公开(公告)号：US20180156135A1

公开(公告)日：2018-06-07

申请号：US15875656

申请日：2018-01-19

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F02C7/36 ,  F02C7/32 ,  F02C3/06 ,  F16H1/36

CPC classification number: F02C7/32 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C3/113 ,  F02C7/00 ,  F02C7/36 ,  F05D2210/12 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/40 ,  F05D2260/40311 ,  F16H1/28 ,  F16H1/36

Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an engine centerline longitudinal axis. The fan has a low corrected fan tip speed less than 1400 ft/sec. A bypass ratio is greater than 13 and less than 20. A fan pressure ratio less than 1.48. A speed reduction device comprises a gear system with a gear ratio of at least 2.6 and less than or equal to 4.1. A low and high pressure turbine is in communication with a first and second shaft, respectively. The low pressure turbine includes at least three stages and no more than four stages. The high pressure turbine includes two stages. The gear ratio is configured such that in operation the fan blade does not exceed a fan tip speed boundary condition or a second stress level. A low pressure turbine rotor does not exceed a first stress level.

公开(公告)号：US20170122220A1

公开(公告)日：2017-05-04

申请号：US15411173

申请日：2017-01-20

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/36 ,  F02C7/06 ,  F02C9/18 ,  F01D25/24 ,  F01D5/06 ,  F01D9/02 ,  F01D21/00 ,  F02C3/06 ,  F02K3/06

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D5/12 ,  F01D9/02 ,  F01D21/003 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/40 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10 at cruise power, and a low fan pressure ratio of less than 1.45 measured across a fan blade alone. A gear arrangement drives the fan section. A compressor section includes both a low pressure compressor and a high pressure compressor. A guide vane includes a forward attachment, the forward attachment positioned aft of a plumbing connection area. A turbine section drives the gear arrangement, and may have a low pressure turbine with a low pressure turbine pressure ratio greater than 5:1, and a two stage high pressure turbine. An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor and a pressure ratio across the high pressure compressor, and greater than 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the high pressure compressor is greater than 7.

公开(公告)号：US20160290241A1

公开(公告)日：2016-10-06

申请号：US15184253

申请日：2016-06-16

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02C7/36 ,  F02C3/04 ,  F02K3/06 ,  F01D5/12 ,  F01D25/24 ,  F01D9/02 ,  F01D25/28 ,  F02C7/28 ,  F02C7/06 ,  F02K3/02

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D5/12 ,  F01D9/02 ,  F01D21/003 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/40 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine includes, among other things, a fan section, a core engine, a bypass passage, and a bypass ratio defined as the volume of air passing into the bypass passage compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to about 8 at cruise power. A gear arrangement is configured to drive the fan section. A compressor section includes both a first compressor section and a second compressor section. A turbine section is configured to drive the gear arrangement, and may have a low pressure turbine with four stages and a low pressure turbine pressure ratio greater than about 5:1, and a high pressure turbine with two stages. An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor section and a pressure ratio across the second compressor section, and greater than about 40, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the second compressor section is greater than about 7.

Abstract translation: 除了别的以外，燃气涡轮发动机还包括风扇部分，核心发动机，旁通通道和旁路比，其被定义为与进入核心发动机的空气体积相比进入旁路通道的空气量， 旁路比在巡航功率时大于或等于约8。 齿轮装置被配置成驱动风扇部分。 压缩机部分包括第一压缩机部分和第二压缩机部分。 涡轮部分构造成驱动齿轮装置，并且可以具有四级的低压涡轮机和大于约5:1的低压涡轮机压力比，以及具有两级的高压涡轮机。 整个压力比通过跨第一压缩机段的压力比和跨越第二压缩机段的压力比的组合提供，并且在海平面和静态的额定额定起飞功率下测量大于约40。 跨越第二压缩机部分的压力比大于约7。

公开(公告)号：US20150315974A1

公开(公告)日：2015-11-05

申请号：US14649265

申请日：2013-05-29

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Karl L. Hasel ,  Jessica Tsay

IPC: F02C9/00

CPC classification number: F02C9/00 ,  F01D13/006 ,  F01D13/02 ,  F02C3/10 ,  F02C3/107 ,  F02K3/06 ,  F02K3/062 ,  F05D2220/324 ,  F05D2220/326 ,  F05D2250/31 ,  F05D2260/4031

Abstract: A gas turbine engine has a first shaft including a first compressor rotor. A second shaft includes a second compressor rotor disposed upstream of the first compressor rotor. The second compressor rotor has a first overall pressure ratio. The first compressor rotor has a second overall pressure ratio, with a ratio of the first overall pressure ratio to the second overall pressure ratio being greater than or equal to about 3.0.

