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公开(公告)号：WO2015088680A1
公开(公告)日：2015-06-18
申请号：PCT/US2014/064460
申请日：2014-11-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： BROWN, Charles W. , ALARCON, Andrew G. , BUGAJ, Shari L. , WATSON, Charles R.
CPC classification number: F01D5/3053 , F01D5/143 , F01D5/30 , F01D11/008 , F05D2220/36 , F05D2230/60 , F05D2260/31 , F05D2300/603 , Y02T50/672
Abstract: In a featured embodiment, a fan rotor comprises a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.
Abstract translation: 在特征实施例中，风扇转子包括平台。 夹具在平台的径向内侧延伸。 每个U形夹具有一个孔。 轮毂具有定位在U形夹的中间间隔的端部处的毂凸耳和孔。 销延伸穿过轮毂中的孔和套筒将平台连接到轮毂。 夹头中的孔形成为具有用于支撑销的内表面。 还公开了一种形成风扇叶片平台的方法。
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公开(公告)号：EP2915742B1
公开(公告)日：2016-11-09
申请号：EP15157399.5
申请日：2015-03-03
Applicant: United Technologies Corporation
Inventor： ROACH, James T. , COOK, III, Grant O. , KLING, Colin J. , O'BRIEN, James F. , BUGAJ, Shari L.
CPC classification number: F01D9/02 , B64C11/14 , F01D5/02 , F01D5/12 , F02C7/04 , F05D2220/32 , F05D2300/10 , F05D2300/603 , F05D2300/6034 , Y02T50/672
Abstract: A spinner (80) for a gas turbine engine (20) comprises an outer shell (82) for defining an airflow path when mounted in a gas turbine engine (20). An inner surface (84) is provided with a plurality of webs (86). A gas turbine engine (20) and a fan section (22) for a gas turbine engine (20) are also disclosed.
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3.发明公开EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开EFFIZIENTER PROPULSOR MIT NIEDRIGEMDRUCKVERHÄLTNISFÜRGASTURBINENMOTOREN
公开(公告)号：EP3085897A1
公开(公告)日：2016-10-26
申请号：EP16166928.8
申请日：2016-04-25
Applicant: United Technologies Corporation
Inventor： GALLAGHER, Edward J. , MONZON, Byron R. , BUGAJ, Shari L.
CPC classification number: F01D5/282 , F02K3/06 , F05D2220/327 , F05D2300/603 , Y02T50/672
Abstract: A gas turbine engine (20) includes a core flow passage, a bypass flow passage, and a propulsor (42) arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor (42) includes a row (72) of propulsor blades (74). The row (72) includes no more than 20 of the propulsor blades (74). The propulsor (42) has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades (74).
Abstract translation: 燃气涡轮发动机（20）包括芯流路，旁通流路和配置在旁通流路和芯流路的入口的推进器（42）。 推进器（42）包括一排（72）的推进式叶片（74）。 行（72）包括不超过20个推进刀片（74）。 推进器（42）的推压刀片（74）之间的压力比介于约1.2和约1.7之间。
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公开(公告)号：EP3080417A1
公开(公告)日：2016-10-19
申请号：EP14869817.8
申请日：2014-11-07
Applicant: United Technologies Corporation
Inventor： BROWN, Charles W. , ALARCON, Andrew G. , BUGAJ, Shari L. , WATSON, Charles R.
CPC classification number: F01D5/3053 , F01D5/143 , F01D5/30 , F01D11/008 , F05D2220/36 , F05D2230/60 , F05D2260/31 , F05D2300/603 , Y02T50/672
Abstract: In a featured embodiment, a fan rotor comprises a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.
Abstract translation: 在特征实施例中，风扇转子包括平台。 夹具沿平台的径向内侧延伸。 每个U形夹具有一个孔。 轮毂具有定位在U形夹的中间间隔的端部处的毂凸耳和孔。 销延伸穿过轮毂和轮毂中的孔，以将平台连接到轮毂。 夹头中的孔形成为具有用于支撑销的内表面。 还公开了一种形成风扇叶片平台的方法。
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公开(公告)号：EP2915742B2
公开(公告)日：2019-08-28
申请号：EP15157399.5
申请日：2015-03-03
Applicant: United Technologies Corporation
Inventor： ROACH, James T. , COOK, III, Grant O. , KLING, Colin J. , O'BRIEN, James F. , BUGAJ, Shari L.
