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公开(公告)号：US20170306840A1
公开(公告)日：2017-10-26
申请号：US15444808
申请日：2017-02-28
Applicant: United Technologies Corporation
CPC classification number: F02C3/06 , F02C3/04 , F02C7/36 , F02K3/02 , F02K3/04 , F02K3/06 , F02K3/072 , F05D2220/3215
Abstract: 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 performance quantity ratio between about 0.8 and about 1.5.
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公开(公告)号：US20170298833A1
公开(公告)日：2017-10-19
申请号：US15488580
申请日：2017-04-17
Applicant: United Technologies Corporation
Inventor： David P. Houston , Daniel Bernard Kupratis , Frederick M. Schwarz
CPC classification number: 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
Abstract: 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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公开(公告)号：US09752511B2
公开(公告)日：2017-09-05
申请号：US15484441
申请日：2017-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
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公开(公告)号：US20170122216A1
公开(公告)日：2017-05-04
申请号：US15395277
申请日：2016-12-30
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Frederick M. Schwarz
IPC: F02C7/36 , F02C3/04 , F02C9/18 , F01D9/02 , F04D29/32 , F04D27/00 , F02K1/78 , F02K3/06 , F01D5/06
CPC classification number: F02C7/36 , F01D5/06 , F01D9/02 , F01D9/065 , F02C3/04 , F02C3/107 , F02C3/36 , F02C7/06 , F02C9/18 , F02K1/78 , F02K3/04 , F02K3/06 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/12 , F05D2240/35 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , Y02T50/671
Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
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公开(公告)号：US20170089299A1
公开(公告)日：2017-03-30
申请号：US15383900
申请日：2016-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis , Francis R. Moon
Abstract: In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and a door operatively associated with the second and third air ducts of the gas turbine engine. The door may have at least an open position allowing air from the second air duct to flow into the third air duct and a closed position preventing air from flowing between the ducts.
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Patent Agency Ranking
66.发明申请CONTROL SYSTEM AND METHOD OF CONTROLLING A VARIABLE AREA GAS TURBINE ENGINE 审中-公开控制系统和控制可变区域燃气涡轮发动机的方法公开(公告)号：US20170074173A1
公开(公告)日：2017-03-16
申请号：US14851907
申请日：2015-09-11
Applicant: United Technologies Corporation
Inventor： Paul R. Hanrahan , Daniel Bernard Kupratis
IPC: F02C9/20
CPC classification number: F02C9/20 , F02C9/22 , F05D2270/708
Abstract: A method of controlling a variable area gas turbine engine includes, running the variable area turbine engine at initial settings, monitoring two sets of operating parameters of the engine at the initial settings, and deducing vane angles of adjustable vanes without directly measuring the vane angles from mapped data of the two sets of operating parameters of a similar engine operated while direct vane angle measurements were being recorded.
Abstract translation: 控制可变区域燃气轮机的方法包括：在初始设定时运行可变区域涡轮发动机，在初始设定时监测发动机的两组运行参数，并且在不直接测量叶片角度的情况下推导可调叶片的叶片角度 在记录直接叶片角度测量时操作的类似发动机的两组操作参数的映射数据。
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公开(公告)号：US20160258359A1
公开(公告)日：2016-09-08
申请号：US14635366
申请日：2015-03-02
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Anthony R. Bifulco
CPC classification number: F02C7/143 , F01D9/041 , F02C3/13 , F02C3/32 , F02C7/10 , F02C7/12 , F02C7/18 , F02C9/18 , F05D2220/32 , F05D2260/14 , F05D2260/205 , F05D2260/232 , F05D2260/601 , Y02T50/676
Abstract: A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages.
