-
Patent Agency Ranking
公开(公告)号：WO2011066365A3
公开(公告)日：2012-01-05
申请号：PCT/US2010057974
申请日：2010-11-24
Applicant: UNITED TECHNOLOGIES CORP , SCHWARK JR FRED W , ATASSI OLIVER V , OWEN WILLIAM D
Inventor： SCHWARK JR FRED W , ATASSI OLIVER V , OWEN WILLIAM D
CPC classification number: F02K1/09 , F02K1/72 , F02K1/763 , F05D2240/50
Abstract: A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider.
Abstract translation: 用于高旁通燃气涡轮发动机的可变面积风扇喷嘴包括可沿着第一界面相对于铰链梁移动的第一轨道滑块。 第二轨道滑块可沿着包括轴承组件的第二接口相对于第一轨道滑块移动。 VAFN整流罩安装到第二轨道滑块。
-
2.发明申请
公开(公告)号：WO2011066368A3
公开(公告)日：2011-12-22
申请号：PCT/US2010057977
申请日：2010-11-24
Applicant: UNITED TECHNOLOGIES CORP , SCHWARK JR FRED W , ATASSI OLIVER V , OWEN WILLIAM D
Inventor： SCHWARK JR FRED W , ATASSI OLIVER V , OWEN WILLIAM D
IPC: F02K1/09
CPC classification number: F02K1/72 , F02K1/09 , F02K3/06 , F05D2260/96 , Y02T50/672
Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners there between to increase a flutter margin.
Abstract translation: 用于高旁路燃气涡轮发动机的机舱组件包括具有第一风扇机舱部分和第二风扇机舱部分的可变区域风扇喷嘴。 所述第二风扇机舱部分可相对于所述第一风扇机舱部分轴向移动以限定辅助端口以改变风扇喷嘴出口区域并调节风扇旁路气流，所述第二风扇机舱部分包括至少一个带有内部部分的整流罩， 以及其间的多个加强件之间以增加颤振余量。
-
公开(公告)号：DE602005007272D1
公开(公告)日：2008-07-17
申请号：DE602005007272
申请日：2005-01-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： OWEN WILLIAM D , WEISSE MICHAEL A , WHITESELL DANIEL J
Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a) has a plurality of cavities (40) and ribs (70) machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs (70) are oriented and biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. In particular, ribs (72a) in a first region (A) of the detail substrate (61) are formed so as not to be parallel to ribs (72c) in a second region (B) of the substrate. The result is a blade with good protection from a wide spectrum of external threats.
-
公开(公告)号：AT397512T
公开(公告)日：2008-06-15
申请号：AT05250319
申请日：2005-01-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： OWEN WILLIAM D , WEISSE MICHAEL A , WHITESELL DANIEL J
Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves (30a;30b). Each detail half (30a) has a plurality of cavities (40) and ribs (70) machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs (70) are oriented and biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. In particular, ribs (72a) in a first region (A) of the detail substrate (61) are formed so as not to be parallel to ribs (72c) in a second region (B) of the substrate. The result is a blade with good protection from a wide spectrum of external threats.
-
公开(公告)号：EP3126638A4
公开(公告)日：2017-04-12
申请号：EP15774355
申请日：2015-03-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BILLINGS SCOTT C , GOTTSCHALK MICHAEL K , OWEN WILLIAM D , GALLAGHER EDWARD J , WHITLOW DARRYL , CHUANG SUE-LI , SADEGHI MANI
IPC: F01D5/14
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/35 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
-
-
-
-
Search Results
5
records
(took 0.023 seconds)
