公开(公告)号：US20170350276A1

公开(公告)日：2017-12-07

申请号：US15685491

申请日：2017-08-24

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D25/18 ,  F02C7/36 ,  F01D25/16 ,  F16H1/28 ,  F16H57/04 ,  F02C7/06

CPC classification number: F01D25/18 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F05D2260/40311 ,  F16H1/28 ,  F16H57/043 ,  F16H57/0471 ,  F16H57/0479 ,  F16H57/0486 ,  Y02T50/671

Abstract: A lubrication system for a fan drive planetary gear system according to an exemplary aspect of the present disclosure includes, among other things, a stationary first bearing configured to receive a lubricant from a lubricant input, the stationary first bearing is axially aligned with a fan drive shaft. A second bearing is configured to rotate with the fan drive shaft, the first bearing engages the second bearing and is configured to transfer the lubricant from the first bearing to the second bearing and into at least one fluid passage in the fan drive shaft. A conduit fluidly connects the at least one passage in the fan drive shaft with at least one component on the fan drive gear system.

公开(公告)号：US09816443B2

公开(公告)日：2017-11-14

申请号：US15337171

申请日：2016-10-28

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F01D1/04 ,  F01D25/16 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F02C7/00 ,  F01D9/04

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 includes an engine centerline longitudinal axis and a fan section including a fan with fan blades and rotatable about the engine centerline longitudinal axis. A low corrected fan tip speed less than about 1400 ft/sec and the low corrected fan tip speed is an actual fan tip speed determined at an ambient temperature divided by [(Tram ° R)/(518.7 ° R)]0.5, where T represents the ambient temperature in degrees Rankine. A bypass ratio greater than about 11 and a speed reduction device having a gear system with a gear ratio. A low and high pressure turbine in communication with a first and second shaft, respectively. The first and second shafts are concentric and mounted via at least one of the bearing systems for rotation about the engine centerline longitudinal axis and the first shaft is in communication with the fan through the speed reduction device and the low pressure turbine includes four stages.

公开(公告)号：US09759309B2

公开(公告)日：2017-09-12

申请号：US14530950

申请日：2014-11-03

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02C7/36 ,  F16H57/04 ,  F01D25/18 ,  F02C3/04 ,  F16H57/08

CPC classification number: F16H57/0427 ,  F01D25/18 ,  F02C3/04 ,  F02C7/36 ,  F05D2230/60 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H57/0421 ,  F16H57/0423 ,  F16H57/046 ,  F16H57/0479 ,  F16H57/0482 ,  F16H57/0486 ,  F16H57/082 ,  Y10T29/49316 ,  Y10T29/4932 ,  Y10T29/49323 ,  Y10T29/49464

Abstract: An epicyclic gear train component includes spaced apart walls with circumferentially spaced mounts that interconnect the walls. The mounts provide circumferentially spaced apart apertures between the mounts at an outer circumference of the walls. Baffles are arranged between the walls near the mounts. Gear pockets are provided between the baffles and the baffles include a lubrication passage that terminates at least one of the gear pockets. One of the walls includes a hole which has a tube that extends through the hole and is received in an opening in the baffle. The tube is in communication with the lubrication passage.

公开(公告)号：US09745862B2

公开(公告)日：2017-08-29

申请号：US14912535

申请日：2014-08-13

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F16H57/04 ,  F01D25/18 ,  F16H1/28 ,  F01D25/16 ,  F02C7/36 ,  F02C7/06

CPC classification number: F01D25/18 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36 ,  F05D2260/40311 ,  F16H1/28 ,  F16H57/043 ,  F16H57/0471 ,  F16H57/0479 ,  F16H57/0486 ,  Y02T50/671

Abstract: A lubrication system for a fan drive planetary gear system according to an exemplary aspect of the present disclosure includes, among other things, a stationary first bearing configured to receive a lubricant from a lubricant input, the stationary first bearing is located adjacent a fan drive shaft. A second bearing is configured to rotate with the fan drive shaft, the first bearing engages the second bearing and is configured to transfer the lubricant from the first bearing to the second bearing and into at least one fluid passage in the fan drive shaft. A conduit fluidly connects the at least one passage in the fan drive shaft with at least one component on the fan drive gear system.

公开(公告)号：US09726083B2

公开(公告)日：2017-08-08

申请号：US14307587

申请日：2014-06-18

Applicant: United Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F02C3/04 ,  F16H1/48 ,  F16H57/04

CPC classification number: F02C7/36 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2240/50 ,  F05D2260/40311 ,  F16H1/2836 ,  F16H1/48 ,  F16H57/0479 ,  Y10T29/49464

Abstract: A disclosed fan drive gear system includes a sun gear rotatable about an axis of rotation, a plurality of intermediate gears rotatable about an intermediate gear rotation axis in meshing engagement with the sun gear and a ring gear circumscribing the intermediate gears. A bearing assembly supports at least one of the plurality of intermediate gears and includes a first beam extending in a first direction and a second beam extending from an end of the first beam in a second direction. The bearing surface supported on the second beam such that first and second beams are configured to maintain the bearing surface substantially parallel to the intermediate gear rotation axis during operation.

