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1. 发明申请

US20160245162A1 COMPOUND ENGINE ASSEMBLY WITH OFFSET TURBINE SHAFT, ENGINE SHAFT AND INLET DUCT 审中-公开
标题翻译：复合发动机组件与偏置涡轮轴，发动机轴和入口导管
公开(公告)号：US20160245162A1
公开(公告)日：2016-08-25
申请号：US14864096
申请日：2015-09-24
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sylvain LAMARRE , Mike FONTAINE , Andre JULIEN , Michael GAUL , Jean THOMASSIN , Lazar MITROVIC , Ilya B. MEDVEDEV , Sergey USIKOV , Andrey ZOLOTOV
IPC分类号： F02B41/00 , F01C11/00 , F02C7/36 , F01C21/18 , F01C1/22
CPC分类号： F02B41/00 , F01C1/22 , F01C11/008 , F01C21/18 , F02C6/12 , F02C6/206 , F02C7/052 , F02C7/36 , F05B2220/40 , F05D2220/323 , F05D2230/51 , F05D2230/72 , F05D2250/312 , F05D2260/4031 , F05D2300/121 , F05D2300/171
摘要： A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.
摘要翻译：具有入口管道，压缩机，包括至少一个内燃机的发动机核心的复合发动机组件和包括被配置为与发动机轴组合动力的涡轮轴的涡轮部分。涡轮机部分可以包括第一级涡轮机和第二级涡轮机。涡轮轴和发动机轴彼此平行。涡轮机轴，发动机轴和入口管道的至少一部分都相互径向偏移。还讨论了驱动飞行器的可旋转载荷的方法。

2. 发明申请

US20140260295A1 GAS TURBINE ENGINE WITH TRANSMISSION AND METHOD OF ADJUSTING ROTATIONAL SPEED 有权
标题翻译：具有变速器的气体涡轮发动机和调整转速的方法
公开(公告)号：US20140260295A1
公开(公告)日：2014-09-18
申请号：US13804799
申请日：2013-03-14
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Richard ULLYOTT , Lazar MITROVIC , Jean DUBREUIL , Stephen Christopher KENNY , Guy BOUCHARD , Ilya B. MEDVEDEV , Keith MORGAN , Daris Jehangir KARANJIA , Nashed Azer YOUSSEF
IPC分类号： F02C3/113
CPC分类号： F02C3/113 , F02C3/107 , F02C7/36 , F02C9/56 , F05D2260/4031
摘要： A method of adjusting a rotational speed of the low pressure compressor rotor(s) of a gas turbine engine, including rotating the high pressure compressor rotor(s) with the high pressure turbine rotor(s) through the high pressure spool, rotating the low pressure turbine rotor(s) with a flow of exhaust gases from the high pressure turbine, rotating the low pressure spool with the low pressure turbine rotor(s), rotating a load of the engine with the low pressure spool, driving a rotation of the low pressure compressor rotor(s) with the low pressure spool through a variable transmission defining a variable transmission ratio between rotational speeds of the compressor rotor(s) and the low pressure spool, and adjusting the transmission ratio to obtain a desired rotational speed for the low pressure compressor rotor(s). A method of adjusting rotational speeds of a gas turbine engine and a gas turbine engine are also described.
摘要翻译：一种调节燃气涡轮发动机的低压压缩机转子的转速的方法，包括通过高压阀芯与高压涡轮转子一起旋转高压压缩机转子，使低压来自高压涡轮机的废气流的高压涡轮机转子，用低压涡轮转子旋转低压阀芯，用低压阀芯旋转发动机的负载，驱动通过限定压缩机转子和低压阀芯的转速之间的可变传动比的可变传动装置与低压阀芯连接的低压压缩机转子，并且调整传动比以获得所需的转速低压压缩机转子。还描述了一种调节燃气涡轮发动机和燃气涡轮发动机的转速的方法。

3. 发明申请

US20210229796A1 PLANETARY GEARBOX FOR GAS TURBINE ENGINE 有权
公开(公告)号：US20210229796A1
公开(公告)日：2021-07-29
申请号：US16832785
申请日：2020-03-27
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Lazar MITROVIC
IPC分类号： B64C11/46 , F16H1/28 , F16H57/08 , F16H57/02 , B64D35/02 , F02C7/36
摘要： An aircraft includes first and second engines, one or more aircraft rotors associated with the first and second engines, a first epicyclic gearbox having: a) an output operatively connected at least one of the one or more aircraft rotors, and b) an input defined by a sun gear of the first epicyclic gearbox; and a second epicyclic gearbox having: a) an output operatively connected to at least one of the one or more aircraft rotors, and b) an input defined by a sun gear of the second epicyclic gearbox. Output of the first epicyclic gearbox is defined by the carrier. Output of the second epicyclic gearbox is defined by its ring gear. A multi-engine aircraft and a method of operating a multi-engine aircraft are also described.

