Premixed liquid propellant propulsion system and method with anti-flashback quenching liquid injector
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-009/50
F02K-009/52
F02K-009/42
출원번호
US-0229823
(2014-03-28)
등록번호
US-9989014
(2018-06-05)
발명자
/ 주소
Straw, Anthony D.
Holthaus, Mark J.
Hoeser, Steven J.
출원인 / 주소
The Boeing Company
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
A liquid injector system for a combustion engine, having a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure, and having a liquid injector assembly. The assembly has a liquid injector having a hollow dome and injector holes configured t
A liquid injector system for a combustion engine, having a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure, and having a liquid injector assembly. The assembly has a liquid injector having a hollow dome and injector holes configured to receive and inject the premixed liquid propellant or the purge gas through the liquid injector and into a combustion chamber. The liquid injector system has a liquid-to-gas zone between an injector outlet side and a flame front. A pressure gradient decrease between the liquid injector and the combustion chamber causes the premixed liquid propellant to expand from liquid to gas phases, which causes a temperature decrease at the liquid-to-gas zone, wherein the pressure gradient decrease and the temperature decrease prevent or mitigate the flame front from propagating upstream of the combustion chamber, which achieves an anti-flashback quenching liquid injector design.
대표청구항▼
1. A liquid injector system for a combustion engine, the liquid injector system comprising: a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure;a liquid injector assembly coupled to the single feed inlet, the liquid injector assembly co
1. A liquid injector system for a combustion engine, the liquid injector system comprising: a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure;a liquid injector assembly coupled to the single feed inlet, the liquid injector assembly comprising: a liquid injector having one or more injector holes configured to receive and to initially inject only the purge gas through the liquid injector and into a combustion chamber coupled to the liquid injector, the purge gas injected under a high pressure in a range of from about 500 psi (pounds per square inch) to about 1700 psi to pressurize an injector inlet side of the liquid injector, and after injection of the purge gas, the one or more injector holes configured to receive and to inject only the premixed liquid propellant through the liquid injector and into the combustion chamber, the premixed liquid propellant injected under a high pressure in a range of from about 500 psi to about 1700 psi to maintain a positive pressure across the liquid injector and to pressurize the injector inlet side, the combustion chamber having a decreased pressure in a range of from about 300 psi to about 1500; and,a hollow dome coupled to the single feed inlet and coupled over the injector inlet side of the liquid injector; and,a liquid-to-gas zone between an injector outlet side of the liquid injector and a flame front in the combustion chamber of the combustion engine, wherein a pressure gradient decrease between the liquid injector and the combustion chamber causes the premixed liquid propellant to expand from a liquid phase into a gas phase, which causes a temperature decrease at the liquid-to-gas zone, wherein the pressure gradient decrease and temperature decrease prevent or mitigate the flame front from propagating upstream of the combustion chamber, which achieves an anti-flashback quenching liquid injector design. 2. The liquid injector system of claim 1 wherein the premixed liquid propellant comprises a mixture of one or more fuels and an oxidizer. 3. The liquid injector system of claim 2 wherein the one or more fuels is selected from the group consisting of acetylene, ethylene, ethane, methane, and a combination of two or more thereof. 4. The liquid injector system of claim 2 wherein the oxidizer is selected from the group consisting of nitrous oxide and liquid oxygen. 5. The liquid injector system of claim 1 wherein the purge gas is an inert gas selected from the group consisting of nitrogen, helium, tridyne, and a combination of two or more thereof. 6. The liquid injector system of claim 1 wherein the one or more injector holes each comprises a channel having sides with a straight configuration perpendicular to both the injector inlet side and the injector outlet side of the liquid injector. 7. The liquid injector system of claim 1 wherein the liquid injector system is a rocket liquid injector system, and the combustion engine is a rocket combustion engine. 8. The liquid injector system of claim 1 wherein the liquid injector is a multiple injector hole liquid injector. 9. A premixed liquid propellant propulsion system, comprising: a combustion engine comprising a liquid injector system coupled to a combustion chamber, the liquid injector system comprising: a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure, wherein the premixed liquid propellant comprises a mixture of one or more fuels and an oxidizer, and further wherein the purge gas comprises an inert gas;a liquid injector assembly coupled to the single feed inlet, the liquid injector assembly comprising: a liquid injector having one or more injector holes configured to receive and to initially inject only the purge gas through the liquid injector and into the combustion chamber coupled to the liquid injector, the purge gas injected under a high pressure in a range of from about 500 psi (pounds per square inch) to about 1700 psi to pressurize an injector inlet side of the liquid injector, and after injection of the purge gas, the one or more injector holes configured to receive and to inject only the premixed liquid propellant through the liquid injector and into the combustion chamber, the premixed liquid propellant injected under a high pressure in a range of from about 500 psi to about 1700 psi to maintain a positive pressure across the liquid injector and to pressurize the injector inlet side, the combustion chamber having a decreased pressure in a range of from about 300 psi to about 1500 psi; and,a hollow dome coupled to the single feed inlet and coupled over the injector inlet side of the liquid injector;a liquid-to-gas zone between an injector outlet side of the liquid injector and a flame front in the combustion chamber, wherein a pressure gradient decrease between the liquid injector and the combustion chamber causes the premixed liquid propellant to expand from a liquid phase into a gas phase, which causes a temperature decrease at the liquid-to-gas zone, wherein the pressure gradient decrease and the temperature decrease prevent or mitigate the flame front from propagating upstream of the combustion chamber, which achieves an anti-flashback quenching liquid injector design;a premixed liquid propellant assembly coupled to the single feed inlet of the liquid injector system, the premixed liquid propellant assembly supplying the premixed liquid propellant under pressure to the liquid injector system; and,a purge gas assembly coupled to the single feed inlet of the liquid injector system, the purge gas assembly supplying the purge gas under pressure to the liquid injector system. 