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公开(公告)号：EP3650648A1
公开(公告)日：2020-05-13
申请号：EP19208287.3
申请日：2019-11-11
摘要： A gas turbine engine article includes an article wall (68) that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall (68) defines a cavity (74). A cooling passage network (76) is embedded in the article wall (68) between inner and outer portions (68a, 68b) of the article wall (68,). The cooling passage network (76) has an inlet orifice (78) through the inner portion (68a) of the article wall (68) to receive cooling air from the cavity (74), a plurality of sub-passages that extend axially from the at least one inlet orifice (78), at least one outlet orifice (85) through the outer portion (68b) of the airfoil wall, and trip strips for mixing cooling air in the cooling passage network (76).
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公开(公告)号：EP3502420A1
公开(公告)日：2019-06-26
申请号：EP18215396.5
申请日：2018-12-21
摘要： Components for gas turbine engines are provided. The components (400) include a hybrid skin core cooling cavity (414) defined by a cold wall (420) and a hot wall (418), wherein the hot wall is exposed to an exterior environment of the component, a hybrid resupply hole (426) formed in the cold wall and fluidly connecting a cold cavity (416) and the hybrid skin core cooling cavity, and a resupply cover (432) located on the cold wall and within the hybrid skin core cooling cavity and positioned relative to the hybrid resupply hole to shield resupply air injected from the cold cavity into the hybrid skin core cooling cavity to minimize losses as the resupply air mixes with air flowing within the hybrid skin core cooling cavity.
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公开(公告)号：EP3650649A1
公开(公告)日：2020-05-13
申请号：EP19208288.1
申请日：2019-11-11
摘要： An airfoil (60) includes an airfoil wall (68) that defines leading and trailing ends (LE, TE) and first and second sides (70, 72) that join the leading and trailing ends (LE, TE). The airfoil wall (68) circumscribes an internal core cavity (74). A cooling passage network (76, 176) is embedded in the airfoil wall (68) between inner and outer portions (68a, 68b) of the airfoil wall (68). The cooling passage network (76, 176) has an inlet orifice (78) through the inner portion (68a) of the airfoil wall (68) to receive cooling air from the internal core cavity (74), a sub-passage region (82) that includes an array of pedestals (82a), and at least one outlet orifice (86) through the outer portion (68b). The outer portion (68b) of the airfoil wall (68) has a protrusion in the cooling passage network (76, 176) that faces toward the inlet orifice (78).
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公开(公告)号：EP3650642A1
公开(公告)日：2020-05-13
申请号：EP19208027.3
申请日：2019-11-08
IPC分类号： F01D5/18
摘要： An airfoil (60) includes an airfoil section (66) that has an airfoil wall (68) that defines an arced leading end (68a), a trailing end (68b), and first and second sides (68c, 68d) that join the arced leading end (68a) and the trailing end (68b). The first and second sides (68c, 68d) span in a longitudinal direction (Al) between first and second ends (68e, 68f). The airfoil wall (68) circumscribes an internal core cavity (70). There is an arced rib (72) in the internal core cavity (70). A cooling passage network (74) is embedded in the airfoil wall (68) between inner and outer portions (68g, 68h) of the airfoil wall (68). The cooling passage network (74) has a trailing edge (80) and an arced leading edge (76).
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公开(公告)号：EP3650651A1
公开(公告)日：2020-05-13
申请号：EP19208400.2
申请日：2019-11-11
IPC分类号： F01D5/18
摘要： An airfoil section (66) has an airfoil wall (68) that defines a leading end (68a), a trailing end (68b), and first and second sides (68c, 68d) that join the leading end (68a) and the trailing end (68b). The airfoil wall (68) circumscribes an internal core cavity (70). A skincore passage (74) is embedded in the first side (68c) of the airfoil wall (68) between inner and outer portions (76, 78) of the first side (68c) of airfoil wall (68). The skincore passage (74) defines a passage forward edge (74a) and a passage aft edge (74b). The first side (68c) of the airfoil wall (68) has a portion (86) that tapers in thickness at the passage aft edge (74b). A cooling passage (80) is embedded in the second side (68d) of the airfoil wall (68) between inner and outer portions (82, 84) of the second side (68d) of airfoil wall (68). The inner portion (82) of the second side (68d) of the airfoil wall (68) includes a protrusion (88) located across the internal core cavity (70) from the portion (86) of the first side (68c) that tapers in thickness.
