公开(公告)号：WO2013154649A3

公开(公告)日：2014-03-20

申请号：PCT/US2013022388

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  ACKERMANN WILLIAM K ,  KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/02

CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F05D2220/323 ,  F05D2250/44

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.

Abstract translation: 燃气涡轮发动机包括非常高速的低压涡轮机，使得由低压涡轮机的出口面积所规定的数量乘以低压涡轮转速的平方，与高压涡轮机的相同参数相比是在 在约0.5和约1.5之间。

公开(公告)号：WO2014007897A3

公开(公告)日：2015-01-08

申请号：PCT/US2013034539

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/04

CPC classification number: F01D1/24 ,  F01D15/12 ,  F02C3/067 ,  F02C3/107 ,  F02C7/36 ,  F05D2250/44 ,  F05D2260/4031

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool rotating in the same direction as the intermediate speed spool. The fan drive turbine rotates in an opposed direction as the intermediate speed spool.

Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮驱动风扇通过齿轮减速。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 高速卷轴以与中间速度卷轴相同的方向旋转。 风扇驱动涡轮机以与中间速度卷轴相反的方向旋转。

公开(公告)号：WO2013169316A3

公开(公告)日：2014-01-16

申请号：PCT/US2013023559

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02K3/06

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.

Abstract translation: 燃气涡轮发动机通常包括风扇部分，压缩机部分，燃烧器部分和涡轮部分。 可以使用诸如行星齿轮组件的减速装置来驱动风扇部分，使得风扇部分可以以不同于涡轮部分的速度旋转，以便增加发动机的整体推进效率。 在这样的发动机结构中，由一个涡轮机部分驱动的轴为行星齿轮组件提供输入，该输入齿轮组件以不同于涡轮机部分的速度驱动风扇部分，使得涡轮机部分和风扇部分可以更接近 最佳速度通过所述和所公开的燃气涡轮发动机的各种部件的公开特征的期望组合来提供增加的性能属性和性能。

公开(公告)号：WO2014105237A3

公开(公告)日：2014-08-21

申请号：PCT/US2013061927

申请日：2013-09-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  KOHLENBERG GREGORY A

IPC: F02C9/16 ,  F02C3/04 ,  F02C7/20 ,  F02K3/06

CPC classification number: F02K3/075 ,  F01D21/045 ,  F02C7/32 ,  F02K1/04 ,  F05D2260/30 ,  F05D2260/311 ,  Y10T29/49245

Abstract: A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle including a primary outer diameter at a primary nozzle trailing edge and a primary maximum inner diameter forward of the primary trailing edge. A bypass passage a secondary nozzle that includes an outer diameter at a secondary nozzle trailing edge and a secondary maximum inner diameter forward of the secondary trailing edge. A ratio between the maximum inner diameter of the primary nozzle and an outer diameter at the trailing edge of the primary nozzle and a ratio between the maximum inner diameter of the secondary trailing edge and the outer diameter at the trailing edge of the secondary nozzle are both less than about 0.700.

Abstract translation: 所公开的示例齿轮涡轮风扇发动机包括风扇部分，该风扇部分包括围绕轴线可旋转的多个风扇叶片和围绕发动机轴线限定的核心发动机部分。 核心发动机部分包括主喷嘴，该主喷嘴包括在主喷嘴后缘处的主外径和在主后缘的前方的主最大内径。 旁通通道是次级喷嘴，其包括次级喷嘴后缘处的外径和次级后缘前方的次级最大内径。 主喷嘴的最大内径与主喷嘴的后缘处的外径之间的比率以及次级后缘的最大内径与次级喷嘴的后缘处的外径之间的比率都是 小于约0.700。

公开(公告)号：WO2014011252A3

公开(公告)日：2014-03-13

申请号：PCT/US2013033962

申请日：2013-03-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDRICK M

IPC: F02C7/36

CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2260/40311

Abstract: A gas turbine engine includes first and second shafts rotatable about a common axis. The gas turbine engine includes a fan, and first and second gear trains interconnected to one another and coupling the first shaft to fan.

