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公开(公告)号：EP0735239B1
公开(公告)日：2005-10-26
申请号：EP96300493.2
申请日：1996-01-24
发明人： Walker, Alan , Staley, Terril K.
CPC分类号： F01D5/143 , F01D1/04 , F05D2230/61 , Y10S415/912 , Y10T29/49238 , Y10T29/49321 , Y10T29/49323
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公开(公告)号：EP2204577A2
公开(公告)日：2010-07-07
申请号：EP09178629.3
申请日：2009-12-10
发明人： Bell, Eric , Gann, Matthew , Livingston, Jamie , Sultan, Mohamad , Walker, Alan
IPC分类号： F03D1/06
CPC分类号： F03D1/06 , F05B2240/30 , Y02E10/721 , Y10T29/49336 , Y10T29/49337
摘要： A blade (108) for use in the generation of power has a leading edge (201) and a trailing edge (203). A first shell portion (301) of the blade (108) extends from the leading edge (201) to the trailing edge (203). A second shell portion (302) of the blade (108) also extends from the leading edge (201) to the trailing edge (203). A root portion (209) of the blade (108) is positioned proximate the wind turbine (100) and a tip portion (207) which extends from the root portion (209) away from the wind turbine (100). A trailing edge insert (220) is positioned between the first shell portion (301) and the second shell portion (302) proximate the root portion (209). The trailing edge insert (220) has a surface (260) which extends between and separates the first shell portion (301) from the second shell portion (302) at the trailing edge (203), such that the insert (220) provides a high lift profile for increased blade efficiency.
摘要翻译： 用于产生动力的叶片（108）具有前缘（201）和后缘（203）。 叶片（108）的第一壳体部分（301）从前缘（201）延伸到后缘（203）。 叶片（108）的第二壳部分（302）也从前缘（201）延伸到后缘（203）。 叶片（108）的根部（209）位于风力涡轮机（100）附近并且从根部（209）远离风力涡轮机（100）延伸的尖端部分（207）。 后缘插入件（220）位于靠近根部（209）的第一壳部分（301）和第二壳部分（302）之间。 后缘插入件（220）具有在后缘（203）处在第一壳部分（302）之间延伸并在第二壳部分（302）处分离第一壳部分（301）的表面（260），使得插入件（220）提供 高升力轮廓提高叶片效率。
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公开(公告)号：EP2204577B1
公开(公告)日：2018-02-21
申请号：EP09178629.3
申请日：2009-12-10
发明人： Bell, Eric , Gann, Matthew , Livingston, Jamie , Sultan, Mohamad , Walker, Alan
IPC分类号： F03D1/06
CPC分类号： F03D1/06 , F05B2240/30 , Y02E10/721 , Y10T29/49336 , Y10T29/49337
摘要： A blade (108) for use in the generation of power has a leading edge (201) and a trailing edge (203). A first shell portion (301) of the blade (108) extends from the leading edge (201) to the trailing edge (203). A second shell portion (302) of the blade (108) also extends from the leading edge (201) to the trailing edge (203). A root portion (209) of the blade (108) is positioned proximate the wind turbine (100) and a tip portion (207) which extends from the root portion (209) away from the wind turbine (100). A trailing edge insert (220) is positioned between the first shell portion (301) and the second shell portion (302) proximate the root portion (209). The trailing edge insert (220) has a surface (260) which extends between and separates the first shell portion (301) from the second shell portion (302) at the trailing edge (203), such that the insert (220) provides a high lift profile for increased blade efficiency.
