Liquid Rocket Engine Utilizing Turbine Exhaust Gas

Abstract

The present invention relates to a liquid rocket engine comprising a turbopump for supplying an oxidizer and fuel supplied to a combustion chamber under high pressure, and more specifically, to a technology capable of recycling exhaust gas that drives the turbine of the turbopump.

Description

Technology Field

[0001] The present invention relates to a liquid rocket engine comprising a turbopump for supplying an oxidizer and fuel supplied to a combustion chamber under high pressure, and more specifically, to a technology capable of recycling exhaust gas that drives the turbine of the turbopump. Background Technology

[0002] Liquid propellant rocket engines (hereinafter referred to as 'liquid rocket engines') generate thrust by expelling high-speed, high-pressure gas obtained from burning an oxidizer and fuel in a combustor through a nozzle, and are used as representative propulsion systems for rockets.

[0003] In the liquid rocket engine described above, stored oxidizer and fuel must be pressurized to high pressure and supplied to the combustion chamber for stable combustion, and a turbopump is used for this purpose.

[0004] FIG. 1 shows a schematic diagram of a liquid propellant rocket engine (10) using a conventional turbopump. As shown, the liquid propellant rocket engine is composed of a fuel supply line (L1) and a fuel pump (12) provided to supply fuel to a combustor (11), an oxidizer supply line (L2) and an oxidizer pump (13) provided to supply oxidizer to the combustor (11), and a turbopump including a drive shaft (14), a turbine (15), and a gas generating unit (16) for driving the fuel pump (12) and the oxidizer pump (13).

[0005] In a liquid propellant rocket engine (10) configured as described above, the oxidizer and fuel stored in the tank are pressurized by pumps (12) and (13) and sent to a combustor (11). At this time, in order to rotate the turbine (15), which is the driving source for the pumps (12) and (13), a portion of the oxidizer and fuel is combusted in a separate combustor (16) called a gas generator (or pre-burner), and the high-temperature, high-pressure gas generated therefrom is supplied to the turbine (15) to rotate the turbine (15).

[0006] The power generation cycle of such a liquid rocket engine is configured so that the gas driving the turbine (15) is discharged to the outside. Although this exhaust gas still maintains high pressure and temperature, it is discharged to the outside as is, resulting in energy loss. Prior art literature

[65535] Republic of Korea Published Patent Application No. 10-2022-0083169 (Date of publication: June 20, 2022) The problem to be solved

[0007] The present invention was devised to solve the above problems and aims to provide a liquid rocket engine utilizing turbine exhaust gas, which improves the supply pressure of an oxidizer or fuel supplied to a pump by using the exhaust gas that drives the turbine of a turbopump.

[0008] In addition, we aim to provide a liquid rocket engine utilizing turbine exhaust gas that can generate electricity by driving a generator using the exhaust gas from driving a turbopump turbine. means of solving the problem

[0009] A liquid rocket engine utilizing turbine exhaust gas according to an embodiment of the present invention comprises: a first propellant which is either an oxidizer or a fuel and is catalytically decomposable, and a second propellant which is the other of an oxidizer or a fuel; a combustor for receiving and combusting the first and second propellants to generate thrust; a first supply line for supplying the first propellant to the combustor and a second supply line for supplying the second propellant to the combustor; a first pump provided on the first supply line to pressurize the first propellant and a second pump provided on the second supply line to pressurize the second propellant; a turbine driven by the high-temperature gas and connected to the first and second pumps via a drive shaft; a third supply line having its front end connected to a high-temperature gas supply means and its rear end connected to the turbine to supply high-temperature gas to the turbine; and a first exhaust turbine driven by the exhaust gas discharged after driving the turbine. It includes a first booster pump connected to the exhaust turbine through a first exhaust drive shaft and provided at the front end of the first supply line to increase the supply pressure of the first propellant; and a fourth supply line, the front end of which is connected to the turbine and the rear end of which is connected to the exhaust turbine to supply the exhaust gas to the first exhaust turbine.

