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21.发明专利
公开(公告)号：CA2854077C
公开(公告)日：2021-03-16
申请号：CA2854077
申请日：2013-01-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , SUCIU GABRIEL , ACKERMANN WILLIAM K , KUPRATIS DANIEL BERNARD
Abstract: A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.
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22.发明专利
公开(公告)号：CA2853839C
公开(公告)日：2020-07-14
申请号：CA2853839
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , SUCIU GABRIEL L , KUPRATIS DANIEL BERNARD , ACKERMANN WILLIAM K
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted on the low pressure turbine with an intermediate bearing.
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公开(公告)号：SG10201706005SA
公开(公告)日：2017-08-30
申请号：SG10201706005S
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , ACKERMANN WILLIAM K , KUPRATIS DANIEL BERNARD , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：CA2854728C
公开(公告)日：2016-08-16
申请号：CA2854728
申请日：2014-06-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHERIDAN WILLIAM G , MCCUNE MICHAEL E , SCHWARZ FREDERICK M , KUPRATIS DANIEL BERNARD , SUCIU GABRIEL L , ACKERMANN WILLIAM K , HUSBAND JASON
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.
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公开(公告)号：CA2854728A1
公开(公告)日：2015-03-24
申请号：CA2854728
申请日：2014-06-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SHERIDAN WILLIAM G , MCCUNE MICHAEL E , SCHWARZ FREDERICK M , KUPRATIS DANIEL BERNARD , SUCIU GABRIEL L , ACKERMANN WILLIAM K , HUSBAND JASON
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.
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Patent Agency Ranking26.发明专利
公开(公告)号：SG11201403615QA
公开(公告)日：2014-10-30
申请号：SG11201403615Q
申请日：2013-01-18
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHWARZ FREDERICK M , SUCIU GABRIEL , ACKERMANN WILLIAM K , KUPRATIS DANIEL BERNARD
IPC: F02K3/06 , F02C7/06 , F04D29/056
Abstract: A gas turbine engine includes a very high speed fan drive turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is mounted by bearings positioned at an outer periphery of a shaft driven by the high pressure turbine.
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27.发明公开METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER FLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS 审中-公开方法和设备用于处理VORDIFFUSORSTROMS进行冷却高压涡轮组件
公开(公告)号：EP2961943A4
公开(公告)日：2017-01-11
申请号：EP14756377
申请日：2014-02-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , ACKERMANN WILLIAM K
CPC classification number: F02C7/18 , F01D5/02 , F01D9/041 , F01D9/065 , F01D17/105 , F01D25/12 , F01D25/24 , F02C3/04 , F02C6/08 , F02C7/04 , F02C7/06 , F02C7/14 , F04D29/541 , F05D2220/32 , F05D2240/12 , F05D2240/35 , F05D2260/20 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.
Abstract translation: 提供了一种用于燃气涡轮发动机扩散器也包括外护罩到护罩内，所述外护罩之间撑杆的倍数，并且所述的内罩在环形设计流动路径来定义，并且在通信中跨预扩散器入口与 所述环形设计流路。
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28.发明公开METHOD AND APPARATUS FOR HANDLING PRE-DIFFUSER AIRFLOW FOR COOLING HIGH PRESSURE TURBINE COMPONENTS 审中-公开方法和设备用于处理VORDIFFUSOR空气流进行冷却高压涡轮组件
公开(公告)号：EP2961942A4
公开(公告)日：2017-01-11
申请号：EP14756284
申请日：2014-02-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , ACKERMANN WILLIAM K
CPC classification number: F02C7/18 , F01D5/02 , F01D9/041 , F01D9/065 , F01D17/105 , F01D25/12 , F01D25/24 , F02C3/04 , F02C6/08 , F02C7/04 , F02C7/06 , F02C7/14 , F04D29/541 , F05D2220/32 , F05D2240/12 , F05D2240/35 , F05D2260/20 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.
Abstract translation: 提供了一种用于燃气涡轮发动机扩散器也包括外护罩到护罩内，所述外护罩之间撑杆的倍数，并且所述的内罩在环形设计流动路径来定义，并且在通信的中间切割扩散预入口与 所述环形设计流路。
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公开(公告)号：EP2834497A4
公开(公告)日：2015-08-12
申请号：EP13773016
申请日：2013-03-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , PICKFORD SIMON , ACKERMANN WILLIAM K , SNAPE NATHAN
IPC: F02C7/00 , F01D13/02 , F01D15/08 , F01D15/12 , F02C7/047 , F02C7/12 , F02C7/14 , F02C7/32 , F02C9/00 , F02K3/00 , F02K3/06 , F02K99/00
CPC classification number: F01D13/02 , F01D15/08 , F01D15/12 , F02C7/047 , F02C7/14 , F02C7/32 , F02K3/06 , F05D2260/213 , Y02T50/675
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30.发明公开GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION AND BEARING SUPPORT FEATURES 审中-公开具有快速低压涡轮部分和贮水池特点的燃气涡轮发动机
公开(公告)号：EP2841718A4
公开(公告)日：2016-03-02
申请号：EP13822569
申请日：2013-04-23
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , SCHWARZ FREDERICK M , KUPRATIS DANIEL BERNARD , MERRY BRIAN D , ACKERMANN WILLIAM K
CPC classification number: F01D25/162 , F02C3/107 , F02C7/06 , F02K3/06
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