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公开(公告)号：EP2204577A3
公开(公告)日：2016-07-27
申请号：EP09178629.3
申请日：2009-12-10
发明人： Bell, Eric , Gann, Matthew , Livingston, Jamie , Sultan, Mohamad , Walker, Alan
IPC分类号： F03D1/06
CPC分类号： F03D1/06 , F05B2240/30 , Y02E10/721 , Y10T29/49336 , Y10T29/49337
摘要： A blade (108) for use in the generation of power has a leading edge (201) and a trailing edge (203). A first shell portion (301) of the blade (108) extends from the leading edge (201) to the trailing edge (203). A second shell portion (302) of the blade (108) also extends from the leading edge (201) to the trailing edge (203). A root portion (209) of the blade (108) is positioned proximate the wind turbine (100) and a tip portion (207) which extends from the root portion (209) away from the wind turbine (100). A trailing edge insert (220) is positioned between the first shell portion (301) and the second shell portion (302) proximate the root portion (209). The trailing edge insert (220) has a surface (260) which extends between and separates the first shell portion (301) from the second shell portion (302) at the trailing edge (203), such that the insert (220) provides a high lift profile for increased blade efficiency.
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公开(公告)号：EP0486133B1
公开(公告)日：1996-12-18
申请号：EP91306338.4
申请日：1991-07-12
CPC分类号： F23R3/002 , B23K26/389 , F02K1/822 , F05D2260/202 , Y02T50/67 , Y02T50/671 , Y02T50/676
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7.发明公开
公开(公告)号：EP0735239A1
公开(公告)日：1996-10-02
申请号：EP96300493.2
申请日：1996-01-24
发明人： Walker, Alan , Staley, Terril K.
CPC分类号： F01D5/143 , F01D1/04 , F05D2230/61 , Y10S415/912 , Y10T29/49238 , Y10T29/49321 , Y10T29/49323
摘要： Power generation turbines having different power outputs for different power grid frequency applications have modular second and third stages, rotors, bucket wheels for all stages and other ancillary parts. The first and second turbines have sizes not geometrically scaled according to speed. Four-stage turbines having different outputs for different power grid frequencies not geometrically scaled have an identical annulus through the first, second and third stages, different geometry in the first and fourth stages, and identical geometry in the second and third stages.
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8.发明公开Boltless turbine nozzle/stationary seal mounting 失效Bolzenlose Befestigung von einerTurbinendüseand einerStationärgleitdichtung。
公开(公告)号：EP0513956A1
公开(公告)日：1992-11-19
申请号：EP92300196.0
申请日：1992-01-09
IPC分类号： F01D9/04
摘要： The invention comprises the use of a split retaining ring (110) cooperating with an inner nozzle support member (60) to retain nozzle segments and a stationary seal (130) without the use of threaded fasteners. Elimination of bolt heads from the rotor/stator cavity reduces windage losses and enables a shortening of the inner nozzle band overhang, reducing the requirement for high pressure cooling and cavity purge air.
摘要翻译： 本发明包括使用与内部喷嘴支撑构件（60）配合的分离保持环（110），以不使用螺纹紧固件来保持喷嘴段和固定密封件（130）。 从转子/定子腔中消除螺栓头减少了风阻损失，并且能够缩短内部喷嘴带的伸出，减少了对高压冷却和空腔吹扫空气的要求。
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公开(公告)号：EP0486133A1
公开(公告)日：1992-05-20
申请号：EP91306338.4
申请日：1991-07-12
CPC分类号： F23R3/002 , B23K26/389 , F02K1/822 , F05D2260/202 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A gas turbine engine combustor is provided, having a single wall sheet metal liner which is generally annular in shape which may be corrugated and a multi-hole film cooling means which includes at least one pattern of a great many small closely spaced sharply downstream angled film cooling holes [80] disposed essentially along portion of the liner to be cooled. Another embodiment provides a corrugated aircraft engine afterburner sheet metal liner having at least one pattern of great many small closely spaced sharply downstream angled film cooling holes disposed essentially along the entire surface of the liner.
摘要翻译： 提供了一种燃气涡轮发动机燃烧器，其具有单个壁板金属衬套，其大致为环形形状，其可以是波纹状的，以及多孔膜冷却装置，其包括至少一个图案，其具有许多小的紧密间隔的急剧下游的成角度的膜 基本上沿着待冷却衬管的部分设置冷却孔[80]。 另一实施例提供了一种瓦楞飞机发动机加力板金属衬套，其具有基本上沿着衬套的整个表面设置的许多小的紧密间隔的急剧下游的成角度的薄膜冷却孔的至少一种图案。
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