A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a first stage turbine, and a turbocharger is discussed. The first stage turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exh
A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a first stage turbine, and a turbocharger is discussed. The first stage turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exhaust port of each rotary unit is in fluid communication with the flowpath of the first stage turbine upstream of its rotor. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit. The inlet of the second stage turbine of the turbocharger is in fluid communication with the flowpath of the first stage turbine downstream of its rotor. The first stage turbine has a lower reaction ratio than that of the second stage turbine. A method of compounding at least two rotary engines is also discussed.
대표청구항▼
1. A compound cycle engine comprising: an output shaft;at least two rotary units each defining an internal combustion engine including an engine rotor sealingly and rotationally received within a respective housing, each housing defining an inlet port and an exhaust port, the engine rotor of each of
1. A compound cycle engine comprising: an output shaft;at least two rotary units each defining an internal combustion engine including an engine rotor sealingly and rotationally received within a respective housing, each housing defining an inlet port and an exhaust port, the engine rotor of each of the at least two rotary units being in driving engagement with the output shaft;a first stage turbine including a flowpath and a turbine rotor having a circumferential array of blades extending across the flowpath, the turbine rotor being in driving engagement with the output shaft; anda turbocharger including a compressor and a second stage turbine in driving engagement with one another; wherein:an outlet of the compressor is in fluid communication with the inlet port of each housing;the exhaust port of each housing is in fluid communication with a first portion of the flowpath of the first stage turbine, the first portion of the flowpath being located upstream of the circumferential array of blades of the first stage turbine;an inlet of the second stage turbine is in fluid communication with a second portion of the flowpath of the first stage turbine, the second portion of the flowpath being located downstream of the circumferential array of blades of the first stage turbine;the first stage turbine has the output shaft extending therethrough, the least two rotary units including a first rotary unit located in front of the first stage turbine along the output shaft and a second rotary unit located behind the first stage turbine along the output shaft; andthe first stage turbine has a lower reaction ratio than that of the second stage turbine. 2. The compound cycle engine as defined in claim 1, wherein the reaction ratio of the first stage turbine is a pressure-based reaction ratio having a value of at most 0.25. 3. The compound cycle engine as defined in claim 1, wherein the reaction ratio of the first stage turbine is a pressure-based reaction ratio having a value of at most 0.1 and the second stage turbine has a pressure-based reaction ratio having a value of at least 0.25. 4. The compound cycle engine as defined in claim 1, wherein the reaction ratio of the first stage turbine is a pressure-based reaction ratio having a value of at most 040.2 and the second stage turbine has a pressure-based reaction ratio having a value of at least 0.25. 5. The compound cycle engine as defined in claim 1, wherein each of the at least two rotary units is a Wankel engine. 6. The compound cycle engine as defined in claim 1, wherein the compressor and the second stage turbine are in driving engagement with one another through a turbocharger shaft rotatable independently of the output shaft. 7. The compound cycle engine as defined in claim 6, wherein the turbocharger shaft and the output shaft extend in a non-parallel manner. 8. The compound cycle engine as defined in claim 1, further comprising common rail fuel injectors for each of the at least two rotary units, and a heavy fuel source in communication with the fuel injectors. 9. The compound cycle engine as defined in claim 1, wherein the at least two rotary units include the first rotary unit, the second rotary unit, and additional rotary units, the additional rotary units being located such that a same number of the rotary units is disposed in front of and behind the first stage turbine along the output shaft. 10. The compound cycle engine as defined in claim 1, wherein the at least two rotary units include the first rotary unit, the second rotary unit, and additional rotary units, the additional rotary units being located such that a number of the rotary units disposed in front of the first stage turbine is one more or one less than a number of the rotary units disposed behind the first stage turbine along the output shaft. 