公开(公告)号：US20150300207A1

公开(公告)日：2015-10-22

申请号：US14755221

申请日：2015-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: F01D25/28 ,  F01D9/02 ,  F01D25/24 ,  F01D5/06 ,  F01D15/12

CPC classification number: F02K3/06 ,  B64D27/26 ,  B64D2027/266 ,  B64D2027/268 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2270/42

Abstract: A gas turbine engine comprises a gear train defined along an engine axis. A spool along the engine axis drives the gear train, and includes a low stage count downstream turbine. A fan rotates at a fan speed about the engine axis and drives the downstream turbine through the gear train. The fan speed is less than a speed of the downstream turbine. A core is surrounded by a core housing defined about the engine axis. A fan nacelle is mounted around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).

Abstract translation: 燃气涡轮发动机包括沿发动机轴线限定的齿轮系。 沿着发动机轴线的线轴驱​​动齿轮系，并且包括低阶计数的下游涡轮机。 风扇以发动机轴线的风扇速度旋转，并通过齿轮系驱动下游涡轮机。 风扇速度小于下游涡轮机的速度。 一个铁芯围绕发动机轴线定义的铁芯壳体围绕。 风扇机舱安装在核心机舱周围，以确定风扇旁路气流的风扇旁路气流。 由风扇旁路通道气流除以通过芯的气流所限定的旁路比大于约十（10）。

公开(公告)号：US20150267618A1

公开(公告)日：2015-09-24

申请号：US14431839

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan ,  Glenn Levasseur

IPC: F02C7/36 ,  B23P15/14 ,  F16H57/04 ,  F16H1/36 ,  F16H1/48

CPC classification number: F02C7/36 ,  B23P15/14 ,  F02C3/107 ,  F05D2260/40311 ,  F16H1/36 ,  F16H1/48 ,  F16H57/0412 ,  F16H57/0486 ,  Y02T50/671 ,  Y10T29/49316

Abstract: A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency.

Abstract translation: 用于燃气涡轮发动机的齿轮架构包括被支撑用于围绕轴线旋转的中心齿轮，与中心齿轮接合的多个中间齿轮和限定中间齿轮的环形齿轮。 在由涡轮部分驱动的输入轴和太阳齿轮之间提供第一柔性联轴器。 齿轮架构提供功率密度，其功率密度包括在限定范围内与齿轮架构的重量相关的功率（HP），该功率有利于整个发动机的重量和效率。

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。

公开(公告)号：US20150176497A1

公开(公告)日：2015-06-25

申请号：US14573812

申请日：2014-12-17

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02C7/32

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a combustor section located axially upstream of the drive turbine, and a speed change mechanism located axially downstream of the combustor section and axially upstream of the drive turbine. 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驱动涡轮机，其构造成驱动风扇部分，位于驱动涡轮机轴向上游的燃烧器部分，以及位于燃烧器部分的轴向下游并且位于轴向上游 驱动涡轮机。 变速机构的输出与风扇连接。

公开(公告)号：US20150044052A1

公开(公告)日：2015-02-12

申请号：US14079688

申请日：2013-11-14

Applicant: United Technologies Corporation

Inventor： Edwin M. Worth ,  Thomas G. Tillman ,  Frederick M. Schwarz

IPC: F01D5/18 ,  F01D5/22

CPC classification number: F01D5/18 ,  F01D5/141 ,  F01D5/145 ,  F01D5/147 ,  F01D5/225 ,  F01D5/28 ,  F02C7/36 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/31 ,  F05D2250/181 ,  F05D2250/311 ,  F05D2250/321 ,  F05D2250/322 ,  F05D2250/62 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/516 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336

Abstract: A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension.

