초록 ▼

A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a second

A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a secondary gaseous fuel is fed into the inlet air port such that the secondary fuel mixes with air, thereby enabling the mixture of the air and the secondary fuel to combust in a catalytic reactor to produce high temperature, oxygen-rich gases that flow into the main combustor chamber. Proper proportional amounts of the two fuels are determined as a function of altitude.

대표청구항 ▼

1. A combustion system for performing stable combustion and flame stabilization at high altitudes, comprising: a first source for providing a primary liquid hydrocarbon fuel;a second source for providing a secondary monopropellant fuel;an inlet air port;a catalytic reactor coupled to the inlet port;

1. A combustion system for performing stable combustion and flame stabilization at high altitudes, comprising: a first source for providing a primary liquid hydrocarbon fuel;a second source for providing a secondary monopropellant fuel;an inlet air port;a catalytic reactor coupled to the inlet port;a main combustor chamber coupled to the catalytic reactor; andan outlet port coupled to the main combustor chamber,the first source being configured to provide the primary fuel directly into the main combustor chamber such that the primary fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor,wherein, when the combustion system operates at an altitude higher than a first predetermined altitude threshold, the combustion system is configured (i) to use the second source to provide the secondary monopropellant fuel into the inlet air port such that the secondary monopropellant fuel mixes with air entering the inlet air port, and (ii) to cause the mixture of the air and the secondary monopropellant fuel to combust in the catalytic reactor to produce a gaseous secondary fuel product that flows into the main combustor chamber, such that the main combustor chamber contains a first proportional amount of the primary fuel vapor and a second proportional amount of the gaseous secondary fuel product. 2. The combustion system of claim 1, wherein the first predetermined threshold altitude is greater than or equal to 60,000 feet above sea level. 3. The combustion system of claim 2, wherein as the altitude at which the combustion system increases from 60,000 feet above sea level to a second predetermined altitude threshold, the first proportional amount decreases and the second proportional amount increases. 4. The combustion system of claim 3, wherein the second predetermined altitude threshold is greater than or equal to 95,000 feet above sea level. 5. The combustion system of claim 3, wherein when the combustion system operates at an altitude higher than the second predetermined altitude threshold, the system is configured to operate by using the secondary monopropellant fuel exclusively at altitudes less than or equal to a third predetermined altitude. 6. The combustion system of claim 5, wherein the third predetermined altitude is greater than or equal to 110,000 feet above sea level. 7. The combustion system of claim 1, the secondary monopropellant fuel comprising hydrazine. 8. A combustion system for performing stable combustion and flame stabilization at high altitudes, comprising: a first source for providing a primary liquid hydrocarbon fuel;a second source for providing a secondary monopropellant fuel;an inlet air port;a catalytic reactor coupled to the inlet port and disposed upstream of the first source and downstream of the second source;a main combustor chamber coupled to the catalytic reactor; andan outlet port coupled to the main combustor chamber,the first source being configured to provide the primary liquid fuel directly into the main combustor chamber such that the primary fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor,wherein, when the combustion system operates at an altitude higher than a first predetermined altitude threshold, the combustion system is configured (i) to use the second source to provide the secondary monopropellant fuel into the inlet air port such that the secondary monopropellant fuel mixes with air entering the inlet air port, and (ii) to cause the mixture of the air and the secondary monopropellant fuel to combust in the catalytic reactor to produce a gaseous combustion fuel product that flows into the main combustor chamber where it atomizes and vaporizes the injected primary liquid fuel, such that the main combustor chamber contains a first proportional amount of primary fuel vapor and a second proportional amount of the gaseous combustion fuel product. 9. The combustion system of claim 8, wherein the first predetermined threshold altitude is greater than or equal to 60,000 feet above sea level. 10. The combustion system of claim 9, wherein as the altitude at which the combustion system increases from 60,000 feet above sea level to a second predetermined altitude threshold, the first proportional amount decreases and the second proportional amount increases. 11. The combustion system of claim 10, wherein the second predetermined altitude threshold is greater than or equal to 95,000 feet above sea level. 12. The combustion system of claim 10, wherein when the combustion system operates at an altitude higher than the second predetermined altitude threshold, the system is configured to operate by using the secondary monopropellant fuel exclusively at altitudes less than or equal to a third predetermined altitude. 13. The combustion system of claim 12, wherein the third predetermined altitude is greater than or equal to 110,000 feet above sea level. 14. The combustion system of claim 8, wherein the gaseous combustion fuel product is produced by decomposition of a monopropellant. 15. The combustion system of claim 14, the monopropellant comprising hydrazine. 16. The combustion system of claim 8, wherein the gaseous combustion fuel product is produced by gasification of a pure fuel. 17. The combustion system of claim 16, the pure fuel being selected from the group consisting of hydrogen, methane, and propane.