[0010] Additionally, the engine further includes a second booster pump connected to the exhaust turbine through the first exhaust drive shaft and provided at the front end of the second supply line to increase the supply pressure of the second propellant.

[0011] Additionally, the engine further comprises: a second exhaust turbine driven by exhaust gas discharged after driving the turbine; a second booster pump connected to the exhaust turbine via a second exhaust drive shaft and provided at the front end of the second supply line to increase the supply pressure of the second propellant; and a fifth supply line, the front end of which is connected to the turbine and the rear end of which is connected to the exhaust turbine to supply the exhaust gas to the second exhaust turbine.

[0012] In addition, the engine further includes a generator connected to the exhaust turbine through the first exhaust drive shaft.

[0013] A liquid rocket engine utilizing turbine exhaust gas according to another embodiment of the present invention comprises: a first propellant which is either an oxidizer or a fuel and is catalytically decomposable, and a second propellant which is the other of an oxidizer or a fuel; a combustor for receiving and combusting the first and second propellants to generate thrust; a first supply line for supplying the first propellant to the combustor and a second supply line for supplying the second propellant to the combustor; a first pump provided on the first supply line to pressurize the first propellant and a second pump provided on the second supply line to pressurize the second propellant; a turbine driven by the high-temperature gas and connected to the first and second pumps via a drive shaft; a third supply line having a front end connected to a high-temperature gas supply means and a rear end connected to the turbine to supply high-temperature gas to the turbine; a first exhaust turbine driven by exhaust gas discharged after driving the turbine; and a generator connected to the exhaust turbine via a first exhaust drive shaft. and includes a fourth supply line, the front end of which is connected to the turbine and the rear end of which is connected to the exhaust turbine to supply the exhaust gas to the first exhaust turbine.

[0014] In addition, the high-temperature gas supply means comprises, in a first embodiment, a gas generator that receives the first and second propellants and generates the high-temperature gas by combustion; a first-1 supply line branched from the first supply line and having its rear end connected to the gas generator to supply the first propellant to the gas generator; and a second-1 supply line branched from the second supply line and having its rear end connected to the gas generator to supply the second propellant to the gas generator.

[0015] Additionally, the engine further includes a heat exchange line through the outer surface of the combustor so that the second supply line is heated by the combustion heat of the combustor.

[0016] Additionally, the high-temperature gas supply means, in a second embodiment, includes a second-2 supply line, the front end of which branches off from the rear end of the heat exchange line and the rear end of which is connected to the third supply line, so as to supply a portion of the high-temperature second propellant passing through the combustor to the turbine.

[0017] In addition, the high-temperature gas supply means, in a third embodiment, includes a sixth supply line, the front end of which is connected to the combustor and the rear end of which is connected to the third supply line, so as to supply a portion of the high-temperature combustion gas combusted in the combustor to the turbine. Effects of the invention

[0018] The liquid rocket engine utilizing turbine exhaust gas according to the above configuration of the present invention has the effect of improving combustion performance by enhancing pump suction performance by increasing the supply pressure of the oxidizer or fuel supplied to the oxidizer pump or fuel pump by utilizing the discarded high-temperature, high-pressure exhaust gas.

[0019] Since electricity can be generated from wasted exhaust gases, a separate power generation facility is not required, and the capacity of the installed battery can be reduced. Brief explanation of the drawing

[0020] Figure 1 is a schematic diagram of a liquid rocket engine using a conventional turbopump. FIG. 2 is a schematic diagram of a liquid rocket engine of a first embodiment of the present invention. FIG. 3 is a schematic diagram of a liquid rocket engine of a second embodiment of the present invention. FIG. 4 is a schematic diagram of a liquid rocket engine of a third embodiment of the present invention. FIG. 5 is a schematic diagram of a liquid rocket engine of the fourth embodiment of the present invention. FIG. 6 is a schematic diagram of a liquid rocket engine of the fifth embodiment of the present invention. FIG. 7 is a schematic diagram of a liquid rocket engine of the sixth embodiment of the present invention. Specific details for implementing the invention

[0021] Hereinafter, an embodiment of the present invention as described above will be explained in detail with reference to the drawings.

