Liquid rocket engine booster engine with combustion gas fuel source
The inventors introduce the Borissov-Markusic Cycle as the new rocket engine cycle to solve the problem of low efficient open gas generator or tap-off gas generator cycles used to supply power to turbopump. A liquid rocket engine directs turbopump exhaust from a turbopump to a booster engine having an intake to accept ambient airflow, such as a variation of a ramjet, scramjet or dual mode ram scramjet engine. The turbopump is powered by combustion gases, such as from a gas generator or a tap-off manifold interfaced with the liquid rocket engine combustion chamber, and applies energy of the combustion gases to pump fuel and/or liquid oxygen to the liquid rocket engine combustion chamber. The combustion gases have a fuel-rich composition that includes unconsumed fuel from incomplete oxidation so that, upon injection into the combustion chamber of the booster engine, oxidation by ambient air of the unconsumed fuel releases energy to generate thrust with the booster engine.
1. A rocket comprising:
a rocket body having plural liquid rocket engines in an interior of the rocket body, the plural liquid rocket engines generating thrust;
plural turbopumps external to the liquid rocket engine and each having an intake and an exhaust, the intake accepting heated air, each turbopump converting energy of the heated air to pump propellant to one associated liquid rocket engine, the exhaust exhausting the heated air; and
plural ramjet engines external to the rocket body and having an ambient air intake, a combustion chamber and a nozzle, an associated one of the plural turbopumps directing the turbopump exhaust interfaced with an associated one of the plural ramjet engine combustion chambers, the exhausted heated air including unconsumed fuel that burns in the combustion chamber with oxygen of the ambient air.
2. The rocket of claim 1 further comprising:
a tap-off manifold interfaced with the liquid rocket engine at a combustion chamber of the liquid rocket engine to accept combustion gases from the liquid rocket engine;
wherein the tap-off manifold provides the combustion gases to the turbopump intake as the heated air.
3. The rocket of claim 2 further comprising fuel ports interfaced with the tap-off manifold and operable to inject fuel into the combustion gases.
4. The rocket of claim 1 further comprising a gas generator interfaced with a fuel source and liquid oxygen source to burn fuel and liquid oxygen to generate the heated air.
5. A method for generating thrust with unconsumed fuel exhausted from a liquid rocket engine auxiliary power system, the method comprising:
passing exhaust gas generated by burning fuel to plural turbopumps, the exhaust gas including unconsumed fuel;
applying the exhaust gas at each turbopump to pump fuel to an associated one of plural liquid rocket engines located in an interior of a rocket body;
burning the fuel in a thruster body combustion chamber of each of the plural liquid rocket engines integrated in the rocket body interior with liquid oxygen;
directing the exhaust gas from each turbopump to each of plural booster engines located external to the liquid rocket engine and coupled to the rocket body exterior;
mixing the exhaust gas with ambient air in each booster engine; and
igniting the unconsumed fuel of the exhaust gas in the booster engine to generate thrust.
6. The method of claim 5 further comprising:
generating the exhaust gas with a gas generator; and
coupling the gas generator to an intake of the turbopump.
7. The method of claim 5 further comprising:
generating the exhaust gas with a combustion chamber of the liquid rocket engine;
tapping-off the exhaust gas from the combustion chamber to a tap-off manifold; and
coupling the tap-off manifold to an intake of the turbopump.
8. The method of claim 7 further comprising:
injecting fuel into the exhaust gas at the tap-off manifold.
9. The method of claim 5 wherein the mixing the exhaust gas with ambient air further comprises:
injecting the exhaust gas at a combustion chamber of the booster engine; and
directing the ambient air into the combustion chamber through an intake based upon movement of the booster engine through the ambient air.
10. The method of claim 9 wherein the booster engine comprises a Ramjet engine.
11. The method of claim 10 further comprising adjusting a configuration of the Ramjet engine based upon ambient air speed to operate as a Scramjet.
12. The method of claim 9 further comprising:
monitoring one or more predetermined conditions associated with ambient air movement relative to the intake; and
initiating burning of the unconsumed fuel only upon detection of the one or more predetermined conditions.
13. A spacecraft comprising:
a rocket body having an interior and a payload;
plural liquid rocket engines coupled within the rocket body interior, each liquid rocket engine having a combustion chamber aligned along a thrust axis, the combustion chamber terminated at a first end by a headend and opened at a second opposing end by a throat;
an oxygen source interfaced with each of the plural liquid rocket engines to provide oxygen to the combustion chamber;
a fuel source interfaced with each of the plural liquid rocket engines to provide fuel to the combustion chamber;
plural turbopumps, each of the plural turbopumps having a turbine that turns a pump, the pump interfaced with the fuel source to pressurize the fuel for injection into the combustion chamber, the turbine having a turbine exhaust that exhausts gas including at least some unconsumed fuel; and
plural booster engines coupled external to the rocket body, each of the plural booster engines having an ambient air intake to accept ambient air, a booster combustion chamber interfaced with the ambient air intake and a booster exhaust nozzle interfaced with the booster combustion chamber to exhaust airflow from the booster combustion chamber and out the booster exhaust nozzle;
wherein each of the plural turbopumps is associated with one of the plural liquid rocket engines and each of the turbine exhausts interfaces with one of the plural booster engines and each of the booster combustion chambers oxidizes the unconsumed fuel with oxygen of the ambient air to generate thrust out of the booster engine exhaust nozzle.
14. The spacecraft of claim 13 further comprising:
a tap-off manifold interfaced with each of the plural liquid rocket engines combustion chamber and with the turbopump turbine associated with each of the plural liquid rocket engines, the tap-off manifold configured to receive combustion gases from the combustion chamber and to direct the combustion gases into the turbopump turbine, the combustion gases powering the turbine to turn the pump, the combustion gases including unconsumed fuel.
15. The spacecraft of claim 14 further comprising:
fuel ports interfacing the fuel source with the tap-off manifold;
wherein the fuel ports direct the fuel into the tap-off manifold to mix with the combustion gases.
16. The spacecraft of claim 14 further comprising:
fuel ports interfacing the fuel source with the turbopump turbine exhaust;
wherein the fuel ports direct the fuel into the turbopump exhaust to mix with the combustion gases.
17. The spacecraft of claim 13 further comprising a gas generator interfaced with the turbine and combusting the fuel and the oxygen to generate heated gas to power the turbine, the heated gas including unconsumed fuel.
18. The spacecraft of claim 13 wherein each of the plural booster engine comprises a dual mode Ram/Scram engine having a variable ambient air intake, the variable ambient air intake configuring to reduce ambient airflow into the intake when the airflow has less than a predetermined speed.
19. The spacecraft of claim 13 wherein each of the plural booster engine comprises a flame holder operable to provide a flame to ignite the unconsumed fuel in the booster combustion chamber, the flame holder providing flame at only greater than a predetermined speed of the ambient airflow.
20. The spacecraft of claim 13 wherein the booster engine comprises a Ramjet engine.