Liquid propellant gasifier and pressurizer

A method for gasifying and pressurizing liquid oxidant and liquid fuel, comprising the following steps:

• a) driving liquid oxidant and liquid fuel (“propellants”) through the inlet channels of a circular motion disc, which keep the two propellants separate;
• b) driving the higher density liquid propellant through compressions ducts from its proximal end of the axis of rotation to a combustion chamber located at the distal end of the axis of rotation, rotating together with the compression ducts;
• c) driving the lower density liquid propellant through compressions ducts from its proximal end of the axis of rotation to combustion chamber located at the distal end of the axis of rotation, rotating together with the compression ducts;
• d) gasifying the lower density liquid propellant in its combustion chamber, by mixing it with higher density propellant;
• e) gasifying the higher density liquid propellant in its combustion chambers by mixing it with the lower density propellant;
• f) driving the combustion gases rich in the higher density propellant, from the combustion chamber for the higher density propellant, into expansion ducts, which move together with the combustion chamber, from their distal end of the axis of rotation, to their proximal end of the axis of rotation;
• g) driving the combustion gases rich in the lower density propellant, from the combustion chamber for the lower density propellant, into expansion ducts, which move together with the combustion chambers, from their distal end of the axis of rotation, to their proximal end of the axis of rotation;
• h) driving the gaseous propellants from the proximal end of the axis of rotation of the expansion ducts into the outlet ducts;
• i) driving liquid propellants, on entering the disc, through bladed inlet channels which induce their entry into the disc, and increase their pressure;
• j) driving gaseous propellants, on leaving the disc, through bladed outlet channels which slow down the rotation of the gas.

A method for gasifying and pressurizing a single liquid propellant, comprising the following steps:

• a) driving the liquid propellant to be gasified and pressurized and the other propellant through the inlet channels of a circular motion disc, which keep the two propellants separate;
• b) driving the liquid oxidant and fuel through compressions ducts from its proximal end of the axis of rotation to a combustion chamber located at the distal end of the axis of rotation, rotating together with the compression ducts;
• c) gasifying the propellant to be pressurized in its combustion chamber, by mixing it with the other propellant;
• d) driving the gaseous propellant, from the combustion chamber, into expansion ducts, which move together with the combustion chamber, from their distal end of the axis of rotation, to their proximal end of the axis of rotation;
• e) driving the gaseous propellant from the proximal end of the axis of rotation of the expansion ducts into the outlet ducts;
• f) driving liquid propellants, on entering the disc, through bladed inlet channels which induce their entry into the disc, and increase their pressure;
• g) driving gaseous propellant, on leaving the disc, through bladed outlet channels which slow down the rotation of the gas.

A gasifying and pressurizing disc for liquid oxidant and liquid fuel comprising:

• a plurality of inlet ducts to the rotating disc;
• a plurality of outlet ducts of the rotating disc;
• a plurality of devices, rotating together, without relative motion between them, comprising:
• an axis of rotation attached to a structural disc positioned perpendicularly;
• compression ducts wherein flow separately the liquid propellants, connecting the inlet ducts of the rotating disc at their proximal end of the axis of rotation with separate combustion chambers for the different propellants, located at the distal end of the axis of rotation;
• combustion chamber for the higher density propellant;
• two different combustion chambers for the lower density propellant, one called high-pressure combustion chamber, that is further away from the axis of rotation than the combustion chambers for the higher density propellant, and further away from the other combustion chamber called low-pressure combustion chamber;
• connections between the outlet of the high-pressure combustion chamber for the lower density propellant and the inlet of the combustion chamber for the higher density propellant;
• connections between the outlet of the combustion chamber for the higher density propellant and expansion ducts;
• connections between the outlet of the low-pressure combustion chamber for the lower density propellant and further expansion ducts;
• separate expansion ducts connecting combustion chambers, located at the distal end of the axis of rotation and connecting to the rotating disc outlet ducts at their proximal end to the axis of rotation;
• a plurality of ducts connecting the liquid propellant compression ducts to the combustion chambers;
• a plurality of ducts connecting the gaseous area of the combustion chambers with the other combustion chambers;
• a plurality of blades located at the inlet of the liquid propellants to induce entry of the liquids and increase their pressure;
• a plurality of blades located at the outlet duct to slow down the rotation of the gases;
• wherein the disc conducts liquid oxidant and liquid fuel through the inlet ducts to each compression duct into the combustion chambers;
• wherein the higher density propellant is gasified, by partial combustion rich in higher density propellant, by mixing it with lower density gaseous propellant from the high-pressure combustion chamber for the lower density propellant;
• wherein the lower density propellant is gasified, by partial combustion rich in lower density propellant, by mixing it with higher density propellant;
• wherein the higher density propellant gasified in its combustion chamber is routed through the expansion ducts to the outlet ducts;
• wherein the lower density propellant gasified in its low-pressure combustion chamber is routed through the expansion ducts to the outlet ducts.