[0022] - Example 1 (Oxidizing agent pressurized type)

[0023] FIG. 2 shows a schematic diagram of a liquid rocket engine (100) of the first embodiment of the present invention.

[0024] As described, the liquid rocket engine (100) comprises a combustor (101), a first pump (110) for pumping a first propellant (P1), a second pump (120) for pumping a second propellant (P2), a turbine (130) for driving the first and second pumps (110) (120), and a gas generator (140) for generating a driving gas for driving the turbine (130). Additionally, the engine (100) comprises a first supply line (L110) for supplying the first propellant (P1) to the combustor (101), a second supply line (L120) for supplying the second propellant (P2) to the combustor (101), and a third supply line (L130) for supplying the high-temperature gas generated in the gas generator (140) to the turbine (130). Additionally, it further includes a first-1 supply line (L115) branched from a first supply line (L110) to supply a first propellant (P1) to a gas generator (140) and connected downstream to a gas generator (140), and a second-1 supply line (L125) branched from a second supply line (L120) to supply a second propellant (P2) to a gas generator (140) and connected downstream to a gas generator (140).

[0025] A first pump (110) is provided on a first supply line (L110) to pressurize a first propellant (P1), and a second pump (120) is provided on a second supply line (L120) to pressurize a second propellant (P2).

[0026] The turbine (130) can be connected to the first and second pumps (110, 120) through a drive shaft (135) to drive the first and second pumps (110, 120) by rotation.

[0027] At this time, the first propellant (P1) may be an oxidizer for a liquid rocket engine, and the second propellant (P2) may be a fuel for a liquid rocket engine.

[0028] Meanwhile, the second supply line (L120) further includes a heat exchange line (L121) passing through the outer surface of the combustor (101) so that the second propellant (P2) can be heated by the combustion heat of the combustor (101).

[0029] The combustor (101) is formed in the shape of a housing with a combustion space formed inside, and can be configured as a conventional liquid rocket engine combustor that receives liquid fuel and oxidizer and burns them to generate thrust through the discharge pressure of the combustion gas.

[0030] The first supply line (L110) is configured such that its front end is connected to a first propellant tank (not shown) to receive the first propellant (P1), and its rear end is connected to a combustor (101) to supply the incoming first propellant (P1) to the combustor (101). A first pump (110) is provided on the first supply line (L110) to supply the high-pressure first propellant (P1), pressurized through the first pump (110), to the combustor (101).

[0031] The second supply line (L120) is configured such that its front end is connected to a second propellant tank (not shown) to receive the second propellant (P2), and its rear end is connected to a combustor (101) to supply the second propellant (P2) to the combustor (101). A second pump (120) is provided on the second supply line (L120) to supply the high-pressure second propellant (P2), which is pressurized through the second pump (120), to the combustor (101). Additionally, the rear end of the second supply line (L120) may be configured to pass through the wall of the combustor (101) to cool the combustor (101) and simultaneously supply high-temperature, high-pressure fuel heated by the combustion heat of the combustor (101) to the combustor (101).

[0032] The third supply line (L130) is configured such that its front end is connected to a gas generator (140) to receive high-temperature, high-pressure turbine driving gas generated by the gas generator (140), and its rear end is connected to a turbine (130) to supply turbine driving gas to the turbine (130) to rotate the turbine (130). The first and second pumps (110, 120) are connected to the turbine (130) by a drive shaft (135) and operate by receiving the rotational force of the turbine (130) through the drive shaft (135).

[0033] At this time, the liquid rocket engine (100) of the first embodiment of the present invention has the following configuration to utilize the high-temperature, high-pressure exhaust gas that drives the turbine (130).

[0034] The liquid rocket engine (100) includes an exhaust turbine (150) driven by exhaust gas, and a booster pump (160) connected to the exhaust turbine (150) via an exhaust drive shaft (155) and provided at the front end of a first supply line (L110) to increase the supply pressure of the first propellant (P1) by rotation. Additionally, it includes a fourth supply line (L150) at its front end connected to a turbine (130) to receive high-temperature, high-pressure exhaust gas, and at its rear end connected to the exhaust turbine (150) to supply high-temperature, high-pressure exhaust gas to the exhaust turbine (150).

