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公开(公告)号：US20150159490A1
公开(公告)日：2015-06-11
申请号：US14625734
申请日：2015-02-19
Applicant: ALSTOM Technology Ltd
Inventor： Joerg KRUECKELS , Brian Kenneth Wardle , Herbert Brandl , Marc Widmer
CPC classification number: F01D5/189 , B22C9/24 , F01D5/186 , F01D9/02 , F05D2260/201 , F05D2260/202
Abstract: The invention refers to an internally cooled casted airfoil for a rotary machine, preferably a gas turbine engine comprising a suction and a pressure side wall each extending in an axial direction, i.e. from a leading to a trailing edge region of said airfoil. At least one suction wall sided cooling channel extends in axial direction confined by the suction side wall and a first inner wall. At least one pressure wall sided cooling channel extends in axial direction confined by the pressure side wall and a second inner wall. At least one feed chamber is defined between the first and second inner wall for feeding said at least one suction and pressure sided cooling channel each by at least one through hole inside of the first and second inner wall. At least one suction wall sided cooling channel and the at least one pressure wall sided cooling channel extend into the trailing edge region separately. At least one suction wall sided cooling channel and at least one pressure wall sided cooling channel join before discharging at the trailing edge.
Abstract translation: 本发明涉及一种用于旋转机器的内部冷却铸造翼型件，优选地是包括抽吸和压力侧壁的燃气涡轮发动机，其各自在轴向方向上延伸，即从所述翼型的导向到后缘区域延伸。 至少一个抽吸壁侧冷却通道在被吸入侧壁和第一内壁限制的轴向方向上延伸。 至少一个压力壁侧冷却通道在受压侧壁和第二内壁限制的轴向方向上延伸。 至少一个进料室限定在第一和第二内壁之间，用于将第一和第二内壁内的至少一个通孔各自供给至少一个吸入和压力侧冷却通道。 至少一个抽吸壁侧冷却通道和至少一个压力壁侧冷却通道分别延伸到后缘区域。 至少一个抽吸壁侧冷却通道和至少一个压力壁侧冷却通道在后缘排放之前连接。
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公开(公告)号：US09890646B2
公开(公告)日：2018-02-13
申请号：US14625734
申请日：2015-02-19
Applicant: ALSTOM Technology Ltd
Inventor： Joerg Krueckels , Brian Kenneth Wardle , Herbert Brandl , Marc Widmer
CPC classification number: F01D5/189 , B22C9/24 , F01D5/186 , F01D9/02 , F05D2260/201 , F05D2260/202
Abstract: An internally cooled airfoil for a rotary machine, for example, a gas turbine engine includes a suction and pressure side wall each extending in an axial direction, i.e. from a leading to a trailing edge of the airfoil. A suction wall sided cooling channel and a pressure wall sided cooling channel extend in the axial direction. A feed chamber is defined between a first and second inner wall for feeding the suction wall and pressure wall sided cooling channel each by at least one through hole inside of the first and second inner wall. The suction wall sided cooling channel and the pressure wall sided cooling channel extend into the trailing edge region separately. The suction wall sided cooling channel and the pressure wall sided cooling channel join before discharging at the trailing edge.
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