A gasifying and pressurizing disc for liquid oxidant and liquid fuel comprising:

• a plurality of inlet ducts to the rotating disc;
• a plurality of outlet ducts of the rotating disc;
• a plurality of devices, moving together, without relative motion between them, comprising:
• an axis of rotation attached to a structural disc positioned perpendicularly;
• compression ducts wherein flow separately the liquid propellants, connecting the inlet ducts of the rotating disc at their proximal end of the axis of rotation with separate combustion chambers for the different propellants, located at the distal end of the axis of rotation;
• combustion chambers for the oxidant;
• combustion chambers for the fuel;
• connections between the outlet of the combustion chamber for the oxidant and expansion ducts;
• connections between the outlet of the combustion chamber for the fuel and expansion ducts;
• separate expansion ducts connecting combustion chambers, located at the distal end of the axis of rotation and connecting to the rotating disc outlet ducts at their proximal end to the axis of rotation;
• a plurality of ducts connecting the liquid propellant compression ducts to the combustion chambers;
• a plurality of ducts connecting the gaseous area of the combustion chambers with the other combustion chambers;
• a plurality of blades located at the inlet of the liquid propellants to induce entry of the liquids and increase their pressure;
• a plurality of blades located at the outlet duct to slow down the rotation of the gases;
• wherein the disc conducts liquid oxidant and liquid fuel through the inlet ducts to each compression duct into the combustion chambers;
• wherein oxidant is gasified, by partial combustion rich in oxidant, by mixing it with fuel;
• wherein the lower fuel is gasified, by partial combustion rich in fuel, by mixing it with oxidant;
• wherein the oxidant gasified in its combustion chamber is routed through the expansion ducts to the outlet ducts;
• wherein the fuel gasified in its combustion chamber is routed through the expansion ducts to the outlet ducts.

A gasifying and pressurizing disc of a single liquid propellant comprising:

• a plurality of inlet ducts to the rotating disc;
• a plurality of outlet ducts of the rotating disc;
• a plurality of devices, moving together, without relative motion between them, comprising:
• an axis of rotation attached to a structural disc positioned perpendicularly;
• compression ducts wherein flow separately the liquid propellants, connecting the inlet ducts of the rotating disc at their proximal end of the axis of rotation with a combustion chamber, located at the distal end of the axis of rotation;
• a combustion chamber for the propellant to be gasified and pressurized;
• connections between the outlet of the combustion chamber and expansion ducts;
• expansion ducts connecting the combustion chamber located at the distal end of the axis of rotation and connecting to the rotating disc outlet ducts at their proximal end to the axis of rotation;
• a plurality of ducts connecting the liquid propellant compression ducts to the combustion chamber;
• a plurality of blades located at the inlet of the liquid propellants to induce entry of the liquids and increase their pressure;
• a plurality of blades located at the outlet duct to slow down the rotation of the gases;
• wherein the disc conducts liquid oxidant and liquid fuel through the inlet ducts to each compression duct into the combustion chamber;
• wherein the propellant to be pressurized is gasified, by partial combustion, by mixing it with the other propellant;
• wherein the propellant gasified in the combustion chamber is routed through the expansion ducts to the outlet ducts.