One embodiment of the present invention is an engine. Another embodiment is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advant
One embodiment of the present invention is an engine. Another embodiment is a unique combustion system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and combustion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
대표청구항▼
1. A combustion system, comprising: a combustion channel having first and second ends and configured to contain a combustion process;wherein the combustion channel is configured to introduce combustion fluid proximate the first end and expel combustion fluid proximate the second end;an igniter dispo
1. A combustion system, comprising: a combustion channel having first and second ends and configured to contain a combustion process;wherein the combustion channel is configured to introduce combustion fluid proximate the first end and expel combustion fluid proximate the second end;an igniter disposed downstream of the first end;wherein the igniter is configured to initiate the combustion process such that a combustion flame front travels from the igniter towards the first end in an opposite direction of a predominant flow direction of the combustible fluid; anda flame accelerator disposed within the combustion channel, wherein the flame accelerator is configured to accelerate the combustion process; andwherein the flame accelerator is configured to yield a directionally-dependent pressure loss in the flow in the combustion channel, wherein the flame accelerator includes a discrete roughness element having a shape configured to yield the directionally-dependent pressure loss in the flow through the combustion channel; and wherein the discrete roughness element is configured to accelerate the combustion process in the opposite direction; wherein the igniter and the discrete roughness element are configured such that the combustion flame front travels upstream toward the first end in the opposite direction past the discrete roughness element. 2. The combustion system of claim 1, wherein the combustion channel includes at least one wall configured to form a combustion chamber; and wherein the discrete roughness element is a shaped obstacle disposed within the combustion chamber. 3. The combustion system of claim 2, wherein the discrete roughness element extends from the at least one wall into the combustion chamber. 4. The combustion system of claim 1, wherein the combustion channel includes at least one wall configured to form a combustion chamber; wherein the discrete roughness element is a cavity formed in the at least one wall; and wherein the cavity is exposed to the combustion chamber. 5. The combustion system of claim 1, wherein the combustion channel includes at least one wall configured to form a combustion chamber, further comprising an insert disposed in the combustion chamber, wherein the insert includes the discrete roughness element. 6. The combustion system of claim 5, wherein the discrete roughness element is a cavity formed in the insert; and wherein the cavity is exposed to the combustion chamber. 7. The combustion system of claim 5, wherein the discrete roughness element extends from the insert into the combustion chamber. 8. The combustion system of claim 1, configured as a pulse detonation combustor. 9. The combustion system of claim 1, configured as a wave rotor. 10. An engine, comprising: a combustion system having an inlet end and an exit end for a combustible fluid to flow therebetween;an igniter disposed at the exit end and configured to produce a combustion process that propagates a flame front that travels in a direction opposite to a predominant direction of the flow of the combustible fluid;a flame accelerator configured to interact with and accelerate the combustion process, wherein the flame accelerator is configured to yield a greater flow contraction in the opposite direction of flow than in the predominant direction of flow, where the flame accelerator includes a discrete roughness element having a shape configured to yield a directionally-dependent pressure loss in the flow through the combustion channel; and wherein the discrete roughness element is configured to accelerate the combustion process in the opposite direction; wherein the igniter and the discrete roughness element are configured such that the combustion flame front travels upstream toward the inlet end in the opposite direction past the discrete roughness element. 11. The engine of claim 10, further comprising a combustion channel configured to contain the combustion process, wherein the flame accelerator is disposed within the combustion channel. 12. The engine of claim 11, wherein the discrete roughness element has a shape configured to yield the directionally-dependent pressure loss in the flow through the combustion channel. 13. The engine of claim 12, wherein the combustion system has the predominant flow direction and the combustion direction opposite the predominant flow direction; and wherein the shape of the discrete roughness element is configured to yield a higher flow area contraction per unit length in the combustion direction than in the predominant flow direction. 14. The engine of claim 13, wherein the shape of the discrete roughness element is configured to yield a sudden contraction in the combustion direction and to yield a gradual contraction in the predominant flow direction. 15. The engine of claim 12, wherein the combustion system has the predominant flow direction and the combustion direction opposite the predominant flow direction; and wherein the discrete roughness element is configured to yield a greater pressure drop in the flow in the combustion direction than in the predominant flow direction. 16. The engine of claim 10, further comprising a turbine in fluid communication with the combustion system. 17. The engine of claim 10, wherein the flame accelerator is structured to transition the combustion process from deflagration combustion to detonation combustion. 18. An engine, comprising: means for containing a combustion process, wherein the means for containing includes an inlet and an exit;means for flowing a combustible fluid in a predominant flow direction from the inlet toward the outlet;an igniter for generating a combustion flame front that travels in an opposite direction to that of the predominant flow direction of the combustible fluid; anda flame accelerator for accelerating the combustion process, wherein the flame accelerator is disposed in the means for containing, and wherein the flame accelerator is structured to yield a directionally-dependent pressure loss; wherein the flame accelerator includes a discrete roughness element having a shape configured to yield the directionally-dependent pressure loss in the flow through the means for containing and wherein the discrete roughness element is configured to accelerate the combustion process in the opposite direction; wherein the igniter and the discrete roughness element are configured such that the combustion flame front travels upstream toward the inlet in the opposite direction past the discrete roughness element. 19. The engine of claim 18, wherein the flame accelerator is structured to transition the combustion process from deflagration combustion to detonation combustion. 20. The engine of claim 18, wherein the flame accelerator is not structured to transition the combustion process from deflagration combustion to detonation combustion.
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이 특허에 인용된 특허 (4)
Snyder,Philip H.; Emmerson,Calvin W., Constant volume combustor.
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