Turbine assembly
The present disclosure relates to a turbine assembly including a turbo pump configured to pressurize an oxidant and fuel to a high pressure and supply the oxidant and fuel to a combustor, and more particularly, to a technology capable of recycling exhaust gas that has operated a turbine of a turbo pump.
1 . A turbine assembly comprising:
a first propellant that is any one of an oxidant and a fuel and is capable of catalytic decomposition;
a second propellant that is the other of the oxidant and the fuel;
a combustor configured to generate a propulsive force by receiving and combusting the first and second propellants;
a first supply line configured to supply the first propellant to the combustor;
a second supply line configured to supply the second propellant to the combustor;
a first pump provided in the first supply line and configured to pressurize the first propellant;
a second pump provided in the second supply line and configured to pressurize the second propellant;
a turbine configured to be operated by a high-temperature gas and connected to the first and second pumps through a driving 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 the high-temperature gas to the turbine;
a first exhaust turbine configured to be operated by an exhaust gas discharged after operating the turbine;
a first booster pump connected to the first exhaust turbine through a first exhaust driving shaft, provided at a front end of the first supply line and configured to increase supply pressure of the first propellant by using an energy generated by the first exhaust turbine operated by the exhaust gas; and
a fourth supply line having a front end connected to the turbine, and a rear end connected to the first exhaust turbine to supply the exhaust gas to the first exhaust turbine.
2 . The turbine assembly of claim 1 , further comprising a second booster pump connected to the first exhaust turbine through the first exhaust driving shaft, provided at a front end of the second supply line, and configured to increase supply pressure of the second propellant.
3 . The turbine assembly of claim 1 , further comprising:
a second exhaust turbine configured to be operated by the exhaust gas discharged after operating the turbine;
a fifth supply line having a front end connected to the turbine, and a rear end connected to the second exhaust turbine to supply the exhaust gas to the second exhaust turbine, and
a second booster pump connected to the second exhaust turbine through a second exhaust driving shaft, provided at a front end of the second supply line, and configured to increase supply pressure of the second propellant.
4 . The turbine assembly of claim 1 , further comprising an electric generator connected to the first exhaust turbine through the first exhaust driving shaft.
5 . The turbine assembly of claim 1 , wherein the high-temperature gas supply means comprises:
a gas generator configured to generate the high-temperature gas by receiving and combusting the first and second propellants;
a first-first supply line branching off from the first supply line and having a rear end connected to the gas generator to supply the first propellant to the gas generator; and
a second-first supply line branching off from the second supply line and having a rear end connected to the gas generator to supply the second propellant to the gas generator.
6 . The turbine assembly of claim 1 , wherein the second supply line further comprises a heat exchange line configured to pass through an outer surface of the combustor so that the second propellant is heated by combustion heat of the combustor.
7 . The turbine assembly of claim 6 , wherein the high-temperature gas supply means comprises a second-second supply line having a front end branching off from a rear end of the heat exchange line, and a rear end of the second-second supply line is connected to the third supply line, such that a part of the high-temperature second propellant, which has passed through the combustor, is supplied to the turbine.
8 . The turbine assembly of claim 1 , wherein the high-temperature gas supply means comprises a sixth supply line having a front end connected to the combustor, and a rear end connected to the third supply line, such that a part of a high-temperature combustion gas combusted in the combustor is supplied to the turbine.