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公开(公告)号:US09909495B2
公开(公告)日:2018-03-06
申请号:US14600487
申请日:2015-01-20
Applicant: United Technologies Corporation
Inventor: Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler , Michael Winter , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.
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公开(公告)号:US09896969B2
公开(公告)日:2018-02-20
申请号:US14663207
申请日:2015-03-19
Applicant: United Technologies Corporation
Inventor: William G. Sheridan , Marc J. Muldoon , Michael E. McCune
CPC classification number: F01D25/186 , F01D11/02 , F01D25/166 , F01D25/183 , F05D2240/61 , F16H57/0426 , F16J15/164 , F16J15/42 , F16L27/087
Abstract: A transfer bearing assembly is configured to allow a flow of a fluid from an inlet tube to a channel defined by a rotating shaft. The transfer bearing assembly includes a body having an axially forward side and an axially aft side and a first wing having an axially aft end coupled to the axially forward side and an axially forward end. The transfer bearing assembly also includes a first side plate having a radially outward end coupled to the axially forward end of the first wing and a radially inward end.
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公开(公告)号:US09777825B2
公开(公告)日:2017-10-03
申请号:US14455539
申请日:2014-08-08
Applicant: United Technologies Corporation
Inventor: William G. Sheridan , Michael E. McCune
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: A turbine engine includes a housing supporting compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle is supported relative to the carrier and includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and the intermediate gears. A spray bar is external to the carrier and is in communication with the lubrication passage. The spray bar terminates near the sun gear for directing lubricant on the sun gear.
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公开(公告)号:US20170276046A1
公开(公告)日:2017-09-28
申请号:US15621406
申请日:2017-06-13
Applicant: United Technologies Corporation
Inventor: Michael E. McCune , William G. Sheridan , Lawrence E. Portlock
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 method of designing a gas turbine engine includes configuring a speed reduction device for driving a fan and configuring 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. A second bearing for rotation is within the first bearing. The second bearing has 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. The first bearing is configured to also include a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.
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公开(公告)号:US20170152756A1
公开(公告)日:2017-06-01
申请号:US14935673
申请日:2015-12-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Frederick M. Schwarz , William G. Sheridan , Michael E. McCune , Gabriel L. Suciu
CPC classification number: F01D15/12 , F01D25/18 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/50 , F05D2260/40311 , F05D2260/98 , F16H1/28 , F16H57/0479 , F16H57/0486
Abstract: A gas turbine engine has a fan rotor, a turbine rotor driving the fan rotor, and an epicyclic gear reduction positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine is configured to drive the sun gear to, in turn, drive the ring gears to, in turn, drive the fan rotor.
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公开(公告)号:US20170108110A1
公开(公告)日:2017-04-20
申请号:US14886676
申请日:2015-10-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: William G. Sheridan
CPC classification number: F16H57/0423 , F01D25/164 , F01D25/18 , F02C3/04 , F02C7/06 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2250/611 , F05D2260/40311 , F05D2260/602 , F05D2260/609 , F05D2260/98 , F16H57/0486 , F16N31/00 , Y02T50/671
Abstract: According to various embodiments, disclosed is a fixed support and gutter system for a ring gear of a turbine engine gear train, the fixed support and gutter system comprising a support structure having an undulating path which forms at least a portion of a gutter structure for capturing oil shed off the gear train.
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公开(公告)号:US20160153356A1
公开(公告)日:2016-06-02
申请号:US15013125
申请日:2016-02-02
Applicant: United Technologies Corporation
Inventor: Frederick M. Schwarz , William G. Sheridan
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath. A core engine includes a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section. A method of designing a gas turbine engine is also disclosed.
Abstract translation: 根据本公开的示例的燃气涡轮发动机尤其包括具有多个风扇叶片的风扇部分。 多个风扇叶片在第一流路的第一内侧边界处具有顶尖半径Rt和内侧前缘半径Rh。 核心发动机包括构造成驱动第一压缩机的第一涡轮机和配置成驱动风扇部分的风扇驱动涡轮机。 还公开了一种设计燃气涡轮发动机的方法。
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公开(公告)号:US20160084104A1
公开(公告)日:2016-03-24
申请号:US14848978
申请日:2015-09-09
Applicant: United Technologies Corporation
Inventor: William G. Sheridan , Michael E. McCune
CPC classification number: F01D15/12 , F01D5/02 , F01D25/16 , F01D25/162 , F01D25/28 , F02C7/36 , F05D2220/32 , F05D2230/60 , F05D2240/24 , F05D2240/52 , F05D2260/40311 , F05D2260/98 , F16H3/44 , F16H57/082
Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted aft of the speed change mechanism.
