flow passages is different than that of the second fluid flow passages; wherein the first rotating diode structure and the second rotating diode structure are configured to rotate at different rotational speeds; wherein the first flow area of the first rotating region is formed by at least a partial misalignment of a first subset of the plurality of first fluid flow passages with a first subset of the second plurality of fluid flow passages; and wherein the second flow area of the second rotating region is formed by at least a partial alignment of a second subset of the plurality of first fluid flow passages with a second subset of the plurality of second fluid flow passages; and wherein the third rotating diode structure has a plurality of third fluid flow passages; wherein the fourth rotating fluid diode structure has a plurality of fourth fluid flow passages; wherein the number of third fluid flow passages is different than that of the fourth fluid flow passages; wherein the second rotating diode structure and the third rotating diode structure are configured to rotate at different rotational speeds; wherein the third flow area of the third rotating region is formed by at least a partial misalignment of a first subset of the plurality of third fluid flow passages with a first subset of the plurality of fourth fluid flow passages; and wherein the fourth flow area of the fourth rotating region is formed by at least a partial alignment of a second subset of the plurality of third fluid flow passages with a second subset of the plurality of fourth fluid flow passages. 12. The combustion system of claim 10, wherein the first fluid diode and the second fluid diode are configured to introduce an air dilution layer at a circumferentially aft portion of the rotating continuous detonation wave. 13. The combustion system of claim 10, wherein the third rotating region is configured to reduce or prevent backflow from the combustion chamber through the second fluid diode; and wherein the fourth rotating region is configured to pass the second fluid into the combustion chamber through the second fluid diode. 14. The combustion system of claim 10, wherein the first fluid diode is configured to introduce a first fluid into the combustion chamber in the lower pressure zone; wherein the first fluid is an oxidant; and wherein the second fluid includes a fuel, and the combustion system further comprising a drive train system configured to supply rotation to the first diode structure, the second diode structure, the third diode structure and the fourth diode structure, wherein the drive train system is configured to rotate the first diode structure and the third diode structure at a first rotational speed; wherein the drive train system is configured to rotate the second diode structure and the fourth diode structure at a second rotational speed different than the first rotational speed; wherein the drive train system is configured to vary the angular relationship between the second diode structure and the fourth diode structure to circumferentially lag the introduction of the second fluid behind the introduction of the first fluid and to vary the amount of lag on the fly during operation of the combustion system. 15. The combustion system of claim 14, wherein the drive train system includes an indexing coupling in mechanical communication with the fourth diode structure and configured to vary the angular relationship between the second diode structure and the fourth diode structure to vary the amount of lag on the fly during operation of the combustion system. 16. The combustion system of claim 10, wherein the first diode structure, the second diode structure, the third diode structure and the fourth diode structure rotate at speeds lower than the speed of the rotating continuous detonation wave. 17. A gas turbine engine, comprising: a compressor system;a combustion system having an annular combustion chamber having a centerline axis and the annular combustion chamber being in fluid communication with the compressor system and configured to contain therein a rotating continuous detonation wave; anda turbine system in fluid communication with the combustion system,wherein the combustion system includes a first fluid diode having a first diode structure and a second diode structure disposed adjacent to the first diode structure; wherein the first fluid diode is configured for relative motion between the first diode structure and the second diode structure to form a first rotating region and a second rotating region, each of which rotate at the same rotational speed as the rotating continuous detonation wave, but wherein the first diode structure and the second diode structure rotate at a lower speed than that of the rotating continuous detonation wave; wherein the first rotating region is positioned adjacent to the rotating continuous detonation wave at a higher pressure zone and configured to reduce or prevent backflow from the combustion chamber through the first fluid diode at the higher pressure zone; and wherein the second rotating region is configured to introduce air into the combustion chamber in the lower pressure zone; andwherein the combustion system includes a second fluid diode having a third diode structure and a fourth diode structure disposed adjacent to the third diode structure; wherein the second fluid diode is configured for relative motion between the third diode structure and the fourth diode structure to form a third rotating region and a fourth rotating region, each of which rotate at the same rotational speed as the rotating continuous detonation wave, but wherein the third diode structure and the fourth diode structure rotate at a lower speed than that of the rotating continuous detonation wave; wherein the third rotating region is positioned adjacent to the rotating continuous detonation wave at a higher pressure zone and configured to reduce or prevent backflow from the combustion chamber through the second fluid diode at the higher pressure zone; and wherein the fourth rotating region is configured to introduce at least some fuel into the combustion chamber in the lower pressure zone,wherein the first fluid diode and the second fluid diode rotate around the centerline axis. 18. The gas turbine engine of claim 17, further comprising a drive train system configured to lag the introduction of the at least some fuel behind the introduction of the air and to vary the amount of fuel introduction lag on the fly during operation of the gas turbine engine. 19. The gas turbine engine of claim 17, further comprising a drive train system configured to supply rotation to the first diode structure, the second diode structure, the third diode structure and the fourth diode structure; wherein the drive train system is configured to rotate the first diode structure and the third diode structure at a first rotational speed; wherein the drive train system is configured to rotate the second diode structure and the fourth diode structure at a second rotational speed different than the first rotational speed; and wherein the drive train system includes an indexing coupling in mechanical communication with the fourth diode structure and configured to vary the angular relationship between the third diode structure and the fourth diode structure to vary the amount of fuel introduction lag on the fly during operation of the gas turbine engine.