Abstract translation: 燃气涡轮发动机部分包括多个间隔开的转子级，在间隔开的转子级之间具有静态导向叶片。 静态导向叶片向通向下游一个间隔开的转子级的空气提供涡流，以及围绕间隔开的转子级的外壳。 分流器将空气的一部分径向向外转移穿过外部壳体，并穿过至少一个热交换器。 转向的空气通过外部壳体径向向内返回到管道中，并且朝向下游的一个间隔开的转子级排出。
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公开(公告)号：US20160131084A1
公开(公告)日：2016-05-12
申请号：US14964607
申请日：2015-12-10
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Frederick M. Schwarz
CPC classification number: F02K3/06 , F02C3/107 , F02C7/36 , F05D2260/20 , F05D2260/40311 , F05D2300/40 , F05D2300/603 , F05D2300/606 , Y02T50/672 , Y02T50/676
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a compressor section including at least a first compressor section and a second compressor section. A power ratio is provided by the combination of the first compressor section and the second compressor section. A method of design a gas turbine engine is also disclosed.
Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括风扇部分和至少包括第一压缩机部分和第二压缩机部分的压缩机部分。 功率比由第一压缩机部和第二压缩机部的组合提供。 还公开了一种设计燃气涡轮发动机的方法。
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69.发明申请Combined Two Engine Cycle With At Least One Recuperated Cycle Engine For Rotor Drive 审中-公开组合两个发动机循环与至少一个循环发动机转子驱动公开(公告)号：US20160003144A1
公开(公告)日：2016-01-07
申请号：US14737633
申请日：2015-06-12
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis
CPC classification number: F02C6/02 , B64C27/14 , B64D35/08 , F01D13/003 , F01D15/12 , F02C3/145 , F02C6/18 , F02C7/10 , F02C7/32 , F02C7/36 , F05D2220/329 , F05D2260/40311 , F05D2260/532
Abstract: A drive architecture comprises a rotor and a gearbox for driving the rotor. A pair of input gears provides rotational drive to the gearbox. A first recuperative cycle engine drives one of the pair of gears and a second engine drives the other of the pair of gears. The first recuperative cycle engine and the second engine are both gas turbine engines. A power takeoff from a drive shaft of the second engine supplies rotational drive to drive at least one component in the first recuperative cycle drive.
Abstract translation: 驱动架构包括用于驱动转子的转子和齿轮箱。 一对输入齿轮为齿轮箱提供旋转驱动。 第一恢复循环发动机驱动该对齿轮中的一个，第二发动机驱动该对齿轮中的另一个。 第一台换热循环发动机和第二台发动机都是燃气涡轮发动机。 来自第二发动机的驱动轴的动力输出提供旋转驱动以在第一换热循环驱动器中驱动至少一个部件。
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公开(公告)号：US20150192071A1
公开(公告)日：2015-07-09
申请号：US14662505
申请日：2015-03-19
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Frederick M. Schwarz
IPC: F02C7/32
CPC classification number: F02C7/36 , F02C3/107 , F02C3/113 , F02K3/04 , F02K3/06 , F02K3/062 , F02K3/065 , Y02T50/671
Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The fan drive turbine includes a plurality of turbine rotors. A fan includes a plurality of blades rotatable about an axis and a ratio between the number of fan blades and the number of fan drive turbine rotors is between about 2.5 and about 8.5. A speed change system is driven by the fan drive turbine for rotating the fan about the axis. The fan drive turbine has a first exit area at a first exit point and rotates at a first speed. The second turbine section has a second exit area at a second exit point and rotates at a second speed, which is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area. A performance ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5.
Abstract translation: 燃气涡轮发动机包括燃烧器。 涡轮机部分与燃烧器流体连通。 涡轮机部分包括风扇驱动涡轮机和第二涡轮机。 风扇驱动涡轮机包括多个涡轮转子。 风扇包括可围绕轴线旋转的多个叶片，并且风扇叶片数量与风扇驱动涡轮转子数量之间的比率在约2.5至约8.5之间。 变速系统由风扇驱动涡轮驱动，用于围绕轴旋转风扇。 风扇驱动涡轮机具有在第一出口处的第一出口区域并以第一速度旋转。 第二涡轮部分在第二出口处具有第二出口区域，并以比第一速度快的第二速度旋转。 第一性能数量被定义为第一速度平方和第一区域的乘积。 第二性能量被定义为第二速度平方和第二区域的乘积。 第一性能量与第二性能量的性能比为约0.5至约1.5。
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