[0035] Therefore, the liquid rocket engine (100) of the present invention has the effect of improving combustion performance by increasing the supply pressure of the oxidizer supplied to the oxidizer pump using the discarded high-temperature, high-pressure exhaust gas, thereby improving the suction performance of the oxidizer pump.

[0036] - Example 2 (Fuel pressurized type) (Gas generator type)

[0037] FIG. 3 shows a schematic diagram of a liquid rocket engine (200) of a second embodiment of the present invention.

[0038] As described, the liquid rocket engine (200) comprises a combustor (201), a first pump (210) for pumping a first propellant (P1), a second pump (220) for pumping a second propellant (P2), a turbine (230) connected to the first and second pumps (210) (220) by a drive shaft (235), and a gas generator (240) for generating a driving gas for driving the turbine (230). Additionally, it comprises a first supply line (L210) for supplying the first propellant (P1) to the combustor (201), a second supply line (L220) for supplying the second propellant (P2) to the combustor (201), and a third supply line (L230) for supplying the high-temperature gas generated in the gas generator (240) to the turbine (230). Additionally, it further includes a first-1 supply line (L215) for supplying a first propellant (P1) to a gas generator (240), a second-1 supply line (L225) for supplying a second propellant (P2) to a gas generator (140), and a heat exchange line (L221) provided on the second supply line (L220) to pass through the outer surface of a combustor (201).

[0039] The detailed configuration of the above-described configuration of the liquid rocket engine (200) according to the second embodiment of the present invention is identical to that of the liquid rocket engine (100) according to the first embodiment, so the relevant description is omitted.

[0040] At this time, the liquid rocket engine (200) of the second embodiment of the present invention has the following configuration to utilize the high-temperature, high-pressure exhaust gas that drives the turbine (230).

[0041] The liquid rocket engine (200) includes an exhaust turbine (270) driven by exhaust gas, and a booster pump (280) connected to the exhaust turbine (270) via an exhaust drive shaft (275) and provided at the front end of a second supply line (L220) to increase the supply pressure of the second propellant (P2) by rotation. Additionally, it includes a fifth supply line (L270) at its front end connected to a turbine (230) to receive high-temperature, high-pressure exhaust gas, and at its rear end connected to the exhaust turbine (270) to supply high-temperature, high-pressure exhaust gas to the exhaust turbine (270).

[0042] Therefore, the liquid rocket engine (200) of the present invention has the effect of improving combustion performance by increasing the fuel supply pressure supplied to the fuel pump using discarded high-temperature, high-pressure exhaust gas, thereby improving the fuel pump intake performance.

[0043] - Example 3 (Simultaneous pressurization of oxidizer and fuel type) (Gas generator type)

[0044] FIG. 4 shows a schematic diagram of a liquid rocket engine (300) of the third embodiment of the present invention.

[0045] As described, the liquid rocket engine (300) comprises a combustor (301), a first pump (310) for pumping a first propellant (P1), a second pump (320) for pumping a second propellant (P2), a turbine (330) connected to the first and second pumps (310) (320) by a drive shaft (335), and a gas generator (340) for generating a driving gas for driving the turbine (330). Additionally, it comprises a first supply line (L310) for supplying the first propellant (P1) to the combustor (301), a second supply line (L320) for supplying the second propellant (P2) to the combustor (301), and a third supply line (L330) for supplying the high-temperature gas generated in the gas generator (340) to the turbine (330). Additionally, it further includes a first-1 supply line (L315) for supplying a first propellant (P1) to a gas generator (340), a second-1 supply line (L325) for supplying a second propellant (P2) to a gas generator (340), and a heat exchange line (L321) provided on the second supply line (L320) to pass through the outer surface of a combustor (301).

[0046] The detailed configuration of the above-described configuration of the liquid rocket engine (300) according to the third embodiment of the present invention is identical to that of the liquid rocket engine (100)(200) according to the first or second embodiment, so the relevant description is omitted.

