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公开(公告)号：US10047701B2
公开(公告)日：2018-08-14
申请号：US15450517
申请日：2017-03-06
发明人： Jayant Sabnis
摘要： 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.
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公开(公告)号：US20170175678A1
公开(公告)日：2017-06-22
申请号：US15450599
申请日：2017-03-06
发明人： Jayant Sabnis
CPC分类号： F02K3/075 , B64D27/10 , F01D5/06 , F01D15/12 , F01D19/02 , F02C3/04 , F02C3/107 , F02K1/52 , F02K3/06 , F04D19/02 , F04D29/325 , F05D2220/323 , F05D2220/36 , F05D2240/35
摘要： 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.
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公开(公告)号：US09624828B2
公开(公告)日：2017-04-18
申请号：US13871221
申请日：2013-04-26
发明人： Jayant Sabnis
摘要： A turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in ambient air. A power turbine converts the gas stream flow into shaft power. The power turbine rotates at a first rotational speed. 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 about fifty (50) 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 is less than about 0.30 at a take-off condition.
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公开(公告)号：US20200217274A1
公开(公告)日：2020-07-09
申请号：US16809092
申请日：2020-03-04
发明人： Jayant Sabnis
IPC分类号： F02K3/075 , F02K1/52 , F01D19/02 , F04D29/32 , F04D19/02 , F01D5/06 , F02C3/04 , B64D27/10 , F01D15/12 , F02C3/107 , F02K3/06
摘要： A disclosed turbofan engine includes a gas generator section for generating a gas stream flow and a propulsor section for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The propulsor section includes a fan driven by a power turbine through a speed reduction device at a second rotational speed lower than a first rotational speed of the power turbine. 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 is between 0.05 and 0.13 during operation of the turbofan engine.
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公开(公告)号：US10669031B2
公开(公告)日：2020-06-02
申请号：US16675585
申请日：2019-11-06
发明人： Jayant Sabnis , Louis J. Bruno
摘要： A method for supplying pressurized air to an aircraft includes that bleed air is bled from a portion of a turbomachine of the aircraft and a thrust output of the turbomachine is increased to increase a pressure of the bleed air in a predetermined environmental condition. The method also includes that modes of an environmental control system (ECS) are switched from a first operating mode configured to receive bleed air from each engine of the aircraft in a first environmental condition to a second operating mode configured to receive bleed air from at least one engine of the aircraft in a second environmental condition. The method further includes that engine thrust is increased in at least one engine and engine thrust is reduced from at least the other engine to maintain a constant total thrust when the ECS is in the second operating mode.
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公开(公告)号：US10047702B2
公开(公告)日：2018-08-14
申请号：US15450599
申请日：2017-03-06
发明人： Jayant Sabnis
摘要： 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.
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公开(公告)号：US20170175675A1
公开(公告)日：2017-06-22
申请号：US15450455
申请日：2017-03-06
发明人： Jayant Sabnis
CPC分类号： F02K3/075 , B64D27/10 , F01D5/06 , F01D15/12 , F01D19/02 , F02C3/04 , F02C3/107 , F02K1/52 , F02K3/06 , F04D19/02 , F04D29/325 , F05D2220/323 , F05D2220/36 , F05D2240/35
摘要： 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 about 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 take-off power conditions.
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公开(公告)号：US20140283500A1
公开(公告)日：2014-09-25
申请号：US13854225
申请日：2013-04-01
发明人： Jayant Sabnis
IPC分类号： F02K3/00
摘要： A turbofan engine includes a gas generator section for generating a gas stream flow with higher energy per unit mass flow than that contained in the ambient air and a power turbine that converts the gas stream flow into shaft power. The turbofan engine further includes a propulsor section including a fan driven by the power turbine through a geared architecture 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. An Engine Unit Thrust Parameter 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 is less than about 0.15 at a take-off condition.
摘要翻译： 涡轮风扇发动机包括气体发生器部分，用于产生具有比包含在环境空气中的每单位质量流更高的能量的气流;以及将气流转换成轴功率的动力涡轮机。 涡轮风扇发动机还包括推进器部分，其包括由动力涡轮机驱动的风扇，该风扇以低于第一速度的第二速度驱动，用于产生作为通过旁路流动路径的空气的质量流量的推进推力。 发动机单元推力参数被定义为净发动机推力除以通过旁路流路的空气的质量流量，风扇的尖端直径和动力涡轮机的第一转速的乘积在一次取样时小于约0.15 关闭条件。
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公开(公告)号：US20200070985A1
公开(公告)日：2020-03-05
申请号：US16675585
申请日：2019-11-06
发明人： Jayant Sabnis , Louis J. Bruno
摘要： A method for supplying pressurized air to an aircraft includes that bleed air is bled from a portion of a turbomachine of the aircraft and a thrust output of the turbomachine is increased to increase a pressure of the bleed air in a predetermined environmental condition. The method also includes that modes of an environmental control system (ECS) are switched from a first operating mode configured to receive bleed air from each engine of the aircraft in a first environmental condition to a second operating mode configured to receive bleed air from at least one engine of the aircraft in a second environmental condition. The method further includes that engine thrust is increased in at least one engine and engine thrust is reduced from at least the other engine to maintain a constant total thrust when the ECS is in the second operating mode.
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公开(公告)号：US10294894B2
公开(公告)日：2019-05-21
申请号：US15450631
申请日：2017-03-06
发明人： Jayant Sabnis
摘要： 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 takeoff power conditions.
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