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公开(公告)号：US20220403774A1
公开(公告)日：2022-12-22
申请号：US17716290
申请日：2022-04-08
摘要： A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.
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公开(公告)号：US11174781B2
公开(公告)日：2021-11-16
申请号：US15764864
申请日：2016-10-05
发明人： Laurent Soulat , Kevin Morgane Lemarchand , Tewfik Boudebiza , Gilles Alain Charier , Nathalie Nowakowski , Augustin Marc Michel Curlier , Adrien Pierre Jean Pertat , Pierre-Alain Jean Philippe Reigner
IPC分类号： F02C3/10 , B64D27/12 , B64D35/04 , F02K3/062 , F01D15/12 , F02C3/107 , F02C7/36 , F02K3/06 , B64D27/18 , B64D27/26
摘要： The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY′) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.
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公开(公告)号：US11142330B2
公开(公告)日：2021-10-12
申请号：US16117305
申请日：2018-08-30
IPC分类号： B64D35/00 , B64D27/14 , B64C21/00 , B64D33/04 , F16H1/22 , F16H37/06 , B64C1/16 , B64C21/06 , F02K3/062
摘要： An aircraft with an integrated boundary layer ingesting propulsion having a mechanically-distributed propulsion system. The mechanically-distributed propulsion system may include an engine to generate a mechanical drive power, a drive shaft, a direction-reversing transmission, and a propulsor fan. The drive shaft may be operatively coupled to the engine to receive the mechanical drive power. The direction-reversing transmission may have a first rotating shaft and a second rotating shaft, the first rotating shaft operatively coupled to the drive shaft to receive the mechanical drive power, which is configured to redirect the mechanical drive power received at the first rotating shaft from a first direction to face a second direction at the second rotating shaft. The propulsor fan may be coupled to the second rotating shaft to convert the mechanical drive power into thrust.
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公开(公告)号：US10557415B2
公开(公告)日：2020-02-11
申请号：US15088525
申请日：2016-04-01
发明人： Tewfik Boudebiza , Gilles Alain Charier , Augustin Marc Michel Curlier , Jean-Christophe Duffet
摘要： A non-faired propeller turbo-engine includes a gas generator and a propulsion unit that is separated from the gas generator by an intermediate housing. The turbo-engine includes a housing and a radially internal ferrule that are coaxial and are connected by hollow radial arms. The housing of the turbo-engine also defines, in part, a gas flow duct of a secondary gas flow. Each radial arm is hollow and is traversed by at least one service of the turbo-engine. Additionally, at least one arm is traversed by a ventilation gas circulation duct from the secondary gas flow and which leads to at least one component from among a power turbine and a mechanical transmission of said propulsion unit.
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公开(公告)号：US09970386B2
公开(公告)日：2018-05-15
申请号：US14298331
申请日：2014-06-06
发明人： Lubomir A. Ribarov , James S. Elder
CPC分类号： F02K1/48 , B64D33/04 , B64D2027/005 , F02K1/386 , F02K3/062 , F05D2240/127 , F05D2260/2212 , Y02T50/672
摘要： An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.
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公开(公告)号：US20170082022A1
公开(公告)日：2017-03-23
申请号：US14508898
申请日：2014-10-07
申请人： Brent LEE
发明人： Brent LEE
CPC分类号： F02C3/26 , F01D25/30 , F02C3/04 , F02C3/165 , F02C7/04 , F02C7/222 , F02C7/264 , F02K3/062 , F05D2210/13 , F05D2220/30 , F05D2220/75 , F05D2240/35 , Y02T50/671
摘要： An engine, a biomass powder energy conversion and/or generation system, hybrid turbine engines, and methods of manufacturing and using the same are disclosed. The engine includes a housing having an inner wall and an outer wall, a central rotary shaft extending from the housing, at least one fuel and air supply channel having a first portion extending radially from the rotary shaft and a second portion in fluidic communication with first portion of the fuel and air supply channel, at least two propulsion vessels, each propulsion vessel connected to the at least one of the fuel and air supply channel and configured to burn or detonate the fuel and rotate around the central rotary shaft; and at least one exhaust duct extending from the housing.
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公开(公告)号：US09016041B2
公开(公告)日：2015-04-28
申请号：US12956674
申请日：2010-11-30
摘要： A gas turbine engine includes: a front fan having at least one rotor carrying fan blades disposed within a fan duct, and drivingly connected to a low pressure turbine, the front fan including at least one row of outer fan blades disposed outwardly of and connected to the fan blades, the outer fan blades extending across an outer bypass duct which circumscribes the fan duct; a core engine located between the front fan and the low pressure turbine; an aft fan disposed downstream of the low pressure turbine, having at least one rotor carrying aft turbine blades disposed within an aft turbine duct, the aft turbine further including at least one row of aft fan blades disposed outwardly of and connected to the aft turbine blades, and extending across an aft fan duct that surrounds the core engine; and apparatus operable to selectively throttle flow through the outer bypass duct.