10. The premixed liquid propellant propulsion system of claim 9 wherein the fuel is selected from the group consisting of acetylene, ethylene, ethane, methane, and a combination of two or more thereof. 11. The premixed liquid propellant propulsion system of claim 9 wherein the oxidizer is selected from the group consisting of nitrous oxide and liquid oxygen. 12. The premixed liquid propellant propulsion system of claim 9 wherein the inert gas is selected from the group consisting of nitrogen, helium, tridyne, and a combination of two or more thereof. 13. The premixed liquid propellant propulsion system of claim 9 wherein the one or more injector holes each comprises a channel having sides with one of a straight configuration, a sloped configuration, or a tapered nozzle configuration. 14. The premixed liquid propellant propulsion system of claim 9 wherein the premixed liquid propellant propulsion system is a rocket premixed liquid propellant propulsion system, and the combustion engine is a rocket combustion engine. 15. The premixed liquid propellant propulsion system of claim 9 wherein the premixed liquid propellant assembly comprises a premixed liquid propellant storage tank, a feed valve coupled to the single feed inlet for controlling flow of the premixed liquid propellant into the liquid injector system, and a premixed liquid propellant feed line connected between the premixed liquid propellant storage tank and the feed valve. 16. The premixed liquid propellant propulsion system of claim 15 wherein the purge gas assembly comprises a purge gas storage tank and a purge gas feed line connected between the purge gas storage tank and the feed valve coupled to the single feed inlet. 17. A method of operating a premixed liquid propellant propulsion system, the method comprising the steps of: coupling a premixed liquid propellant assembly to a liquid injector system of the premixed liquid propellant propulsion system, the premixed liquid propellant assembly configured to supply a premixed liquid propellant under pressure to the liquid injector system;coupling a purge gas assembly to the liquid injector system, the purge gas assembly configured to supply a purge gas under pressure to the liquid injector system;injecting initially only the purge gas into a liquid injector of the liquid injector system via a single feed inlet, and injecting the purge gas through one or more injector holes of the liquid injector and into a combustion chamber coupled to the liquid injector, and injecting the purge gas under a high pressure in a range of from about 500 psi (pounds per square inch) to about 1700 psi to pressurize an injector inlet side of the liquid injector;after injecting the purge gas, injecting only the premixed liquid propellant into the liquid injector via the single feed inlet, and injecting the premixed liquid propellant through the one or more injector holes and into the combustion chamber, and injecting the premixed liquid propellant under a high pressure in a range of from about 500 psi to about 1700 psi to maintain a positive pressure across the liquid injector and to pressurize the injector inlet side of the liquid injector;creating a pressure gradient decrease between the liquid injector and the combustion chamber, and expanding the premixed liquid propellant from a liquid phase into a gas phase at a liquid-to-gas zone between an injector outlet side of the liquid injector and a flame front in the combustion chamber, resulting in a temperature decrease at the liquid-to-gas zone, wherein the pressure gradient decrease and the temperature decrease prevent or mitigate the flame front from propagating upstream of the combustion chamber, the combustion chamber having a decreased pressure in a range of from about 300 psi to about 1500 psi;igniting and burning the premixed liquid propellant in the gas phase;ceasing injection of the premixed liquid propellant into the liquid injector; and,repeating the step of injecting only the purge gas into the liquid injector, and removing any premixed liquid propellant in the liquid injector and upstream of the liquid injector. 18. The method of claim 17 wherein the step of coupling the premixed liquid propellant assembly further comprises coupling the premixed liquid propellant assembly comprising a premixed liquid propellant storage tank, a feed valve for controlling flow of the premixed liquid propellant into the liquid injector system, and a premixed liquid propellant feed line connected between the premixed liquid propellant storage tank and the feed valve. 19. The method of claim 18 wherein the step of coupling the purge gas assembly to the liquid injector system further comprises coupling the purge gas assembly comprising a purge gas storage tank and a purge gas feed line connected between the purge gas storage tank and the feed valve. 20. The method of claim 17 wherein the step of injecting only the purge gas further comprises injecting only the purge gas comprising an inert gas selected from the group consisting of nitrogen, helium, tridyne, and a combination of two or more thereof. 21. The method of claim 17 wherein the step of injecting only the premixed liquid propellant further comprises injecting only the premixed liquid propellant comprising a mixture of one or more fuels and an oxidizer, wherein the one or more fuels is selected from the group consisting of acetylene, ethylene, ethane, methane, and a combination of two or more thereof, and wherein the oxidizer is selected from the group consisting of nitrous oxide and liquid oxygen. 22. The method of claim 17 wherein the step of injecting only the premixed liquid propellant further comprises injecting the premixed liquid propellant through the one or more injector holes, each injector hole comprising a channel having sides with one of a straight configuration, a sloped configuration, or a tapered nozzle configuration. 23. The method of claim 17 wherein the method of operating the premixed liquid propellant propulsion system comprises operating a rocket premixed liquid propellant propulsion system.
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이 특허에 인용된 특허 (11)
Fisher, Steven C., Bi-propellant injector with flame-holding zone igniter.
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