公开(公告)号：WO2014025441A2

公开(公告)日：2014-02-13

申请号：PCT/US2013041797

申请日：2013-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F02C3/06

CPC classification number: F02C3/113 ,  F02C7/36 ,  F02K3/02 ,  F02K3/06 ,  F02K3/075

Abstract: gas turbine engine has a fan rotor, a first compressor rotor and a second compressor rotor and three turbine sections. A fan drive drives the fan through a gear reduction. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. A second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed that 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 ratio of the first performance quantity to the second performance quantity is between about 0.5 and about 1.5.

Abstract translation: 燃气涡轮发动机具有风扇转子，第一压缩机转子和第二压缩机转子以及三个涡轮区段。 风扇驱动通过齿轮减速来驱动风扇。 风扇驱动涡轮部分在第一出口点处具有第一出口区域并且构造成以第一速度旋转。 第二涡轮机部分在第二出口点处具有第二出口区域并且构造成以比第一速度更快的第二速度旋转。 第一表现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比例在大约0.5和大约1.5之间。

公开(公告)号：WO2013165515A3

公开(公告)日：2014-01-23

申请号：PCT/US2013025802

申请日：2013-02-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D5/06 ,  F01D5/02 ,  F02C7/04

CPC classification number: F01D15/12 ,  F02C7/047 ,  F02C7/36 ,  F02K3/072 ,  F05D2260/40311

Abstract: A gas turbine engine includes a shaft, a speed change device driven by the shaft, and a fan including a fan rotor driven by the speed change device. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract translation: 燃气涡轮发动机包括轴，由轴驱动的变速装置和包括由变速装置驱动的风扇转子的风扇。 至少一个诱导器台被定位在风扇的后面，并被联接成与风扇转子一起旋转。

公开(公告)号：WO2013165521A3

公开(公告)日：2013-12-27

申请号：PCT/US2013026075

申请日：2013-02-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  KUPRATIS DANIEL BERNARD

IPC: F01D5/04 ,  F01D5/02 ,  F02C7/04

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

Abstract: A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract translation: 燃气涡轮发动机包括限定旋转轴线的第一轴和能够围绕旋转轴线旋转并相对于第一轴径向向外间隔开的第二轴。 变速机构由第二轴驱动。 风扇包括由变速机构驱动的风扇转子，使得风扇和第一轴以比第二轴更慢的速度旋转。 至少一个诱导器台被定位在风扇的后面，并被联接成与风扇转子一起旋转。

公开(公告)号：WO2015088619A2

公开(公告)日：2015-06-18

申请号：PCT/US2014057127

申请日：2014-09-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M

IPC: F02C3/107

CPC classification number: F02C3/107 ,  F01D5/142 ,  F02K3/06 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/40311 ,  Y02T50/671 ,  Y02T50/673

Abstract: A turbofan engine includes a fan section including a fan blade having a leading edge and hub to tip ratio of less than about 0.34 and greater than about 0.020 measured at the leading edge and a speed change mechanism with gear ratio greater than about 2.6 to 1. A first compression section includes a last blade trailing edge radial tip length that is greater than about 67% of the radial tip length of a leading edge of a first stage of the first compression section. A second compression section includes a last blade trailing edge radial tip length that is greater than about 57% of a radial tip length of a leading edge of a first stage of the first compression section.

Abstract translation: 涡轮风扇发动机包括风扇部分，风扇部分包括风扇叶片，风扇叶片具有在前缘处测量的小于大约0.34且大于大约0.020的前缘和毂到尖端比率以及具有大于大约2.6比1的齿轮比的变速机构。 第一压缩区段包括最终叶片后缘径向末端长度，该长度大于第一压缩区段的第一级的前缘的径向末端长度的约67％。 第二压缩区段包括最终叶片后缘径向末端长度，该长度大于第一压缩区段的第一级的前缘的径向末端长度的约57％。

