A turboprop propulsion unit includes at least one pusher propeller 5, 6 driven by an aircraft gas-turbine engine, with the aircraft gas-turbine engine being arranged in front of the pusher propeller 5, 6 in a direction of flight. A turbine outlet area 9 is arranged at the front in the direction of f
A turboprop propulsion unit includes at least one pusher propeller 5, 6 driven by an aircraft gas-turbine engine, with the aircraft gas-turbine engine being arranged in front of the pusher propeller 5, 6 in a direction of flight. A turbine outlet area 9 is arranged at the front in the direction of flight and a compressor area 14 faces towards the pusher propeller 5, 6.
대표청구항▼
1. A turboprop propulsion unit comprising: a gas-turbine engine,at least one pusher propeller positioned aft of the gas-turbine engine and driven by the gas-turbine engine;wherein a main gas flow through the gas-turbine engine moves from aft forward, with respect to a direction of propulsion, such t
1. A turboprop propulsion unit comprising: a gas-turbine engine,at least one pusher propeller positioned aft of the gas-turbine engine and driven by the gas-turbine engine;wherein a main gas flow through the gas-turbine engine moves from aft forward, with respect to a direction of propulsion, such that a turbine outlet area of the gas-turbine engine is physically positioned forward of a compressor of the gas-turbine engine in the direction of flight; and at least one inlet flow duct for guiding airflow to the compressor, at least a portion of the at least one inlet flow duct positioned forward of the compressor. 2. The turboprop propulsion unit of claim 1, and further comprising: a reduction gear; anda turbine shaft connecting a turbine of the gas turbine engine with the pusher propeller via the reduction gear. 3. The turboprop propulsion unit of claim 2, wherein the at least one inlet flow duct guides airflow from an exterior of the gas-turbine engine toward the compressor and generally reverses a direction of such airflow before directing such airflow into an inflow area of the compressor. 4. The turboprop propulsion unit of claim 3, and further comprising at least one exhaust gas flow duct for guiding and generally reversing a direction of exhaust gas flow from the gas-turbine engine toward the thrust propeller. 5. The turboprop propulsion unit of claim 4, and further comprising at least one exhaust nozzle connected to the exhaust gas flow duct for rearwardly directing exhaust gas flow from the exhaust gas flow duct. 6. The turboprop propulsion unit of claim 5, wherein the inlet flow duct and the exhaust nozzle are arranged offset from one another in a circumferential direction of the turboprop propulsion unit. 7. The turboprop propulsion unit of claim 6, and further comprising a plurality of at least one of the inlet flow duct and the exhaust nozzle. 8. The turboprop propulsion unit of claim 7, comprising a plurality of counter-rotating pusher propellers. 9. The turboprop propulsion unit of claim 1, wherein the at least one inlet flow duct guides airflow from an exterior of the gas-turbine engine toward the compressor and generally reverses a direction of such airflow before directing such airflow into an inflow area of the compressor. 10. The turboprop propulsion unit of claim 9, and further comprising at least one exhaust gas flow duct for guiding and generally reversing a direction of exhaust gas flow from the gas-turbine engine toward the thrust propeller. 11. The turboprop propulsion unit of claim 10, and further comprising at least one exhaust nozzle connected to the exhaust gas flow duct for rearwardly directing exhaust gas flow from the exhaust gas flow duct. 12. The turboprop propulsion unit of claim 11, wherein the inlet flow duct and the exhaust nozzle are arranged offset from one another in a circumferential direction of the turboprop propulsion unit. 13. The turboprop propulsion unit of claim 12, and further comprising a plurality of at least one of the inlet flow duct and the exhaust nozzle. 14. The turboprop propulsion unit of claim 13, comprising a plurality of counter-rotating pusher propellers. 15. The turboprop propulsion unit of claim 1, and further comprising at least one exhaust gas flow duct for guiding and generally reversing a direction of exhaust gas flow from the gas-turbine engine toward the thrust propeller. 16. The turboprop propulsion unit of claim 15, and further comprising at least one exhaust nozzle connected to the exhaust gas flow duct for rearwardly directing exhaust gas flow from the exhaust gas flow duct. 17. The turboprop propulsion unit of claim 16, wherein the inlet flow duct and the exhaust nozzle are arranged offset from one another in a circumferential direction of the turboprop propulsion unit. 18. The turboprop propulsion unit of claim 17, and further comprising a plurality of at least one of the inlet flow duct and the exhaust nozzle. 19. The turboprop propulsion unit of claim 18, comprising a plurality of counter-rotating pusher propellers. 20. The turboprop propulsion unit of claim 1, comprising a plurality of counter-rotating pusher propellers.
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이 특허에 인용된 특허 (2)
Lardellier Alain M. J. (Melun FRX), Counterrotating fan engine.
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