[0047] At this time, the liquid rocket engine (300) of the third embodiment of the present invention has the following configuration to utilize the high-temperature, high-pressure exhaust gas that drives the turbine (330).

[0048] The liquid rocket engine (300) includes a first exhaust turbine (350) driven by exhaust gas, and a first booster pump (360) connected to the first exhaust turbine (350) via a first exhaust drive shaft (355) and provided at the front end of a first supply line (L310) to increase the supply pressure of the first propellant (P1) by rotation. Additionally, it includes a fourth supply line (L350) at its front end connected to a turbine (330) to receive high-temperature, high-pressure exhaust gas, and at its rear end connected to the first exhaust turbine (350) to supply high-temperature, high-pressure exhaust gas to the exhaust turbine (350).

[0049] Additionally, the liquid rocket engine (300) includes a second exhaust turbine (370) driven by exhaust gas, and a second booster pump (380) connected to the second exhaust turbine (370) via a second exhaust drive shaft (375) and provided at the front end of the second supply line (L320) to increase the supply pressure of the second propellant (P2) by rotation. Additionally, it includes a fifth supply line (L370) at its front end connected to the turbine (330) to receive high-temperature, high-pressure exhaust gas, and at its rear end connected to the second exhaust turbine (370) to supply high-temperature, high-pressure exhaust gas to the second exhaust turbine (370).

[0050] Meanwhile, the first and second exhaust turbines (350, 370) and the first and second exhaust drive shafts (355, 375) may be formed as a single unit, so that a single exhaust turbine may be connected to the first and second booster pumps (360, 380) respectively through a single drive shaft. Accordingly, the fourth and fifth supply lines (L350, L370) may also be configured as a single unit.

[0051] Therefore, the liquid rocket engine (300) of the present invention has the effect of further improving combustion performance by increasing the supply pressure of the oxidizer and fuel supplied to the oxidizer and fuel pump using the discarded high-temperature and high-pressure exhaust gas, thereby improving the intake performance of the oxidizer and fuel pump.

[0052] - Example 4 (Generator Type) (Gas Generator Type)

[0053] FIG. 5 shows a schematic diagram of a liquid rocket engine (400) of the fourth embodiment of the present invention.

[0054] As described, the liquid rocket engine (400) comprises a combustor (401), a first pump (410) for pumping a first propellant (P1), a second pump (420) for pumping a second propellant (P2), a turbine (430) connected to the first and second pumps (410) (420) by a drive shaft (435), and a gas generator (440) for generating a driving gas for driving the turbine (430). Additionally, it comprises a first supply line (L410) for supplying the first propellant (P1) to the combustor (401), a second supply line (L420) for supplying the second propellant (P2) to the combustor (201), and a third supply line (L430) for supplying the high-temperature gas generated in the gas generator (440) to the turbine (430). Additionally, it further includes a first-1 supply line (L415) for supplying a first propellant (P1) to a gas generator (440), a second-1 supply line (L425) for supplying a second propellant (P2) to a gas generator (140), and a heat exchange line (L421) provided on the second supply line (L420) to pass through the outer surface of a combustor (401).

[0055] The detailed configuration of the above-described configuration of the liquid rocket engine (400) according to the fourth embodiment of the present invention is identical to that of the liquid rocket engines (100)(200)(300) according to the first to third embodiments, so the relevant description is omitted.

[0056] At this time, the liquid rocket engine (400) of the fourth embodiment of the present invention has the following configuration to utilize the high-temperature, high-pressure exhaust gas that drives the turbine (430).

[0057] The liquid rocket engine (400) includes an exhaust turbine (450) driven by exhaust gas and a generator (490) connected to the exhaust turbine (470) via an exhaust drive shaft (455). Additionally, it includes a fourth supply line (L450) in which the front end is connected to the turbine (430) to receive high-temperature, high-pressure exhaust gas, and the rear end is connected to the exhaust turbine (450) to supply high-temperature, high-pressure exhaust gas to the exhaust turbine (250). The electricity generated by the generator (490) can be configured to be charged and stored in a rechargeable battery or supplied to electronic equipment that requires electricity.

