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71. 发明授权

US4790133A High bypass ratio counterrotating turbofan engine 失效
标题翻译：高旁路比逆转涡扇发动机
公开(公告)号：US4790133A
公开(公告)日：1988-12-13
申请号：US166749
申请日：1988-03-10
申请人： Alan R. Stuart
发明人： Alan R. Stuart
IPC分类号： F02C3/067 , F02K3/072
CPC分类号： F02C3/067 , F02K3/072
摘要： A gas turbine engine comprising a core gas generator engine for generating combustion gases, an additional power turbine, an additional fan section, and a booster compressor is disclosed. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively. The fan section includes a first fan blade row connected to the first drive shaft and a second fan blade row connected to the second drive shaft. The booster compressor includes a first compressor blade row connected to the first drive shaft and a second compressor blade row connected to the second drive shaft.
摘要翻译：公开了一种燃气涡轮发动机，其包括用于产生燃烧气体的核心气体发生器发动机，附加动力涡轮机，附加风扇部分和增压压缩机。动力涡轮机包括分别有效地旋转第一和第二驱动轴的第一和第二反向旋转涡轮叶片排。风扇部分包括连接到第一驱动轴的第一风扇叶片排和连接到第二驱动轴的第二风扇叶片排。增压压缩机包括连接到第一驱动轴的第一压缩机叶片排和连接到第二驱动轴的第二压缩机叶片排。

72. 发明授权

US4758129A Power frame 失效
标题翻译：电源框架
公开(公告)号：US4758129A
公开(公告)日：1988-07-19
申请号：US739804
申请日：1985-05-31
申请人： William J. Strock , Ambrose A. Hauser
发明人： William J. Strock , Ambrose A. Hauser
IPC分类号： F01D1/24 , F01D5/02 , F01D5/06 , F01D5/18 , F01D7/00 , F01D9/06 , F02K3/072 , F02C3/04
CPC分类号： F01D5/18 , F01D5/02 , F01D7/00 , F01D9/065 , F02K3/072 , F05D2260/74 , F05D2260/76 , Y02T50/676
摘要： A rotor stage disposed within an annular fluid flowpath in a turbomachine is disclosed. The rotor stage includes outer and inner rings and a plurality of first and second airfoils. The outer and inner rings define flowpath surfaces for said flowpath. The first and second airfoils extend between the rings for transferring energy between the fluid and the rotor stage. At least one of the first airfoils surrounds means for transmitting energy across the flowpath.
摘要翻译：公开了一种设置在涡轮机中的环形流体流路内的转子级。转子级包括外圈和内圈以及多个第一和第二翼型件。外圈和内圈限定所述流路的流路面。第一和第二翼型件在环之间延伸以在流体和转子级之间传递能量。第一翼型中的至少一个围绕用于在流动路径上传递能量的装置。

73. 发明授权

US2416389A Torque balancing of jet propulsion turbine plant 失效
标题翻译：喷气推进涡轮机厂的扭矩平衡
公开(公告)号：US2416389A
公开(公告)日：1947-02-25
申请号：US49552543
申请日：1943-07-20
申请人： ARMSTRONG SIDDELEY MOTORS LTD
发明人： MAX HEPPNER FRITZ ALBERT , DENIS VOCE JOHN , RHYS EVANS DAVID
IPC分类号： F02C3/067 , F02K3/072
CPC分类号： F02C3/067 , F02K3/072

74. 发明申请

US20180231016A1 Thrust-Ring and Rotor Fan System 审中-公开
公开(公告)号：US20180231016A1
公开(公告)日：2018-08-16
申请号：US15338035
申请日：2016-10-28
申请人： Rolls-Royce Corporation
发明人： Bronwyn Power , Jonathan M. Rivers
IPC分类号： F04D29/28 , F04D29/34 , B64C11/06 , B63H1/16 , B23K101/00 , F04D29/32 , B64C11/00
CPC分类号： F04D29/282 , B23K2101/001 , B63H1/16 , B64C11/001 , B64C11/06 , B64C2201/162 , B64C2201/165 , B64D2027/005 , F01D5/143 , F01D5/225 , F02C9/58 , F02K3/04 , F02K3/072 , F04D29/326 , F04D29/329 , F04D29/34 , F05D2220/323 , F05D2220/326 , F05D2220/327 , F05D2220/36
摘要： A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees, more preferably between about 5 degrees and about 30 degrees. Optionally, an outlet guide vane may be mounted rearward of the one or more rotors having a ring airfoil.

