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US 9,512,805 B2Granted
Continuous detonation combustion engine and system
AssigneeRolls-Royce North American Technologies Inc.
InventorPhilip H. Snyder
Life of this patent
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Abstract
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.
Claims19
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;
- and
- a 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;
- and
- a 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.
7 more elements
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;
- and
- a 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;
- and
- wherein 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.
11 more elements
Dependencies are inferred from the claim text.