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Patent Agency Ranking
公开(公告)号：EP2915742A1
公开(公告)日：2015-09-09
申请号：EP15157399.5
申请日：2015-03-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ROACH, James T. , COOK, III, Grant O. , KLING, Colin J. , O'BRIEN, James F. , BUGAJ, Shari L.
CPC classification number: F01D9/02 , B64C11/14 , F01D5/02 , F01D5/12 , F02C7/04 , F05D2220/32 , F05D2300/10 , F05D2300/603 , F05D2300/6034 , Y02T50/672
Abstract: A spinner (80) for a gas turbine engine (20) comprises an outer shell (82) for defining an airflow path when mounted in a gas turbine engine (20). An inner surface (84) is provided with a plurality of webs (86). A gas turbine engine (20) and a fan section (22) for a gas turbine engine (20) are also disclosed.
Abstract translation: 用于燃气涡轮发动机（20）的旋转器（80）包括用于在安装在燃气涡轮发动机（20）中时限定气流路径的外壳（82）。 内表面（84）设置有多个腹板（86）。 还公开了一种燃气涡轮发动机（20）和用于燃气涡轮发动机（20）的风扇部分（22）。
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公开(公告)号：EP3029297B1
公开(公告)日：2020-04-22
申请号：EP15197598.4
申请日：2015-12-02
Applicant: United Technologies Corporation
Inventor： KLING, Colin J. , BUGAJ, Shari L. , ROACH, James T.
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公开(公告)号：EP3029297A1
公开(公告)日：2016-06-08
申请号：EP15197598.4
申请日：2015-12-02
Applicant: United Technologies Corporation
Inventor： KLING, Colin J. , BUGAJ, Shari L. , ROACH, James T.
Abstract: A spinner (60;76) for a gas turbine engine (20) is disclosed. The spinner (60;76) may include a body (66) extending between a first and second end (62,64) comprised of a cured chopped unidirectional fiber pre-impregnated material. The body (66) may have a generally conical shape and may further be plated with a metal or metal alloy.
Abstract translation: 公开了一种用于燃气涡轮发动机（20）的旋转器（60; 76）。 旋转器（60; 76）可以包括在由固化的切断的单向纤维预浸渍材料组成的第一和第二端（62,64）之间延伸的主体（66）。 主体（66）可以具有大致圆锥形的形状，并且还可以镀金属或金属合金。
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公开(公告)号：EP3019710A2
公开(公告)日：2016-05-18
申请号：EP14822947.9
申请日：2014-07-09
Applicant: United Technologies Corporation
Inventor： ROACH, James T. , BARNETT, Barry , COOK III, Grant O. , WATSON, Charles R. , BUGAJ, Shari L. , LEVASSEUR, Glenn , TWELVES, Wendell V. Jr. , HERTEL, Christopher J. , KLING, Colin J. , TURNER, Matthew A. , XU, JinQuan , CLARKSON, Steven , CAULFIELD, Michael
CPC classification number: F04D19/002 , B32B1/00 , B32B1/08 , B32B27/281 , B32B27/285 , B32B27/34 , B32B27/36 , B32B2255/10 , B32B2255/205 , B32B2262/101 , B32B2262/103 , B32B2262/106 , B32B2270/00 , B32B2307/554 , F01D5/147 , F01D5/26 , F01D5/282 , F01D5/286 , F01D9/041 , F01D25/02 , F01D25/24 , F04D29/388 , F04D29/541 , F05D2220/32 , F05D2230/90 , F05D2240/00 , F05D2240/12 , F05D2240/30 , F05D2260/96 , F05D2300/10 , F05D2300/43 , F05D2300/603 , Y02T50/672 , Y02T50/673
Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.
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公开(公告)号：EP3019721B1
公开(公告)日：2020-02-26
申请号：EP14822381.1
申请日：2014-07-09
Applicant: United Technologies Corporation
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