75. 发明申请

US20180209335A1 INTERDIGITATED COUNTER ROTATING TURBINE SYSTEM AND METHOD OF OPERATION 审中-公开
公开(公告)号：US20180209335A1
公开(公告)日：2018-07-26
申请号：US15412197
申请日：2017-01-23
申请人： General Electric Company
发明人： Alan Roy Stuart , Jeffrey Donald Clements , Richard Schmidt , Thomas Ory Moniz
IPC分类号： F02C3/04 , F02C7/36 , F02K3/06
CPC分类号： F02C3/04 , F02C3/067 , F02C7/36 , F02K3/06 , F02K3/072 , F05D2220/32 , F05D2260/40311
摘要： The present disclosure is directed to a method of operating a gas turbine engine with an interdigitated turbine section. The engine includes a fan rotor, an intermediate pressure compressor, a high pressure compressor, a combustion section, and a turbine section in serial flow arrangement. The turbine section includes, in serial flow arrangement, a first stage of a low speed turbine rotor, a high speed turbine rotor, a second stage of the low speed turbine rotor, an intermediate speed turbine rotor, and one or more additional stages of the low speed turbine rotor. The low speed turbine rotor is coupled to the fan rotor via a low pressure shaft. The intermediate speed turbine rotor is coupled to the intermediate pressure compressor via an intermediate pressure shaft. The high speed turbine rotor is coupled to the high pressure compressor via a high pressure shaft. The method includes rotating the low speed turbine rotor in a first direction along the circumferential direction; rotating the high speed turbine rotor in a second direction opposite of the first direction along the circumferential direction; and rotating the intermediate speed turbine rotor in the second direction.

76. 发明申请

US20180209294A1 AIRCRAFT COMPRISING A TURBINE ENGINE INCORPORATED INTO THE REAR FUSELAGE WITH VARIABLE SUPPLY 审中-公开
公开(公告)号：US20180209294A1
公开(公告)日：2018-07-26
申请号：US15745704
申请日：2016-07-21
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Francois GALLET , Nicolas Jerome Jean TANTOT
IPC分类号： F01D17/14 , B64D27/20 , F02K3/072 , F02K3/12 , F01D17/16
CPC分类号： F01D17/141 , B64C11/48 , B64D27/14 , B64D27/20 , F01D1/023 , F01D1/24 , F01D17/105 , F01D17/14 , F01D17/145 , F01D17/148 , F01D17/16 , F01D17/162 , F01D17/167 , F02C3/10 , F02K1/52 , F02K3/072 , F02K3/075 , F02K3/077 , F02K3/12 , F05D2220/323 , F05D2240/128 , F05D2260/606 , F05D2270/093 , F05D2270/102
摘要： The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).

77. 发明申请

US20170370285A1 GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION 审中-公开
公开(公告)号：US20170370285A1
公开(公告)日：2017-12-28
申请号：US15682848
申请日：2017-08-22
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Frederick M. Schwarz , William K. Ackermann , Daniel Bernard Kupratis
IPC分类号： F02C3/113 , F02C3/06 , F02K3/06 , F02C7/36 , F02C9/16
CPC分类号： F02C3/113 , F02C3/06 , F02C7/36 , F02C9/16 , F02K3/06 , F02K3/072 , F05D2200/221 , F05D2220/3215 , F05D2220/323 , F05D2260/40311 , F05D2270/20
摘要： A compressor section is in fluid communication with a fan, which includes a first compressor section and a second compressor section. A turbine section includes a first turbine section driving the fan and the first compressor section and a second turbine section driving the second compressor section and the second compressor rotor. A first performance quantity is defined as a product of the first speed squared and the first area. A second performance quantity is defined as a product of the second speed squared and the second exit area. A performance ratio of the first performance quantity to the second performance quantity is between about 0.2 and about 0.8. A gear reduction is included between the first turbine section and the first compressor section.

78. 发明授权

US09850821B2 Gas turbine engine with fan-tied inducer section 有权
公开(公告)号：US09850821B2
公开(公告)日：2017-12-26
申请号：US14788913
申请日：2015-07-01
申请人： United Technologies Corporation
发明人： Daniel Bernard Kupratis , Frederick M. Schwarz
IPC分类号： F02C7/36 , F02C7/042 , F02C7/047 , F02K3/072
CPC分类号： F02C7/36 , F02C7/042 , F02C7/047 , F02K3/072 , F05D2230/51 , F05D2260/40311
摘要： A gas turbine engine includes a shaft, a speed reduction device driven by the shaft, and a fan including a fan rotor driven by the speed reduction device. A compressor section has a plurality of compressor stages driven by the shaft. At least one inducer stage is positioned aft of the fan and coupled for rotation with the fan rotor. The at least one inducer stage is positioned upstream of the compressor section.

79. 发明授权

US09845726B2 Gas turbine engine with high speed low pressure turbine section 有权
公开(公告)号：US09845726B2
公开(公告)日：2017-12-19
申请号：US14568167
申请日：2014-12-12
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Frederick M. Schwarz , William K. Ackermann , Daniel Bernard Kupratis
IPC分类号： F02C3/06 , F02C7/36 , F02K3/02 , F02K3/06 , F02C3/04 , F02K3/04 , F02K3/072
CPC分类号： F02C3/06 , F02C3/04 , F02C7/36 , F02K3/02 , F02K3/04 , F02K3/06 , F02K3/072 , F05D2220/3215
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

80. 发明申请

US20170298834A1 GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE 审中-公开
公开(公告)号：US20170298834A1
公开(公告)日：2017-10-19
申请号：US15488630
申请日：2017-04-17
申请人： United Technologies Corporation
发明人： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
IPC分类号： F02C7/36 , F01D5/02 , F02K3/072 , F01D25/16 , F02C7/06
CPC分类号： F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

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