摘要翻译： 燃气涡轮发动机包括：前风扇，其具有至少一个承载风扇叶片的转子，风扇叶片设置在风扇管道内，并且驱动地连接到低压涡轮机，所述前风扇包括至少一排外风扇叶片，所述外风扇叶片设置在外部并连接到 风扇叶片，外风扇叶片延伸穿过外部旁路管道，外部旁路管道外围风扇管道; 位于前风扇和低压汽轮机之间的核心发动机; 设置在所述低压涡轮机下游的后风扇，具有至少一个转子，所述至少一个转子承载设置在后涡轮机管道内的后涡轮机叶片，所述后涡轮机还包括设置在所述后涡轮机叶片外侧并连接到所述后涡轮叶片的至少一排后翼扇叶片 并且延伸穿过围绕所述核心发动机的后部风扇管道; 以及可操作以选择性地调节通过外部旁路管道的流动的装置。
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公开(公告)号：US20050155343A1
公开(公告)日：2005-07-21
申请号：US10760805
申请日：2004-01-20
申请人： Srinivasa Gowda , Kevin Early , Steven Martens
发明人： Srinivasa Gowda , Kevin Early , Steven Martens
CPC分类号： F02K1/48 , F05D2300/505
摘要： A method of assembling a gas turbine engine includes coupling an annular exhaust duct to the gas turbine engine, coupling a plurality of chevrons to the annular exhaust duct, and coupling a chevron actuation system to the annular exhaust duct such that selective operation of the chevron actuation system repositions the plurality of chevrons to adjust an amount convergence of the annular exhaust duct.
摘要翻译： 一种组装燃气涡轮发动机的方法包括将环形排气管连接到燃气涡轮发动机，将多个人字形连接到环形排气管，以及将人字形致动系统耦合到环形排气管，使得人字形操纵 系统重新定位多个人字形以调节环形排气管的收敛量。
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公开(公告)号：US4934139A
公开(公告)日：1990-06-19
申请号：US405052
申请日：1989-09-08
CPC分类号： F02C7/04 , F02K3/062 , Y02T50/671 , Y10T137/0536
摘要： The present invention relates to turbofan gas turbine engines. In conventional high bypass ratio turbofans the large variations in the free air stream flowing into the fan duct inlet is accommodated by a thick lip and a long, thick fan casing to prevent air flow separation from the outer surface of the fan casing, but produces a heavy fan casing and large drag values. In the invention a turbofan comprises a core engine which has a core casing, and a fan assembly positioned downstream of the core engine. The fans operate in a fan duct defined by the fan casing. The core casing has an external form upstream of the fan duct inlet which affects the airflow streamlines flowing into the fan duct inlet to cause it to adopt a flow path which is near alignment with the length of the fan casing to reduce fan casing weight, length and drag.
摘要翻译： 本发明涉及涡轮风扇燃气涡轮发动机。 在传统的高旁通比涡轮风扇中，流入风扇管道入口的自由空气流的大变化由厚的唇缘和长而厚的风扇壳体容纳，以防止气流从风扇外壳的外表面分离，但产生 重型风扇外壳和大阻力值。 在本发明中，涡轮风扇包括具有芯壳的核心发动机和位于核心发动机下游的风扇组件。 风扇在由风扇外壳限定的风扇风扇中工作。 芯壳体具有在风扇管道入口上游的外部形式，其影响流入风扇管道入口的气流流线，以使其采用与风扇壳体的长度近似对准的流动路径，以减小风扇壳体重量，长度 并拖动。
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公开(公告)号：US4826403A
公开(公告)日：1989-05-02
申请号：US49409
申请日：1987-05-14
申请人： Ronald Catlow
发明人： Ronald Catlow
CPC分类号： F01D21/045 , F01D5/03 , F02C3/067 , F02K3/072 , Y02T50/673
摘要： A power turbine (12) comprises alternate annular arrays of contra-rotatable turbine blades. Two arrays of turbine blades (30) and (47) have annular arrays of aerofoil propulsion blades (17,18) respectively attached thereto. Alternate arrays of turbine blades are attached to a primary drum member (55) in such a manner that below normal operating temperatures, limited relative radial movement is permitted between them. However when the normal operating temperature is reached, the relative radial movement is inhibited in such a manner that the rigidity of the power turbine (12) enhanced.
摘要翻译： 动力涡轮机（12）包括可逆转的涡轮叶片的交替的环形阵列。 涡轮机叶片（30）和（47）的两个阵列具有分别连接到其上的机翼推进叶片（17,18）的环形阵列。 涡轮叶片的替代阵列以这样的方式附接到主鼓构件（55），使得在其之间允许有限的相对径向移动。 然而，当达到正常工作温度时，以增加动力涡轮机（12）的刚性的方式抑制相对径向运动。
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