Gas turbine engine and pulse detonation combustion system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-007/00
F02C-005/00
F23C-015/00
출원번호
US-0337104
(2011-12-24)
등록번호
US-8683780
(2014-04-01)
발명자
/ 주소
Shimo, Masayoshi
Snyder, Philip H.
출원인 / 주소
Shimo, Masayoshi
대리인 / 주소
Krieg DeVault LLP
인용정보
피인용 횟수 :
3인용 특허 :
0
초록▼
One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine including a unique pulse detonation combustion system. In some embodiments, the pulse detonation combustion system includes an inlet section, a vortex generator a
One embodiment of the present invention is a unique pulse detonation combustion system. Another embodiment is a unique gas turbine engine including a unique pulse detonation combustion system. In some embodiments, the pulse detonation combustion system includes an inlet section, a vortex generator and at least one flame accelerator. The inlet section, vortex generator and the at least one flame accelerator may be operative to initiate a deflagration to detonation transition. In some embodiments, the pulse detonation combustion system may include a flame accelerator configured with a directionally-dependent drag coefficient. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for pulse detonation combustion systems, gas turbine engines, and other machines and engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.
대표청구항▼
1. A pulse detonation combustion system, comprising: an inlet section in communication with a fuel supply and an oxidizer supply;a detonation chamber in fluid communication with the inlet section;an igniter in fluid communication with the inlet section and the detonation chamber; anda plurality of f
1. A pulse detonation combustion system, comprising: an inlet section in communication with a fuel supply and an oxidizer supply;a detonation chamber in fluid communication with the inlet section;an igniter in fluid communication with the inlet section and the detonation chamber; anda plurality of first flame accelerators disposed on an upstream side of the igniter and a plurality of second flame accelerators disposed on a downstream side of the igniter,wherein at least one first flame accelerator of the plurality of first flame accelerators and at least one second flame accelerator of the plurality of second flame accelerators are geometrically structured to have directionally-dependent drag coefficients, wherein the at least one first flame accelerator and the at least one second flame accelerator have a greater drag coefficient for precursor and combustion shockwaves propagating in a direction away from the igniter than for waves propagating in a direction toward the igniter. 2. The pulse detonation combustion system of claim 1, wherein drag forces produced by the at least one first flame accelerator during the deflagration to detonation transition are counteracted by drag forces produced by the at least one second flame accelerator during the deflagration to detonation transition. 3. The pulse detonation combustion system of claim 1, wherein the at least one first flame accelerator and the at least one second flame accelerator have a more abrupt transition for waves propagating in a direction away from the igniter than for waves propagating in a direction toward the igniter. 4. The pulse detonation combustion system of claim 1, wherein the at least one first flame accelerator and the at least one second flame accelerator are geometrically configured to generate drag forces of the same magnitude but opposite in direction relative to each other for counter-propagating waves propagating in a direction away from the igniter. 5. A pulse detonation combustion system, comprising: an inlet section having a first flame accelerator;a fuel supply line in fluid communication with the inlet section;an oxidizer supply line in fluid communication with the inlet section;a vortex generator having an inlet face and an outlet face, wherein the vortex generator is in fluid communication with the inlet section;an igniter coupled to the vortex generator and positioned between the inlet face and the outlet face of the vortex generator, wherein the igniter is operative to initiate deflagration combustion of fuel and oxidizer received from the fuel supply line and the oxidizer supply line;a detonation chamber having a second flame accelerator, wherein the detonation chamber is in fluid communication with the inlet section via the vortex generator, wherein the first flame accelerator is disposed on an upstream side of the igniter and the second flame accelerator is disposed on a downstream side of the igniter; anda discharge opening in fluid communication with the detonation chamber and operative to discharge combustion products,wherein the inlet section, the first flame accelerator, the vortex generator and the second flame accelerator are operative to initiate a deflagration to detonation transition,wherein the first flame accelerator and the second flame accelerator are geometrically structured to have a directionally-dependent drag coefficient, each having a greater drag coefficient for precursor and combustion shockwave propagations in a direction away from the igniter than for wave propagations propagating in a direction toward the igniter. 6. The pulse detonation combustion system of claim 5, wherein the drag forces produced by the first flame accelerator during the deflagration to detonation transition are counteracted by the drag forces produced by the second flame accelerator during the deflagration to detonation transition. 7. The pulse detonation combustion system of claim 5, wherein the first flame accelerator and the second flame accelerator each have a more abrupt transition for waves propagating in a direction away from the igniter than for waves propagating in a direction toward the igniter. 8. The pulse detonation combustion system of claim 5, wherein the first flame accelerator and the second flame accelerator are geometrically configured to respectively generate drag forces of the same magnitude but opposite in direction for counter-propagating waves propagating in a direction away from the igniter. 9. The pulse detonation combustion system of claim 5, further comprising a converging-diverging nozzle in fluid communication with the detonation chamber. 10. A gas turbine engine, comprising: a compressor;a turbine; anda pulse detonation combustion system fluidly disposed between the compressor and the turbine, including: a fuel supply line;an oxidizer supply line separate from the fuel supply line;an inlet section in communication with the fuel supply line and the oxidizer supply line;a vortex generator having an inlet face and an outlet face, wherein the vortex generator is in fluid communication with the inlet section;an igniter coupled to the vortex generator and positioned between the inlet face and the outlet face of the vortex generator, wherein the igniter is operative to initiate deflagration combustion of fuel and oxidizer received from the fuel supply line and the oxidizer supply line;a detonation chamber in fluid communication with the inlet section via the vortex generator;a first flame accelerator disposed on an upstream side of the igniter and a second flame accelerator disposed on a downstream side of the igniter; anda discharge opening in fluid communication with the detonation chamber and operative to discharge combustion products,wherein the inlet section, the vortex generator and the flame accelerator are operative to initiate a deflagration to detonation transition; andwherein the first flame accelerator and the second flame accelerator are geometrically structured to have a directionally-dependent drag coefficient, each having a greater drag coefficient for precursor and combustion shockwaves propagating in a direction away from the igniter than for waves propagating in a direction toward the igniter. 11. The gas turbine engine of claim 10, wherein a volume of the inlet section is tuned to achieve a desired detonation cycle time. 12. The gas turbine engine of claim 10, further comprising a converging-diverging nozzle in fluid communication with the detonation chamber. 13. The gas turbine engine of claim 10, wherein the flame accelerator is structured to amplify a precursor shock wave strength. 14. The gas turbine engine of claim 10, wherein the flame accelerator is structured to perform turbulent mixing of the fuel and the oxidizer. 15. The gas turbine engine of claim 10, wherein the pulse detonation combustion system is configured to control fuel and oxidizer supply timing without the use of a mechanical valve. 16. The gas turbine engine of claim 10, wherein the vortex generator includes a recirculation zone for mixing fuel and oxidizer. 17. The gas turbine engine of claim 10, wherein the flame accelerator is positioned in the detonation chamber. 18. The gas turbine engine of claim 10, wherein the flame accelerator is positioned in the inlet section. 19. The gas turbine engine of claim 10, further comprising an other flame accelerator positioned in the detonation chamber. 20. The pulse detonation combustion system of claim 10, wherein each of the first flame accelerator and the second flame accelerator have a more abrupt transition for waves propagating in a direction away from the igniter than for waves propagating in a direction toward the igniter.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허를 인용한 특허 (3)
Gutmark, Ephraim Jeff; Glaser, Aaron Jerome; Rasheed, Adam, Duplex tab obstacles for enhancement of deflagration-to-detonation transition.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.