The invention relates to a field of feeding reaction engines, and in particular a turbopump 9 for feeding at least one combustion chamber 2 with a first propellant, the turbopump comprising a pump 9a, a turbine 9b to the pump 9a in order to drive it, and a variable and/or disengageable braking devic
The invention relates to a field of feeding reaction engines, and in particular a turbopump 9 for feeding at least one combustion chamber 2 with a first propellant, the turbopump comprising a pump 9a, a turbine 9b to the pump 9a in order to drive it, and a variable and/or disengageable braking device 11.
대표청구항▼
1. A feed circuit for feeding at least one combustion chamber with a first propellant, the circuit comprising: a first turbopump comprising: a first pump for pumping a flow of the first propellant;a first turbine, driven by the flow of the first propellant and coupled to the first pump in order to d
1. A feed circuit for feeding at least one combustion chamber with a first propellant, the circuit comprising: a first turbopump comprising: a first pump for pumping a flow of the first propellant;a first turbine, driven by the flow of the first propellant and coupled to the first pump in order to drive the first pump; anda variable and/or disengageable braking device which applies a braking torque to the first turbopump so as to control a speed at which the first turbopump reaches operating equilibrium during a rise in speed; anda heat exchanger situated downstream from the first pump and upstream from the first turbine for heating a flow of the first propellant between the first pump and the first turbine by using heat generated in said combustion chamber,wherein at an end of the rise in speed, the operating equilibrium of the first turbopump is reached when a torque generated by the first turbine is equal to a sum of a torque consumed by the first pump and the braking torque applied by the braking device to the first turbopump,wherein a selective application of the braking device allows the first turbopump to operate at multiple speeds that achieves a selective plurality of thrust levels. 2. A circuit according to claim 1, further including a bypass passage for bypassing at least the first turbine and fitted with a first bypass valve. 3. A feed circuit according to claim 1, wherein said braking device of the first turbopump is an electromagnetic braking device. 4. A feed circuit according to claim 1, wherein said braking device of the first turbopump is a friction braking device. 5. A feed circuit according to claim 1, wherein said braking device of the first turbopump is a hydrodynamic braking device. 6. A system for feeding at least one combustion chamber with propellants, the system comprising: a first circuit for feeding the at least one combustion chamber with a first propellant and comprising: a first turbopump comprising: a first pump for pumping a flow of the first propellant;a first turbine, driven by the flow of the first propellant and coupled to the first pump in order to drive the first pump; anda variable and/or disengageable braking device which applies a braking torque to the first turbopump so as to control a speed at which the first turbopump reaches operating equilibrium during a rise in speed; anda heat exchanger situated downstream from the first pump and upstream from the first turbine for heating the flow of the first propellant between the first pump and the first turbine by using heat generated in said combustion chamber;a second circuit for feeding the at least one combustion chamber with a second propellant; anda second turbopump comprising: a second pump situated in the second circuit for pumping a flow of the second propellant; anda second turbine situated in the first circuit, so as to be driven by the flow of the first propellant, and coupled to the second pump in order to drive the second pump,wherein at an end of the rise in speed, the operating equilibrium of the first turbopump is reached when a torque generated by the first turbine is equal to a sum of a torque consumed by the first pump and the braking torque applied by the braking device to the first turbopump,wherein a selective application of the braking device allows the first turbopump to operate at multiple speeds that achieves a selective plurality of thrust levels. 7. A system according to claim 6, wherein the first circuit also includes a bypass passage for bypassing the second turbine and fitted with a second bypass valve. 8. A system according to claim 6, wherein the second turbine is situated downstream from the first turbine in the first circuit. 9. A system according to claim 6, wherein said first circuit further includes a bypass passage for bypassing at least the first turbine and fitted with a first bypass valve. 10. A system according to claim 6, wherein said braking device for braking the first turbopump is an electromagnetic braking device. 11. A system according to claim 6, wherein said braking device for braking the first turbopump is a friction braking device. 12. A system according to claim 6, wherein said braking device for braking the first turbopump is a hydrodynamic braking device. 13. A method of controlling a combustion chamber fed with a first propellant by a first turbopump comprising a first pump for pumping a flow of the first propellant; a first turbine, driven by the flow of the first propellant after the first propellant has been heated, between the first pump and the first turbine, using heat generated in said combustion chamber, the first turbine being coupled to drive the first pump; and a variable and/or disengageable braking device, the method comprising: applying a braking torque to said first turbopump by the braking device during a rise in speed of the turbopump in order to restrict a flow rate of propellant delivered to the combustion chamber so as to control the speed that said first turbopump reaches in operating equilibrium,wherein at an end of the rise in speed, the operating equilibrium of the first turbopump is reached when a torque generated by the first turbine is equal to a sum of a torque consumed by the first pump and the braking torque applied by the braking device to the first turbopump,wherein a selective application of the braking device allows the first turbopump to operate at multiple speeds that achieves a selective plurality of thrust levels.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (4)
Wagner William R. (Los Angeles CA), Expander-cycle, turbine-drive, regenerative rocket engine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.