A disclosed turbofan engine includes a gas generator section for generating a gas stream flow. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for g
A disclosed turbofan engine includes a gas generator section for generating a gas stream flow. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than forty-five (45) inches and an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine for cruise, climb and sea level take-off power conditions.
대표청구항▼
1. A turbofan engine comprising: a low spool having an inner shaft and a power turbine including between 3 and 6 stages;a high spool having an outer shaft concentric about the inner shaft;a propulsor section including a fan with a number of fan blades that have a fan tip diameter between 50 inches a
1. A turbofan engine comprising: a low spool having an inner shaft and a power turbine including between 3 and 6 stages;a high spool having an outer shaft concentric about the inner shaft;a propulsor section including a fan with a number of fan blades that have a fan tip diameter between 50 inches and 160 inches, wherein a ratio between the number of fan blades and a number of power turbine rotors is between 3.3 and 8.6; anda speed reduction device in driving connection between the power turbine and the fan, wherein the speed reduction device includes a speed reduction greater than 2.3, wherein an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through a bypass flow path, a tip diameter of a fan and a first rotational speed of the power turbine, the EUTP is less than 0.30 in operation at a maximum takeoff thrust, wherein the net engine thrust is between 16,000 lbf and 120,000 lbf, the mass flow rate of air through the bypass flow path is between 625 lbm/sec and 80,000 lbm/sec and the first rotational speed is between 6200 rpm and 12,500 rpm. 2. The turbofan engine as recited in claim 1, wherein the EUTP in operation at the maximum take-off thrust is less than 0.25. 3. The turbofan engine as recited in claim 2, wherein the EUTP in operation at a cruise condition is less than 0.10. 4. The turbofan engine as recited in claim 3, wherein the EUTP in operation at a climb condition is less than 0.10. 5. The turbofan engine as recited in claim 4, wherein the EUTP in operation at the maximum takeoff thrust is less than 0.10. 6. The turbofan engine as recited in claim 4, wherein the EUTP in operation at a cruise condition is less than 0.08. 7. The turbofan engine as recited in claim 6, wherein the EUTP in operation at the maximum takeoff thrust is less than 0.10. 8. The turbofan engine as recited in claim 1, further comprising a low fan pressure ratio across the fan alone that is less than 1.45 in operation. 9. The turbofan engine as recited in claim 8, further comprising a gas generator section including a core flow path portion of the propulsor section, a low pressure compressor, a combustor, a two-stage high pressure turbine and a part of the power turbine. 10. The turbofan engine as recited in claim 9, wherein the number of fan blades is less than 20. 11. The turbofan engine as recited in claim 10, wherein the EUTP at the maximum takeoff thrust is less than 0.15. 12. The turbofan engine as recited in claim 11, wherein the EUTP in operation at the maximum takeoff thrust is less than 0.10. 13. The turbofan engine as recited in claim 1, wherein the fan rotates in operation at a fan tip speed less than about 1150 ft/sec. 14. The turbofan engine as recited in claim 13, further comprising a gas generator section including a core flow path portion of the propulsor section, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a part of the power turbine, the gas generator in operation having an overall pressure ratio between entering airflow into the gas generator and a gas stream exiting from the gas generator that is between 40 and 80. 15. The turbofan engine as recited in claim 14, wherein the fan includes less than 20 fan blades. 16. The turbofan engine as recited in claim 15, wherein the gas generator includes a two stage high pressure turbine. 17. The turbofan engine as recited in claim 16, wherein the EUTP in operation at the maximum takeoff thrust is less than 0.25 and at a cruise condition is less than 0.10. 18. The turbofan engine as recited in claim 17, wherein the EUTP in operation at the maximum takeoff thrust is less than 0.10. 