4. 发明申请

US20200095942A1 MULTI-SPOOL GAS TURBINE ENGINE ARCHITECTURE 审中-公开
公开(公告)号：US20200095942A1
公开(公告)日：2020-03-26
申请号：US16583896
申请日：2019-09-26
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Eric DUROCHER , Keith MORGAN , Lazar MITROVIC , Jean DUBREUIL , Martin POULIN
IPC分类号： F02C7/32 , F02C6/20 , F02C3/10 , F02C3/14
摘要： A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.

5. 发明申请

US20160245156A1 ENGINE ASSEMBLY WITH MODULAR COMPRESSOR AND TURBINE 审中-公开
标题翻译：发动机组件与模块式压缩机和涡轮机
公开(公告)号：US20160245156A1
公开(公告)日：2016-08-25
申请号：US14864068
申请日：2015-09-24
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sylvain LAMARRE , Mike FONTAINE , Andre JULIEN , Michael GAUL , Jean THOMASSIN , Lazar MITROVIC , Ilya B. MEDVEDEV , Sergey USIKOV , Andrey ZOLOTOV
IPC分类号： F02B37/10 , F02B53/14 , F02B53/02 , B64D27/02 , F02B33/40
CPC分类号： F02B37/105 , B64D27/02 , F01C1/22 , F01C11/008 , F02B33/40 , F02B53/02 , F02B53/14 , F02B2053/005 , F02C6/12 , F02C6/206 , F02C7/36 , F05D2220/323 , F05D2220/40 , F05D2230/51 , F05D2230/72 , F05D2250/312 , F05D2260/4031 , F05D2300/121 , F05D2300/171
摘要： An engine assembly including an engine core with at least one internal combustion engine, a first casing, a turbine module including a second casing located outside of the first casing, and a compressor module including a third casing located outside of the first and second casings. The turbine shaft extends into the first casing, is rotationally supported by a bearings all contained within the first casing, and is free of rotational support within the second casing. The first casing may be a gearbox module casing through which the turbine shaft is in driving engagement with the engine shaft. A method of driving a rotatable load of an aircraft, and an engine assembly with a rotary engine core, a gearbox module with a first casing, and a second module including a second casing located outside of the first casing and detachably connected to the first casing are also discussed.
摘要翻译：一种发动机组件，包括具有至少一个内燃机的发动机芯，第一壳体，包括位于第一壳体外部的第二壳体的涡轮机模块，以及包括位于第一和第二壳体外部的第三壳体的压缩机模块。涡轮轴延伸到第一壳体中，由全部包含在第一壳体内的轴承旋转地支撑，并且在第二壳体内不具有旋转支撑。第一壳体可以是齿轮箱模块壳体，涡轮轴通过该外壳与发动机轴驱动接合。一种驱动飞行器的可旋转载荷的方法，以及具有旋转发动机芯的发动机组件，具有第一壳体的齿轮箱模块和包括位于第一壳体外部的第二壳体的第二模块，并且可拆卸地连接到第一壳体也被讨论。

6. 发明申请

US20140290265A1 GAS TURBINE ENGINE WITH TRANSMISSION 审中-公开
标题翻译：气体涡轮发动机与传动
公开(公告)号：US20140290265A1
公开(公告)日：2014-10-02
申请号：US13754304
申请日：2013-01-30
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Richard ULLYOTT , Keith MORGAN , Jean DUBREUIL , Lazar MITROVIC , Kevin A. DOOLEY , Stephen KENNY , Ilya MEDVEDEV , Johnny VINSKI
IPC分类号： F02C7/36
CPC分类号： F02C7/36 , F02C3/113 , F05D2220/324 , F05D2220/327
摘要： A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g. connected to a compressor rotor) is engaged to the driving member. First and second power transfer devices are engaged to the first spool and the selectively rotatable member, respectively. A circuit interconnects the power transfer devices and allows a power transfer therebetween, and a control unit controls the power being transferred between the power transfer devices. Power can thus be transferred between the first spool and the selectively rotatable member to change the speed ratio between the first spool and the rotatable shaft.
摘要翻译：具有差速器的多线轴燃气涡轮发动机具有可选择性地旋转的构件，其转速确定差速器的驱动和驱动构件的转速之间的可变比。被驱动构件接合到第一卷轴，并且与其它卷轴（例如，连接到压缩机转子）无关的可旋转轴接合到驱动构件。第一和第二动力传递装置分别接合到第一卷轴和可选择性旋转的构件。电路将功率传输装置互连并允许它们之间的电力传输，并且控制单元控制在功率传输装置之间传输的功率。因此能够在第一卷轴和可选择性地旋转的构件之间传递动力，以改变第一卷轴和可旋转轴之间的速比。

7. 发明申请

US20210123507A1 PLANETARY GEAR ASSEMBLY AND METHOD OF OPERATING SAME 有权
公开(公告)号：US20210123507A1
公开(公告)日：2021-04-29
申请号：US16682596
申请日：2019-11-13
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Lazar MITROVIC
IPC分类号： F16H1/36 , F16H57/08 , B64D35/02 , F02C7/36
摘要： A carrier assembly for a planetary gear assembly includes a planet frame defining a central aperture therethrough, the central aperture defining a rotation axis, the planet frame configured to rotatably support a plurality of planet gears, and a carrier connected to the planet frame via a stud. At least one of a portion of the carrier proximate the stud and a portion of the stud between the carrier and the planet frame has a dimension reduction, such as a thickness reduction, therein.