公开(公告)号：US09677420B2

公开(公告)日：2017-06-13

申请号：US14474869

申请日：2014-09-02

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  William G. Sheridan ,  Lawrence E. Portlock

IPC: F01D25/18 ,  F01D25/16 ,  F02C3/10 ,  F02C7/36 ,  F02K3/06 ,  F02C7/06 ,  F02C7/10 ,  F16N7/34

CPC classification number: F01N3/208 ,  F01D25/16 ,  F01D25/18 ,  F01N3/2066 ,  F01N11/00 ,  F01N2610/01 ,  F01N2610/02 ,  F01N2610/1406 ,  F01N2610/142 ,  F01N2610/148 ,  F01N2900/1814 ,  F02C3/10 ,  F02C7/06 ,  F02C7/10 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  F16N7/34 ,  Y02T10/24 ,  Y02T50/671 ,  Y10T29/4932 ,  Y10T137/0324 ,  Y10T137/7297

Abstract: A gas turbine engine includes a fan, a speed reduction device driving the fan and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows and a second race. A second bearing for rotation is within the first bearing including a first opening in registration with the first race such that lubricant may flow from the first race through the first opening into a first conduit. There is a rotating carrier for supporting at least one planetary gear. The second bearing extends from the rotating carrier about an axis. A first spray bar is disposed on the carrier. The second bearing has a second opening in registration with the second race and a second conduit for passing lubricant to the spray bar.

公开(公告)号：US20170130673A1

公开(公告)日：2017-05-11

申请号：US15411459

申请日：2017-01-20

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02K3/06 ,  F04D29/52 ,  F01D25/16 ,  F02C7/36

CPC classification number: F02K3/06 ,  F01D25/168 ,  F02C7/36 ,  F04D29/522 ,  F05D2220/36 ,  F05D2260/40311

Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.

公开(公告)号：US20170114661A1

公开(公告)日：2017-04-27

申请号：US14922507

申请日：2015-10-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D21/00 ,  F02C3/04 ,  F02C7/06 ,  F01D15/12

CPC classification number: F01D21/006 ,  F01D15/12 ,  F01D25/20 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02K3/06 ,  F05D2220/36 ,  F05D2260/311 ,  F05D2260/902 ,  F05D2260/98 ,  F05D2270/116 ,  F05D2270/301 ,  F05D2270/3032 ,  F16D11/16 ,  F16D2011/006

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.

公开(公告)号：US20170074165A1

公开(公告)日：2017-03-16

申请号：US15358267

申请日：2016-11-22

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/06 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F16H1/28 ,  F02K1/06 ,  F01D5/06 ,  F04D29/32 ,  F04D29/38 ,  F02C7/28 ,  F02C3/04 ,  F02C9/18

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 turbofan engine according to an exemplary aspect of the present disclosure includes, among other things, a fan having a plurality of blades, and a transmission is configured to drive the fan. The fan blades have a peak tip radius RT. The fan blades have 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: 根据本公开的示例性方面的涡轮风扇发动机尤其包括具有多个叶片的风扇，并且变速器构造成驱动风扇。 风扇叶片具有峰顶半径RT。 风扇叶片在流路的内侧边界处具有内侧前缘半径RH。 RH与RT的比值小于约0.40。

公开(公告)号：US20170051677A1

公开(公告)日：2017-02-23

申请号：US15337171

申请日：2016-10-28

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F02C7/36 ,  F01D9/04 ,  F01D25/16 ,  F02C3/04 ,  F02K3/06

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 includes an engine centerline longitudinal axis and a fan section including a fan with fan blades and rotatable about the engine centerline longitudinal axis. A low corrected fan tip speed less than about 1400 ft/sec and the low corrected fan tip speed is an actual fan tip speed determined at an ambient temperature divided by [(Tram ° R)/(518.7° R)]0.5, where T represents the ambient temperature in degrees Rankine. A bypass ratio greater than about 11 and a speed reduction device having a gear system with a gear ratio. A low and high pressure turbine in communication with a first and second shaft, respectively. The first and second shafts are concentric and mounted via at least one of the bearing systems for rotation about the engine centerline longitudinal axis and the first shaft is in communication with the fan through the speed reduction device and the low pressure turbine includes four stages.

Abstract translation: 燃气涡轮发动机包括发动机中心线纵向轴线和风扇部分，风扇部分包括具有风扇叶片的风扇并可围绕发动机中心线纵向轴线旋转。 小于约1400ft / sec的低校正风扇叶尖速度和低校正风扇叶尖速度是在环境温度除以[（Tram°R）/（518.7°R）] 0.5时确定的实际风扇叶尖速度，其中T 表示环境温度，以度兰为单位。 旁路比大于约11，减速装置具有齿轮比齿轮系。 分别与第一和第二轴连通的低压和高压涡轮机。 第一和第二轴是同心的，并且经由至少一个轴承系统安装，用于围绕发动机中心线纵向轴线旋转，并且第一轴通过减速装置与风扇连通，低压涡轮机包括四个阶段。