Abstract translation: 风扇叶片包括具有在前缘和后缘之间延伸的翼型件的主体。 风扇叶片具有由盖封闭的通道和覆盖前缘和后缘中的至少一个的端盖中的至少一个。 盖和端盖中的至少一个具有一对相对的端部。 从机翼的吸力壁和压力壁中的至少一个到相对端中的一个的盖和端盖中的一个的外表面延伸的步骤被限定，该步骤小于或等于 到约0.010英寸（0.0254厘米）的尺寸。

公开(公告)号：US08899915B2

公开(公告)日：2014-12-02

申请号：US14260557

申请日：2014-04-24

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Jason Husband ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F01D15/12 ,  F02C7/36 ,  F02C7/20 ,  F02K3/06 ,  F02C3/107

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 flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.

Abstract translation: 燃气涡轮发动机包括用于风扇驱动齿轮系统的柔性安装座。 一个非常高速的风扇驱动涡轮驱动风扇驱动齿轮系统。

公开(公告)号：US08869504B1

公开(公告)日：2014-10-28

申请号：US14087471

申请日：2013-11-22

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02K3/02 ,  F02K1/06 ,  F02C7/06 ,  F01D5/14

CPC classification number: F02C7/06 ,  F01D5/02 ,  F01D5/06 ,  F01D9/06 ,  F01D17/105 ,  F02C3/04 ,  F02C3/06 ,  F02C3/10 ,  F02C3/107 ,  F02C7/28 ,  F02C7/36 ,  F02C9/18 ,  F02K1/06 ,  F02K1/09 ,  F02K3/04 ,  F02K3/06 ,  F04D29/321 ,  F04D29/325 ,  F04D29/38 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/52 ,  F05D2240/54 ,  F05D2240/60 ,  F05D2260/40311 ,  F16H1/28

Abstract: A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.

Abstract translation: 三阀塞涡轮风扇发动机（20）具有可变风扇喷嘴（35）。 风扇叶片在流路的内侧边界处具有峰顶半径RT和内侧前缘半径RH。 RH与RT的比值小于约0.40。

公开(公告)号：US08850793B2

公开(公告)日：2014-10-07

申请号：US14102764

申请日：2013-12-11

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz

IPC: F02K3/02 ,  F02C7/36 ,  F02K7/06

CPC classification number: F02C9/18 ,  F01D1/02 ,  F01D5/02 ,  F01D9/041 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C3/113 ,  F02C7/20 ,  F02C7/36 ,  F02K3/025 ,  F02K3/06 ,  F02K3/075 ,  F02K7/06 ,  F05D2220/32 ,  F05D2260/40311 ,  F05D2260/606 ,  Y02T50/671

Abstract: A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.

Abstract translation: 涡轮风扇发动机被公开并且包括与风扇部分连通的风扇和压缩机，燃烧器，涡轮机和联接到风扇并由涡轮机旋转的减速机构。 涡轮机包括包括三级或更多级的第一涡轮机部分和包括至少两级的第二涡轮部分。 第一涡轮部分中的翼型件与旁路区域的比例小于约170。

公开(公告)号：US20140020404A1

公开(公告)日：2014-01-23

申请号：US14034720

申请日：2013-09-24

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune ,  Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Gabriel L. Suciu ,  William K. Ackermann ,  Jason Husband

IPC: F02C7/06

CPC classification number: F02C7/06 ,  F01D25/18 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/4031 ,  Y02T50/671

Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.

Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括能量消除等于输入到齿轮系统中的能量的小于约2％的能量。

公开(公告)号：US20130192266A1

公开(公告)日：2013-08-01

申请号：US13629681

申请日：2012-09-28

Applicant: United Technologies Corporation

Inventor： David P. Houston ,  Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C3/04

CPC classification number: F02K3/06 ,  F01D5/02 ,  F01D5/026 ,  F01D5/066 ,  F02C3/107 ,  F02C7/36 ,  F05D2240/24 ,  F05D2260/40311 ,  F05D2270/02 ,  F05D2270/07 ,  Y02T50/671 ,  Y02T50/673

Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.