8. 发明申请

US20180179948A1 COMPOUND ENGINE ASSEMBLY WITH CANTILEVERED COMPRESSOR AND TURBINE 审中-公开
公开(公告)号：US20180179948A1
公开(公告)日：2018-06-28
申请号：US15849977
申请日：2017-12-21
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sylvain LAMARRE , Mike FONTAINE , Andre JULIEN , Michael GAUL , Jean THOMASSIN , Lazar MITROVIC
IPC分类号： F02B41/10 , F02C6/20 , F01C11/00 , F01C13/04 , F01C21/00 , F01D25/16 , F02B53/02 , F02B53/10 , F02C6/12 , F01C1/22 , F02C7/36 , F02B53/00
摘要： A compound engine assembly with an engine core including at least one internal combustion engine, a compressor, and a turbine section where the turbine shaft is configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft is rotationally supported by a plurality of bearings all located on a same side of the compressor rotor(s) and all located on a same side of the turbine rotor(s), for example all located between the compressor rotor(s) and the turbine rotor(s), such that the compressor rotor(s) and the turbine rotor(s) are cantilevered. A method of driving a rotatable load of an aircraft is also discussed.

9. 发明申请

US20160245170A1 COMPOUND ENGINE ASSEMBLY WITH MOUNT CAGE 审中-公开
标题翻译：复合发动机总成与安装笼
公开(公告)号：US20160245170A1
公开(公告)日：2016-08-25
申请号：US14864124
申请日：2015-09-24
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Sylvain LAMARRE , Mike FONTAINE , Andre JULIEN , Michael GAUL , Jean THOMASSIN , Lazar MITROVIC , Ilya B. MEDVEDEV , Sergey USIKOV , Andrey ZOLOTOV
IPC分类号： F02C3/10 , F01C11/00 , F02C7/36 , F02B37/00
CPC分类号： F02C7/36 , F01C1/22 , F01C11/008 , F02B33/34 , F02B41/10 , F02B53/00 , F02B61/04 , F02B2053/005 , F02C6/12 , F02C6/206 , F02C7/32 , F05B2220/40 , Y02T10/163 , Y02T10/17
摘要： A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, the compressor and the engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and the engine core. The mount cage includes a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and engine core being located outside of the axial space.
摘要翻译：具有包括至少一个内燃机，涡轮部分和具有与发动机芯的入口流体连通的出口的压缩机的发动机芯的复合发动机组件。壳体连接到涡轮部分，压缩机和发动机核心。安装架连接到附接到壳体之间的安装件，压缩机与包括涡轮部分和发动机芯部的热区域之间。安装架包括从支架远离涡轮部分和发动机芯部延伸的多个支柱。壳体可以是齿轮箱模块壳体，涡轮轴通过该外壳与发动机轴接合。安装架可以完全容纳在轴向空间内，涡轮部分和发动机芯位于轴向空间的外部。

10. 发明申请

US20160229549A1 APPARATUS AND METHODS FOR POWERING AN ELECTRICAL DEVICE ASSOCIATED WITH AN AIRCRAFT ROTOR TECHNICAL FIELD 有权
标题翻译：用于为与飞机转子相关的电气设备供电的装置和方法技术领域
公开(公告)号：US20160229549A1
公开(公告)日：2016-08-11
申请号：US14338711
申请日：2014-07-23
申请人： Pratt & Whitney Canada. Corp.
发明人： Lazar MITROVIC , Richard ULLYOTT
IPC分类号： B64D41/00 , B64C11/44 , F02C7/32 , B64D27/10 , F16H3/66 , B64C11/02 , B64D15/12
CPC分类号： B64D41/00 , B64C11/02 , B64C11/44 , B64D15/12 , B64D15/14 , B64D27/10 , F02C7/32 , F05D2260/40311 , F16H3/666
摘要： Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.
摘要翻译：公开了一种用于产生用于为由飞行器的燃气涡轮发动机驱动的叶片转子相关联的装置供电的装置和方法。该装置包括一个转子轴，该转子轴连接飞行器的叶片转子并通过减速齿轮系由发动机的涡轮轴驱动。增速传递装置具有与转子轴连接的输入端和用于输出高于在增速传递装置的输入端处接收的转子轴的转速的转速的输出。设置在叶片转子的轮毂中的发电机被耦合到增速功率传递装置的输出端，并被配置为产生与叶片转子相关联的装置的电力。

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