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公开(公告)号:US20160025003A1
公开(公告)日:2016-01-28
申请号:US14776080
申请日:2014-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Frederick M. Schwarz , William G. Sheridan
CPC classification number: F02C3/107 , F01D25/16 , F02C7/06 , F02C7/36 , F02K3/06 , F04D25/028 , F04D29/059 , F04D29/321 , F05D2260/40311
Abstract: A turbofan engine (300; 600; 700) comprising a fan shaft (120) configured to rotate about an axis (500) of the engine. A fan drive gear system (60) is configured to drive the fan shaft. The fan drive gear system has a centerplane (540). A first spool comprises a high pressure turbine (326) and a high pressure compressor (324). A second spool comprises an intermediate pressure turbine (328), a lower pressure compressor, and a shaft (334) coupling the intermediate pressure turbine to the lower pressure compressor. A third spool comprises a lower pressure turbine (330) coupled to the fan drive gear system to drive the fan. The engine has a plurality of main bearings. The turbofan engine has a single stage fan. Of the main bearings, at least one is a shaft-engaging bearing engaging a driving shaft (336) coupled to the fan drive gear system. A closest (340; 640) of the shaft-engaging bearings engaging the driving shaft behind the fan drive gear system has a centerplane (550) and a characteristic radius (RB). The half angle (θ) of a virtual cone (530) intersecting the core flowpath inboard boundary at the gear system centerplane (540) and said closest of the shaft-engaging bearings at the characteristic radius (RB) is greater than about 32°. A hub-to-tip ratio (HR:FR) of the fan is less than about 0.38.
Abstract translation: 涡轮风扇发动机(300; 600; 700)包括构造成围绕发动机的轴线(500)旋转的风扇轴(120)。 风扇驱动齿轮系统(60)构造成驱动风扇轴。 风扇驱动齿轮系统具有中心面(540)。 第一阀芯包括高压涡轮机(326)和高压压缩机(324)。 第二卷轴包括中压涡轮机(328),低压压缩机以及将中压涡轮机与低压压缩机联接的轴(334)。 第三卷轴包括联接到风扇驱动齿轮系统以驱动风扇的低压涡轮机(330)。 发动机具有多个主轴承。 涡扇发动机具有单级风扇。 在主轴承中,至少一个是与联接到风扇驱动齿轮系统的驱动轴(336)接合的轴接合轴承。 与风扇驱动齿轮系统后面的驱动轴接合的轴接合轴承的最接近(340; 640)具有中心面(550)和特征半径(RB)。 与齿轮系中心平面(540)处的内侧边界处的核心流路相交的虚拟锥体(530)和特征半径(RB)处的所述最接近的轴接合轴承的半角(& tt)大于约32° 。 风扇的轮毂比(HR:FR)小于约0.38。
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40.
公开(公告)号:US20150377142A1
公开(公告)日:2015-12-31
申请号:US14767477
申请日:2014-02-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: William G. Sheridan , Gabriel L. Suciu , Brian D. Merry
CPC classification number: F02C7/275 , F01D19/00 , F02C3/107 , F02C7/36 , F05D2260/40 , F05D2260/403 , F05D2260/85
Abstract: A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine.
Abstract translation: 燃气涡轮发动机包括第一压缩机,第二压缩机,起动发电机和离合器。 起动发电机联接到第一压缩机。 离合器选择性地联接第二压缩机和第一压缩机。 离合器设置在第一轴和第二轴之间,以使第一轴与静止的第二轴接合。 飞行重量系统与离合器机构接合以允许当经受超过阈值速度的旋转运动时第一轴相对于第二轴的续流。 一种用于启动燃气涡轮发动机的方法包括使用离合器将低压压缩机与高压压缩机接合,利用联接到低压压缩机的启动发电机旋转低压压缩机和高压压缩机,点燃燃气涡轮发动机, 以及在所述燃气涡轮发动机的操作速度下离合所述离合器。
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