公开(公告)号：WO2014055113A9

公开(公告)日：2015-04-09

申请号：PCT/US2013029321

申请日：2013-03-06

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  BIFULCO ANTHONY R

IPC: F02K3/06 ,  F02C3/04 ,  F02C7/04 ,  F02C7/36

CPC classification number: F02C7/36 ,  F01D5/14 ,  F01D5/282 ,  F02C3/10 ,  F02K3/06 ,  F05D2220/36 ,  F05D2260/403 ,  F05D2300/121 ,  F05D2300/603 ,  Y02T50/672 ,  Y10T29/49321

Abstract: A gas turbine engine includes a fan rotating structure including a plurality of fan blades supported on a hub that defines a frontal area. A turbine section drives the fan through a geared architecture about the axis. The fan rotating structure includes a weight of the fan rotating structure relative to the frontal area that enables improvements in engine operating and propulsive efficiencies.

Abstract translation: 燃气涡轮发动机包括风扇旋转结构，其包括支撑在限定正面区域的轮毂上的多个风扇叶片。 涡轮机部分通过围绕轴的齿轮架构驱动风扇。 风扇旋转结构包括相对于前部区域的风扇旋转结构的重量，其能够改善发动机运行和推进效率。

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：WO2014099085A3

公开(公告)日：2014-09-18

申请号：PCT/US2013062104

申请日：2013-09-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BOMZER DAVID ,  SCHWARZ FREDERICK M

IPC: F01D5/14 ,  F02C7/00

CPC classification number: F01D25/28 ,  F02C7/20 ,  F02K3/06 ,  F05D2260/4031 ,  Y02T50/672

Abstract: A gas turbine engine includes a plurality of fan blades rotatable about an axis, wherein each of the plurality of fan blades includes a leading edge. The gas turbine engine also includes turbine section includes an aft most turbine blade having a trailing edge and a geared architecture driven by the turbine section for rotating the plurality of fan blades about the axis. A center of gravity of the gas turbine engine is located a first axial distance from the trailing edge of the aft most turbine blade that is between about 35% and about 75% of a total length between the leading edge of the plurality of fan blades and the trailing edge of the aft most turbine blade.

Abstract translation: 燃气涡轮发动机包括可围绕轴线旋转的多个风扇叶片，其中多个风扇叶片中的每一个包括前缘。 燃气涡轮发动机还包括涡轮部分，其包括具有后缘的后部大多数涡轮机叶片和由涡轮机部分驱动的用于使多个风扇叶片绕轴线旋转的齿轮架构。 燃气涡轮发动机的重心位于距离尾部最大涡轮机叶片的后缘的第一轴向距离处，其在多个风扇叶片的前缘之间的总长度的约35％和约75％之间， 尾部最后端的涡轮叶片。

公开(公告)号：WO2014018141A2

公开(公告)日：2014-01-30

申请号：PCT/US2013037674

申请日：2013-04-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  SCHWARZ FREDERICK M

IPC: F02C3/107 ,  F02C3/067 ,  F02K3/072

CPC classification number: F02C3/107 ,  F01D1/10 ,  F01D1/26 ,  F01D5/06 ,  F01D15/12 ,  F02C3/06 ,  F02C3/067 ,  F02C3/073 ,  F05D2220/32 ,  F05D2250/44 ,  F05D2260/4031 ,  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 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 and the fan drive turbine configured to rotate in the same first direction. The intermediate speed spool rotates in an opposed, second 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。 所述高速线轴和所述风扇驱动涡轮机构造成沿相同的第一方向旋转。 中间速度卷轴以相对的第二方向旋转。

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：WO2015138030A2

公开(公告)日：2015-09-17

申请号：PCT/US2014071037

申请日：2014-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL L

IPC: F02C3/107

CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/4031

Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan. An output of the speed change mechanism connects to the fan.

Abstract translation: 根据本公开的示例的燃气涡轮发动机包括构造成驱动风扇部分的驱动涡轮机，连接到驱动涡轮机并位于驱动涡轮机的后部并且位于风扇后部的变速机构。 变速机构的输出与风扇连接。