11. A compound cycle engine comprising: a first stage turbine having a first turbine rotor drivingly engaged to an output shaft;at least two rotary engines each having an engine rotor sealingly and rotationally received within a respective housing having an inlet port and an exhaust port, the engine rotor of each of the at least two rotary engines being drivingly engaged to the output shaft, the at least two rotary engines including a first rotary engine located in front of the first stage turbine along the output shaft and a second rotary engine located behind the first stage turbine along the output shaft;a respective exhaust pipe providing fluid communication between each exhaust port and an inlet of the first stage turbine;a turbocharger including a compressor and a second stage turbine drivingly engaged to one another;an inlet duct providing fluid communication between an outlet of the compressor and the inlet port of each of the at least two rotary engines; anda turbine pipe providing fluid communication between an outlet of the first stage turbine and an inlet of the second stage turbine;wherein the first stage turbine has a lower reaction ratio than that of the second stage turbine. 12. The compound cycle engine as defined in claim 11, wherein the reaction ratio of the first stage turbine is a pressure-based reaction ratio having a value of at most 0.25. 13. The compound cycle engine as defined in claim 11, wherein the reaction ratio of the first stage turbine is a pressure-based reaction ratio having a value of at most 0.1 and the second stage turbine has a pressure-based reaction ratio having a value of at least 0.25. 14. The compound cycle engine as defined in claim 11, wherein the reaction ratio of the first stage turbine is a pressure-based reaction ratio having a value of at most 0.2 and the second stage turbine has a pressure-based reaction ratio having a value of at least 0.25. 15. The compound cycle engine as defined in claim 11, wherein each exhaust pipe extends axially. 16. The compound cycle engine as defined in claim 11, wherein each of the at least two rotary engines is a Wankel engine. 17. The compound cycle engine as defined in claim 11, wherein the first stage turbine has the output shaft extending therethrough and is in driving engagement with the output shaft through a transmission, the transmission being located between the first and second rotary engines. 18. The compound cycle engine as defined in claim 11, further comprising common rail fuel injectors for each of the at least two rotary engines, and a heavy fuel source in communication with the fuel injectors. 19. The compound cycle engine as defined in claim 11, wherein the at least two rotary engines are located such that a same number of the at least two rotary engines is disposed in front of and behind the first stage turbine along the output shaft. 20. The compound cycle engine as defined in claim 11, wherein the at least two rotary engines are located such that a number of the at least two rotary engines disposed in front of the first stage turbine is one more or one less than a number of the at least two rotary engines disposed behind the first stage turbine along the output shaft. 21. A method of compounding at least two rotary engines, the method comprising: drivingly engaging a second stage turbine and a compressor in a turbocharger such as to drive the compressor with the second stage turbine;drivingly engaging each of the at least two rotary engines and a first stage turbine to an output shaft by placing the first stage turbine between two of the at least two rotary engines along the output shaft, the first stage turbine having a lower reaction ratio than that of the second stage turbine;circulating a compressor exhaust flow from an outlet of the compressor into an inlet port of each of the at least two rotary engines;circulating an engine exhaust flow from an exhaust port of each of the at least two rotary engines into an inlet of the first stage turbine; andcirculating a first stage turbine exhaust flow from an outlet of the first stage turbine into an inlet of the second stage turbine of the turbocharger. 22. The method as defined in claim 21, further comprising providing fluid communication between a source of heavy fuel and each of the at least two rotary engines.
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이 특허에 인용된 특허 (18)
Whurr John (Derby GB2), Aircraft compound cycle propulsion engine.
Finger, Helmut; Fledersbacher, Peter; Sumser, Siegfried; Wirbeleit, Friedrich, Internal combustion engine with exhaust gas turbocharger and compound power turbine.
Jenes John A. (7 Hollies Close Newton Solney ; Burton-on-Trent ; Staffordshire ; DE15 OSB GB2), Positive displacement engine compounded with a gas turbine engine.
Kuhlbach, Kai Sebastian; Schorn, Norbert Andreas; Weber, Carsten, Supercharged internal combustion engine having two turbines, and method for operating an internal combustion engine of said type.
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