[0058] Therefore, the liquid rocket engine (400) of the present invention has the effect of reducing volume or weight and reducing battery capacity by utilizing high-temperature, high-pressure exhaust gas that is discarded, thereby eliminating additional power generation facilities.

[0059] Additionally, the exhaust turbine (450) described above may be configured to be connected to the booster pump (160) (280) of the first or second embodiment described above to drive the generator (490) and simultaneously drive the booster pump (160) (280) of the first or second embodiment.

[0060] - Example 5 (Oxidizer pressurized type) (Expansion gas classification method)

[0061] FIG. 6 illustrates a schematic diagram of a liquid rocket engine (500) of the fifth embodiment of the present invention. (In the first embodiment described above, a configuration is described in which turbine driving gas is supplied to a turbine using a gas generator, but in this embodiment, a configuration is shown in which a portion of the fuel is heated and expanded through a combustor and utilized as turbine driving gas.)

[0062] As described, the liquid rocket engine (500) comprises a combustor (501), a first pump (510) for pumping a first propellant (P1), a second pump (520) for pumping a second propellant (P2), and a turbine (530) for driving the first and second pumps (510) (520). Additionally, the engine (500) comprises a first supply line (L510) for supplying the first propellant (P1) to the combustor (501) and a second supply line (L520) for supplying the second propellant (P2) to the combustor (501). The second supply line (L520) further comprises a heat exchange line (L521) passing through the outer surface of the combustor (501) so that the second propellant (P2) can be heated by the combustion heat of the combustor (501).

[0063] Meanwhile, the engine (500) may be configured to further include a second supply line (L522) in which the front end is branched from the rear end of the heat exchange line (L521) and the rear end is connected to the turbine (530) so as to supply a portion of the high-temperature, high-pressure second propellant (P2) passing through the combustor (501) to the turbine (530).

[0064] The detailed configuration of the above-described configuration of the liquid rocket engine (500) according to the fifth embodiment of the present invention is identical to that of the liquid rocket engine (100) according to the first embodiment, so the relevant description is omitted.

[0065] At this time, the liquid rocket engine (500) of the fifth embodiment of the present invention has the following configuration to utilize the high-temperature, high-pressure exhaust gas that drives the turbine (530).

[0066] The liquid rocket engine (500) includes an exhaust turbine (550) driven by exhaust gas, and a booster pump (560) connected to the exhaust turbine (550) via an exhaust drive shaft (555) and provided at the front end of a first supply line (L510) to increase the supply pressure of the first propellant (P1) by rotation. Additionally, it includes a fourth supply line (L550) at its front end connected to a turbine (530) to receive high-temperature, high-pressure exhaust gas, and at its rear end connected to the exhaust turbine (550) to supply high-temperature, high-pressure exhaust gas to the exhaust turbine (550).

[0067] Therefore, the liquid rocket engine (500) of the present invention has the effect of improving combustion performance by increasing the supply pressure of the oxidizer supplied to the oxidizer pump using the discarded high-temperature, high-pressure exhaust gas, thereby improving the suction performance of the oxidizer pump.

[0068] In addition, it is obvious that the turbo-driven gas supply method of the liquid rocket engine of the second to fourth embodiments described above can be configured by replacing it with the expansion gas classification method of the fifth embodiment.

[0069] - Example 6 (Oxidizer pressurized type) (Combustion gas classification method)

[0070] FIG. 7 illustrates a schematic diagram of a liquid rocket engine (600) of the sixth embodiment of the present invention. (In the first embodiment described above, a configuration is described in which turbine driving gas is supplied to a turbine using a gas generator, but in this embodiment, a configuration is shown in which a portion of the combustion gas burned in a combustor is utilized as turbine driving gas.)