Abstract translation: 燃气涡轮发动机具有包括第一压缩机转子的第一轴。 第二轴包括设置在第一压缩机转子的上游的第二压缩机转子。 第二压缩机转子具有第一总压力比。 第一压缩机转子具有第二总压力比，第一总压力比与第二总压力比的比率大于或等于约3.0。

公开(公告)号：US20150027101A1

公开(公告)日：2015-01-29

申请号：US14044971

申请日：2013-10-03

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel

IPC: F02K3/02 ,  F02C7/36

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

Abstract: An example gas turbine engine includes, among other things, a geared architecture rotatably coupled to the fan drive shaft, and a high pressure compressor. The gas turbine engine is configured so that a core temperature at an exit of the high-pressure compressor is approximately in a range of about 1150 to about 1350 degrees Fahrenheit at take-off. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to a primary stream exhaust velocity, is approximately in a range of about 0.75 to about 0.90. A Bypass Ratio of the engine is greater than about 8.0.

Abstract translation: 一个示例性的燃气涡轮发动机尤其包括可旋转地联接到风扇驱动轴的齿轮架构和高压压缩机。 燃气涡轮发动机构造成使得在高压压缩机的出口处的核心温度在起飞时大约在1150至约1350华氏度的范围内。 燃气涡轮发动机被构造成使得由风扇流排气速度与主流排气速度的比率限定的排气速度比大约在约0.75至约0.90的范围内。 发动机的旁路比大于约8.0。

公开(公告)号：US20140234078A1

公开(公告)日：2014-08-21

申请号：US14203863

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F02C7/36

CPC classification number: F02C7/36 ,  F05D2230/60 ,  F05D2260/40311 ,  F05D2260/941

Abstract: A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0.

Abstract translation: 燃气涡轮发动机包括风扇部分，风扇部分包括可围绕轴线旋转的风扇。 减速装置连接到风扇。 减速装置包括具有至少2.5的行星齿轮比的行星风扇驱动齿轮系统。 旁路比大于约11.0。

公开(公告)号：US20140205439A1

公开(公告)日：2014-07-24

申请号：US14219112

申请日：2014-03-19

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  Karl L. Hasel

IPC: F02C3/107 ,  F02C7/36 ,  F02C7/06 ,  F02K3/00

CPC classification number: F02C7/06 ,  F01D25/162 ,  F02C3/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/00 ,  F02K3/04 ,  Y02T50/671 ,  Y10T29/4932

Abstract: A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.

Abstract translation: 燃气涡轮发动机包括壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 齿轮架构包括行星齿轮系。 风扇由齿轮架构旋转驱动。 轴提供旋转轴。 轮毂由轴可操作地支撑。 第一和第二轴承分别相对于中间壳体和进气口支撑轴。

公开(公告)号：US08753065B2

公开(公告)日：2014-06-17

申请号：US13758075

申请日：2013-02-04

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F01D1/24

CPC classification number: F02C7/36 ,  F01D1/04 ,  F01D9/041 ,  F01D25/162 ,  F02C3/04 ,  F02C7/00 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/50 ,  F05D2260/40311

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract translation: 根据本公开的示例性方面的燃气涡轮发动机包括除了别的以外的风扇部分，其包括可围绕轴线旋转的风扇和与风扇连通的减速装置。 减速装置包括具有至少1.5的星形齿轮比的星形驱动齿轮系。 风扇的风扇叶片尖端速度小于1400 fps。

公开(公告)号：US20140157756A1

公开(公告)日：2014-06-12

申请号：US14179771

申请日：2014-02-13

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02K3/06

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

Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6. A compressor section includes both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor.

Abstract translation: 燃气涡轮发动机具有风扇部分，其包括风扇，构造成驱动风扇部分的齿轮装置，齿轮装置限定大于或等于约2.6的齿轮减速比。 压缩机部分包括第一压缩机和第二压缩机。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供。

公开(公告)号：US20140157754A1

公开(公告)日：2014-06-12

申请号：US14179640

申请日：2014-02-13

Applicant: United Technologies Corporation

Inventor： Karl L. Hasel ,  Joseph B. Staubach ,  Brian D. Merry ,  Gabriel L. Suciu ,  Christopher M. Dye

IPC: F02K3/06

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D5/12 ,  F01D9/02 ,  F01D21/003 ,  F01D25/24 ,  F01D25/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18 ,  F02K3/025 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2260/40 ,  F05D2260/4031 ,  F05D2260/40311

Abstract: A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, and a compressor section, including both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor, with the overall pressure ratio being greater than or equal to about 35. A pressure ratio across the fan section is less than or equal to about 1.50. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.

Abstract translation: 一种燃气涡轮发动机具有风扇部分，包括风扇，构造成驱动风扇部分的齿轮装置和包括第一压缩机和第二压缩机的压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 总压力比由第一压缩机和第二压缩机的组合提供，总压力比大于或等于约35.风扇部分的压力比小于或等于约1.50。 风扇被配置为将一部分空气输送到压缩机部分中，并且一部分空气进入旁通管道。