19. A turbofan engine comprising: a propulsor section including a fan having less than 20 fan blades and a fan tip diameter between 50 inches and 160 inches, and that rotates at a fan tip speed less than about 1150 ft/sec in operation;a low speed spool having an inner shaft and a power turbine including more than 3 stages and no more than 6 stages and rotating at a speed between 6200 rpm and about 12,500 rpm;a high speed spool having an outer shaft concentric about the inner shaft; anda speed reduction device in driving connection between the power turbine and the fan, wherein the speed reduction device includes a speed reduction greater than 2.3, wherein an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of a mass flow rate of air through a bypass flow path, a tip diameter of the fan and a first rotational speed of the power turbine in operation is less than 0.30 at a sea level takeoff power condition, wherein the net engine thrust is between 16,000 lbf and 120,000 lbf, the mass flow rate of air through the bypass flow path is between 625 lbm/sec and 80,000 lbm/sec and the fan tip diameter is between 50 inches and 160 inches. 20. The turbofan engine as recited in claim 19, wherein the EUTP in operation at the sea level takeoff power condition is less than 0.25. 21. The turbofan engine as recited in claim 20, wherein high speed spool has a two stage high pressure turbine. 22. The turbofan engine as recited in claim 20, wherein the EUTP in operation at one of a climb condition and a cruise condition is less than 0.15. 23. The turbofan engine as recited in claim 22, wherein a ratio between a number of fan blades and a number of rotors in the power turbine is between 3.3 and 8.6. 24. The turbofan engine as recited in claim 23, wherein the EUTP in operation at one of a climb condition and a cruise condition is less than 0.10. 25. The turbofan engine as recited in claim 24, further comprising a low fan pressure ratio across the fan alone that is less than 1.45 in operation. 26. The turbofan engine as recited in claim 25, wherein the EUTP in operation at the sea level takeoff power condition is less than 0.20. 27. The turbofan engine as recited in claim 26, wherein the EUTP at the sea level takeoff power condition is less than 0.15 and at a cruise condition is less than 0.08. 28. The turbofan engine as recited in claim 27, further comprising a gas generator section including a core flow path portion of the propulsor section, a low pressure compressor, a high pressure compressor, a combustor, and a part of the power turbine, the gas generator in operation having an overall pressure ratio between entering airflow into the gas generator and a gas stream exiting from the gas generator that is between 40 and 80, wherein a ratio between a number of fan blades and a number of rotors in the power turbine is between about 3.3 and 8.6.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (67)
Manteiga, John Alan; Wilusz, Christopher James; Dykhuizen, Cornelius Harm, Aircraft engine mount with single thrust link.
Seda, Jorge F.; Dunbar, Lawrence W.; Szucs, Peter N.; Brauer, John C.; Johnson, James E., Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor.
Burr Donald N. (Glastonbury CT) Danilowicz Paul S. (Manchester CT) Franz Thomas C. (Bolton CT) Mortimer Thomas P. (Bolton CT) Pero Edward B. (Somers CT), Fuel and oil heat management system for a gas turbine engine.
Curley Robert C. (White Marsh MD) Fisher Mark T. (Bel Air MD) Dileonardi James V. (Baltimore MD) DePinho ; Jr. A. Norton (Baldwin MD), Light weight fan blade containment system.
Terentieva Valentina Sergeevna (Moscow RUX) Bogachkova Olga Petrovna (Moscow RUX) Goriatcheva Elena Valentinovna (Moscow RUX), Method for protecting products made of a refractory material against oxidation, and resulting protected products.
Brun, Milivoj Konstantin; Luthra, Krishan Lal, Method to prevent recession loss of silica and silicon-containing materials in combustion gas environments.
Brodell Robert F. (Marlborough CT) Hovan Edward J. (Manchester CT) Selfors Steven T. (Somerville MA) Loffredo Constantino V. (Newington CT) Duesler Paul W. (Manchester CT), Nacelle and mounting arrangement for an aircraft engine.
Moniz, Thomas Ory; Schilling, Jan Christopher; Orlando, Robert Joseph; Patt, Raymond Felix, Power take-off system and gas turbine engine assembly including same.
Harry Edwin Eaton, Jr. ; William Patrick Allen ; Nathan S. Jacobson ; Narottam P. Bansal ; Elizabeth J. Opila ; James L. Smialek ; Kang N. Lee ; Irene T. Spitsberg ; Hongyu Wang ; Peter Joel, Silicon based substrate with environmental/thermal barrier layer.
Duesler Paul W. ; Loffredo Constantino V. ; Prosser ; Jr. Harold T. ; Jones Christopher W., Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems.
Rey Nancy M. ; Miller Robin M. ; Tillman Thomas G. ; Rukus Robert M. ; Kettle John L. ; Dunphy James R. ; Chaudhry Zaffir A. ; Pearson David D. ; Dreitlein Kenneth C. ; Loffredo Constantino V. ; Wyno, Variable area nozzle for gas turbine engines driven by shape memory alloy actuators.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.