Abstract translation: 燃气涡轮发动机包括围绕公共轴线旋转的第一和第二轴。 燃气涡轮发动机包括风扇，以及彼此互连并将第一轴联接到风扇的第一和第二齿轮系。

公开(公告)号：WO2014018142A2

公开(公告)日：2014-01-30

申请号：PCT/US2013037675

申请日：2013-04-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD ,  MERRY BRIAN D ,  ACKERMANN WILLIAM K

CPC classification number: F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02K3/06

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. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

Abstract translation: 燃气涡轮发动机包括超高速低压涡轮机，使得与低压涡轮机的相同参数相比，由低压涡轮机的出口面积乘以低压涡轮机转速的平方所确定的量处于 比率在约0.5和约1.5之间。 高压涡轮机由位于第一轴连接到承载与第二涡轮机部分相关联的涡轮机转子的轮毂的点处的轴承支撑。

公开(公告)号：WO2015112212A2

公开(公告)日：2015-07-30

申请号：PCT/US2014062764

申请日：2014-10-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： KUPRATIS DANIEL BERNARD ,  SCHWARZ FREDERICK M

IPC: F02C3/107 ,  F02C7/36

CPC classification number: F02C3/107 ,  F01D5/187 ,  F05D2300/606 ,  Y02T50/672 ,  Y02T50/676

Abstract: A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second compressor section and a fan drive turbine driving at least a gear arrangement to drive the fan section. A power ratio is provided by the combination of the first compressor section and the second compressor section, with the power ratio being provided by a first power input to the first compressor section and a second power input to the second compressor section, the power ratio being equal to, or greater than, about 1.0 and less than, or equal to, about 1.4.

Abstract translation: 燃气涡轮发动机包括风扇部分和压缩机部分。 压缩机部分包括第一压缩机部分和第二压缩机部分两者。 涡轮机部分包括至少一个涡轮机并且驱动第二压缩机部分，并且风扇驱动涡轮机驱动至少一个齿轮装置以驱动风扇部分。 功率比由第一压缩机部分和第二压缩机部分的组合提供，功率比由输入到第一压缩机部分的第一功率和输入到第二压缩机部分的第二功率提供，功率比是 等于或大于约1.0且小于或等于约1.4。

公开(公告)号：WO2014007893A3

公开(公告)日：2014-02-27

申请号：PCT/US2013034324

申请日：2013-03-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D5/02 ,  F02C7/00

CPC classification number: F16J15/0887 ,  F01D15/12 ,  F02C3/067 ,  F02C7/36 ,  F02K3/072 ,  Y02T50/672

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool, with the high speed spool rotating in an opposed direction to the intermediate speed spool. The fan drive turbine rotates in the same direction as the intermediate speed spool.

Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩至比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二个涡轮驱动压缩机转子。 风扇驱动涡轮机定位在第二涡轮机转子的下游。 风扇驱动涡轮通过齿轮减速来驱动风扇。 第一压缩机转子和第二涡轮机转子作为中速卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速卷轴，高速卷轴沿与中速卷轴相反的方向旋转。 风扇驱动涡轮以与中速阀芯相同的方向旋转。

公开(公告)号：WO2013165512A3

公开(公告)日：2013-12-19

申请号：PCT/US2013025727

申请日：2013-02-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D17/16 ,  F02C7/042

CPC classification number: F01D17/162 ,  F02C9/22 ,  F05D2270/112 ,  F05D2270/3032

Abstract: A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.

Abstract translation: 燃气涡轮发动机包括轴和配置成驱动轴的涡轮。 涡轮机具有至少一个级，其包括散布有多个涡轮叶片的多个涡轮叶片。 所述多个叶片包括至少一个可变叶片，所述至少一个可变叶片可在关闭位置和减小气流的打开位置之间移动，以增加气流。 基于发动机限制条件来控制至少一个可变叶片的运动。

公开(公告)号：WO2014007896A3

公开(公告)日：2014-04-10

申请号：PCT/US2013034537

申请日：2013-03-29

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/04

CPC classification number: F02K3/075 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2260/40311

Abstract: A gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor. The second compressor rotor compresses air to a higher pressure than the first compressor rotor. A first turbine rotor drives the second compressor rotor and a second turbine rotor. The second turbine drives the compressor rotor. A fan drive turbine is positioned downstream of the second turbine rotor. The fan drive turbine drives the fan rotor through a gear reduction. The first compressor rotor and second turbine rotor rotate as an intermediate speed spool. The second compressor rotor and first turbine rotor together as a high speed spool. The high speed spool, the intermediate speed spool, and the fan drive turbine rotate in the same direction.

Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子。 第二压缩机转子将空气压缩到比第一压缩机转子更高的压力。 第一涡轮转子驱动第二压缩机转子和第二涡轮转子。 第二涡轮驱动压缩机转子。 风扇驱动涡轮机位于第二涡轮转子的下游。 风扇驱动涡轮通过齿轮减速器驱动风扇转子。 第一压缩机转子和第二涡轮机转子作为中间速度卷轴旋转。 第二压缩机转子和第一涡轮转子一起作为高速滑阀。 高速卷轴，中速卷轴和风扇驱动涡轮机沿相同方向旋转。