[0071] As described, the liquid rocket engine (600) includes a combustor (601), a first pump (610) for pumping a first propellant (P1), a second pump (620) for pumping a second propellant (P2), and a turbine (630) for driving the first and second pumps (610) (620). Additionally, the engine (600) includes a first supply line (L610) for supplying the first propellant (P1) to the combustor (601) and a second supply line (L620) for supplying the second propellant (P2) to the combustor (601). The second supply line (L620) further includes a heat exchange line (L621) passing through the outer surface of the combustor (601) so that the second propellant (P2) can be heated by the combustion heat of the combustor (601).

[0072] Meanwhile, the engine (600) may further include a sixth supply line (L660) in which the front end is connected to the combustor (601) and the rear end is connected to the turbine (630) to supply a portion of the high-temperature, high-pressure combustion gas combusted in the combustor (601) to the turbine (630).

[0073] The detailed configuration of the above-described configuration of the liquid rocket engine (600) according to the 6th embodiment of the present invention is identical to that of the liquid rocket engine (100) according to the 1st embodiment, so the relevant description is omitted.

[0074] At this time, the liquid rocket engine (600) of the sixth embodiment of the present invention has the following configuration to utilize the high-temperature, high-pressure exhaust gas that drives the turbine (630).

[0075] The liquid rocket engine (600) includes an exhaust turbine (650) driven by exhaust gas, and a booster pump (660) connected to the exhaust turbine (650) via an exhaust drive shaft (655) and provided at the front end of a first supply line (L610) to increase the supply pressure of the first propellant (P1) by rotation. Additionally, it includes a fourth supply line (L650) at its front end connected to a turbine (630) to receive high-temperature, high-pressure exhaust gas, and at its rear end connected to the exhaust turbine (650) to supply high-temperature, high-pressure exhaust gas to the exhaust turbine (650).

[0076] Therefore, the liquid rocket engine (600) of the present invention has the effect of improving combustion performance by increasing the supply pressure of the oxidizer supplied to the oxidizer pump using the discarded high-temperature, high-pressure exhaust gas, thereby improving the suction performance of the oxidizer pump.

[0077] In addition, it is obvious that the turbo-driven gas supply method of the liquid rocket engine of the second to fourth embodiments described above can be configured by replacing it with the combustion gas classification method of the sixth embodiment.

[0078] The technical concept of the present invention should not be interpreted as being limited to the embodiments described above. Not only is the scope of application diverse, but various modifications are possible at the level of a person skilled in the art without departing from the essence of the invention claimed in the claims. Therefore, such improvements and modifications fall within the scope of protection of the present invention insofar as they are obvious to a person skilled in the art. Explanation of the symbols

[0079] 100~600: Liquid Rocket Engine P1: 1st Propellant P2: 2nd Propellant 101, 201, 301, 401, 501, 601: Combustion Chamber 110, 210, 310, 410, 510, 610: 1st Pump 120, 220, 320, 420, 520, 620: 2nd Pump 130, 230, 330, 430, 530, 630: Turbine 140, 240, 340, 440: Gas Generator 150, 270, 450, 550, 650: Exhaust Turbine 350: 1st Exhaust Turbine 370: 2nd Exhaust Turbine 160, 280, 460, 560, 660: Booster Pump 360 : 1st Booster Pump 380 : 2nd Booster Pump L110, L210, L310, L410, L510, L610 : 1st Supply Line L115, L215, L315, L415 : 1-1 Supply Line L120, L220, L320, L420, L520, L620 : 2nd Supply Line L121, L221, L321, L421, L521, L621 : Heat Exchange Line L125, L225, L325, L425 : 2-1 Supply Line L522 : 2-2 Supply Line L130, L230, L330, L430 : 3rd Supply Line L150, L350, L450, L550, L650 : 4th Supply Line L270, L370 : 5 Supply Line L660: 6th Supply Line