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公开(公告)号：EP3650641A1
公开(公告)日：2020-05-13
申请号：EP19207980.4
申请日：2019-11-08
摘要： An airfoil (60) includes a cooling passage circuit (76) that has a first plenum (78), a skincore passage (82), a first connector passage (80), a second plenum (86), and a second connector passage (84). The first plenum (78) is in a first platform (62) and extends adjacent a first side (68c), a trailing end (68b), and a second side (68d) of an airfoil section (66). The skincore passage (82) is embedded in the first side (68c) of the airfoil section (66) and extends longitudinally. The first connector passage (80) is longitudinally spaced from an internal core cavity (70) in the airfoil section (66) so as to extend around the cavity (70). The first connector passage (80) connects the first plenum (78) with the skincore passage (82). The second plenum (86) is in the second platform (64) and extends adjacent the first side (68c), the trailing end (68b), and the second side (68d) of the airfoil section (66). The second connector passage (84) connects the skincore passage (82) with the second plenum (86).
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公开(公告)号：EP3584409A1
公开(公告)日：2019-12-25
申请号：EP19180982.1
申请日：2019-06-18
IPC分类号： F01D5/18
摘要： A turbine airfoil (60) includes an airfoil outer wall (66) that defines leading and trailing ends (LE,TE) and first and second sides (68a,68b) that join the leading and trailing ends (LE,TE). At least one cooling passage (74) is embedded in the airfoil outer wall (66) and has a radially-elongated entrance manifold (76), a radially-elongated diffuser orifice (78) that opens to an exterior surface of the airfoil outer wall (66), and a bank of sub-passages (80) fluidly connecting the radially-elongated entrance manifold (76) with the radially-elongated diffuser orifice (78). The radially-elongated diffuser orifice (78) is sloped relative to the radially-elongated entrance manifold (76).
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公开(公告)号：EP3502420B1
公开(公告)日：2020-09-09
申请号：EP18215396.5
申请日：2018-12-21
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公开(公告)号：EP3650650A1
公开(公告)日：2020-05-13
申请号：EP19208383.0
申请日：2019-11-11
IPC分类号： F01D5/18
摘要： An airfoil (60) includes an airfoil section (66; 166) that has an airfoil wall (68) that defines a leading end (68a), an arced trailing end (68b), and first and second sides (68c, 68d) that join the leading end (68a) and the arced trailing end (68b). The first and second sides (68c, 68d) span in a longitudinal direction (Al) between first and second ends (68e, 68f). The airfoil wall (68) circumscribes an internal core cavity (70) that includes an exit region (74, 174) that spans between the first and second ends (68e, 68f) and that opens through the arced trailing end (68b). The exit region (74; 174) includes pedestals (76) arranged in a plurality of longitudinal pedestal rows (78, 178). At least one of the longitudinal pedestal rows (78; 178) is straight and at least one of the longitudinal pedestal rows (78; 178) is arced.
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公开(公告)号：EP3650643A1
公开(公告)日：2020-05-13
申请号：EP19208065.3
申请日：2019-11-08
摘要： An airfoil (60) includes an airfoil section (66) that has an airfoil wall (68) that define leading and trailing ends (68a, 68b) and first and second sides (68c, 68d) that join the leading and trailing ends (68a, 68b). The first and second sides (68c, 68d) span in a longitudinal direction (Al) between first and second ends (68e, 68f). The airfoil wall (68) circumscribes an internal core cavity (70). The airfoil section (66) extends from a platform (62). The platform (62) defines a shelf (72) that extends forward from the first end (68e) at the leading end (68a) of the airfoil section (66) to a platform leading edge (72a), aft from the first end (68e) at the trailing end (68b) of the airfoil section (66) to a platform trailing edge (72b), laterally from the first end (68e) at the first side (68c) of the airfoil section (66) to a first platform side edge (68c), and laterally from the first end (68e) at the second side (68d) of the airfoil section (66) to a second platform side edge (68d). The internal core cavity (70) extends from the airfoil section (66) into the shelf (72).
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