Claims

Claim 1 A first propellant which is either an oxidizer or a fuel and is catalytically decomposable, and a second propellant which is the other of an oxidizer or a fuel; a combustor for receiving and combusting the first and second propellants to generate thrust; a first supply line for supplying the first propellant to the combustor and a second supply line for supplying the second propellant to the combustor; a first pump provided on the first supply line to pressurize the first propellant and a second pump provided on the second supply line to pressurize the second propellant; a turbine driven by high-temperature gas and connected to the first and second pumps via a drive shaft; a third supply line, the front end of which is connected to a high-temperature gas supply means that generates the high-temperature gas and the rear end of which is connected to the turbine to supply high-temperature gas to the turbine; a first exhaust turbine driven by exhaust gas discharged after driving the turbine; a first booster pump connected to the exhaust turbine via a first exhaust drive shaft and provided at the front end of the first supply line to increase the supply pressure of the first propellant; A liquid rocket engine utilizing turbine exhaust gas, comprising: a fourth supply line, the front end of which is connected to the turbine and the rear end of which is connected to the exhaust turbine to supply the exhaust gas to the first exhaust turbine. Claim 2 A liquid rocket engine utilizing turbine exhaust gas according to claim 1, further comprising: a second booster pump connected to the exhaust turbine through the first exhaust drive shaft and provided at the front end of the second supply line to increase the supply pressure of the second propellant. Claim 3 A liquid rocket engine utilizing turbine exhaust gas according to claim 1, wherein the engine further comprises: a second exhaust turbine driven by exhaust gas discharged after driving the turbine; a second booster pump connected to the exhaust turbine through a second exhaust drive shaft and provided at the front end of the second supply line to increase the supply pressure of the second propellant; and a fifth supply line having its front end connected to the turbine and its rear end connected to the exhaust turbine to supply the exhaust gas to the second exhaust turbine. Claim 4 A liquid rocket engine utilizing turbine exhaust gas, wherein the engine further comprises a generator connected to the exhaust turbine through the first exhaust drive shaft. Claim 5 A first propellant which is either an oxidizer or a fuel and is catalytically decomposable, and a second propellant which is the other of an oxidizer or a fuel; a combustor for receiving and burning the first and second propellants to generate thrust; a first supply line for supplying the first propellant to the combustor and a second supply line for supplying the second propellant to the combustor; a first pump provided on the first supply line to pressurize the first propellant and a second pump provided on the second supply line to pressurize the second propellant; a turbine driven by high-temperature gas and connected to the first and second pumps via a drive shaft; a third supply line, the front end of which is connected to a high-temperature gas supply means that generates the high-temperature gas and the rear end of which is connected to the turbine to supply high-temperature gas to the turbine; a first exhaust turbine driven by exhaust gas discharged after driving the turbine; and a generator connected to the exhaust turbine via a first exhaust drive shaft. A liquid rocket engine utilizing turbine exhaust gas, comprising: a fourth supply line, the front end of which is connected to the turbine and the rear end of which is connected to the exhaust turbine to supply the exhaust gas to the first exhaust turbine. Claim 6 A liquid rocket engine utilizing turbine exhaust gas, wherein the high-temperature gas supply means according to claim 1 or 5 comprises: a gas generator that receives the first and second propellants and generates the high-temperature gas by combustion; a first-1 supply line branched from the first supply line and having its rear end connected to the gas generator to supply the first propellant to the gas generator; and a second-1 supply line branched from the second supply line and having its rear end connected to the gas generator to supply the second propellant to the gas generator. Claim 7 A liquid rocket engine utilizing turbine exhaust gas according to claim 1 or 5, wherein the engine further comprises a heat exchange line in which the second supply line passes through the outer surface of the combustor so that the second propellant is heated by the combustion heat of the combustor. Claim 8 In claim 7, the high-temperature gas supply means comprises a 2-2 supply line, the front end of which branches off from the rear end of the heat exchange line and the rear end of which is connected to the third supply line, to supply a portion of the high-temperature second propellant passing through the combustor to the turbine, thereby utilizing turbine exhaust gas in a liquid rocket engine. Claim 9 A liquid rocket engine utilizing turbine exhaust gas according to claim 1 or 5, wherein the high-temperature gas supply means comprises a sixth supply line, the front end of which is connected to the combustor and the rear end of which is connected to the third supply line, so as to supply a portion of the high-temperature combustion gas combusted in the combustor to the turbine.

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